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NASA 2009 SBIR Phase 2 Solicitation


PROPOSAL NUMBER: 09-2 A1.02-8576
PHASE-1 CONTRACT NUMBER: NNX10CE66P
SUBTOPIC TITLE: Sensing and Diagnostic Capability for Aircraft Aging and Damage
PROPOSAL TITLE: Automated NDE Flaw Mapping System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cybernet Systems Corporation
727 Airport Boulevard
Ann Arbor, MI 48108-1639
(734) 668-2567

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ryan O'Grady
proposals@cybernet.com
727 Airport Blvd
Ann Arbor,  MI 48108-1639
(734) 668-2567

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's Aircraft Aging and Durability Project (AADP) aims to ensure the safety of both commercial and military aviation aircraft. Non-destructive evaluation (NDE) techniques are integral to this effort. In particular, NDE techniques are used to a) detect and characterize damage to aircraft and b) validate models of materials through iterative testing. The costs associated with the acquisition of major aircraft require a long usage period in order to obtain a good return on investment. The commercial and military aircraft fleets are inspected and maintained to produce a long operational life. However, many of the NDE techniques are slow, tedious, and costly. Interestingly, the technologies used to inspect aircraft to detect flaws are quite sophisticated, but tools for keeping track of these flaws, their location, and evolution over time are haphazard and inspection-specific, so they are not easily generalized to inspections in general. We propose to leverage our machine vision technology to help automate portions of the inspection process to greatly reduce the time and cost associated with the inspection task. In this approach, machine vision is used to localize the sensor scan information gathered during inspection so that it can be viewed and manipulated in the context of a 3D CAD model of the inspected object. This then helps support the prediction of flaw propagation and structure life. The system allows maintainers to accurately collect information about flaws and accurately integrate them into CAD models. The models can then be leveraged in finite element analysis tools to help predict flaw and material behavior.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology is initially being developed to support the non-destructive inspection of large aerospace structures, such as aircraft and spacecraft. The technology will allow maintainers to more rapidly complete inspections of large surfaces and record the data for historical perspective and future use. The system will help identify the specific location of where flaws exist on the test object and integrate the flaw data into the 3D CAD model so that the flaw data can be used within finite element analysis programs to predict flaw propagation and material life. The system will be applied to aid in the prediction of how aircraft and spacecraft components age and can be applied to testing of failed aircraft components to help identify root causes of crashes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology can also be applied to use in the commercial and military aviation markets. The average age of military aircraft is actually older than the average age of commercial aircraft and is therefore an ideal target for the proposed system. Therefore, we will leverage our existing contacts in the DoD to find potential end users for the technology. Commercial airlines also have a requirement to inspect aircraft. Therefore, we will also target commercial airlines as a potential application space.

TECHNOLOGY TAXONOMY MAPPING
Structural Modeling and Tools


PROPOSAL NUMBER: 09-2 A1.03-8806
PHASE-1 CONTRACT NUMBER: NNX10CE67P
SUBTOPIC TITLE: Prediction of Aging Effects
PROPOSAL TITLE: DARWIN-HC: A Tool to Predict Hot Corrosion of Nickel-Based Turbine Disks

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2559
(434) 973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Burkholder
burkholder@bainet.com
1410 Sachem Place, Suite 202
CHarlottesville,  VA 22901-2559
(434) 973-1215

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Hot Corrosion of turbine engine components has been studied for many years. The underlying mechan-isms of Type I Hot Corrosion and Type II Hot Corrosion are increasingly well-understood. Modern turbine engine designs that seek to achieve better fuel efficiency in part by increasing turbine inlet temperatures are strong candidates for nickel-based superalloy turbine disk materials. As disk temperatures approach 700C, designers must consider the likelihood and effects of Type II corrosion. Type II corrosion is typically characterized by localized corrosion pitting caused by melting of sulfur-containing salts. Type II hot corrosion pits have been shown to decrease the fatigue resistance of superalloys due to initiation of fatigue cracks at hot corrosion pits. However, the rigorous analytical models and tools needed by turbine engine designers to predict Type II corrosion effects are not currently available. The overall objective of this research program will be to develop DARWIN-HC ? a probabilistic Type II hot corrosion, fatigue cracking, and fatigue life prediction software tool for nickel-based superalloy turbine disks. The Phase I research was based on data provided by both NASA and the research team. The key Phase I innovations included enhanced probabilistic models that are explicitly parameterized by the relevant environmental and material variables. The models are a significant step towards modeling the spatial and temporal evolutions of corrosion pits ? setting the stage for the development of fatigue life prediction capability. Whereas the existing DARWIN software contains probabilistic models of hard alpha anomalies in titanium disk materials, DARWIN-HC will feature the probabilistic models of defect distributions due to Type II hot corrosion, which can lead to fatigue crack initiation. In Phase II, the team will create a functional DARWIN-HC prototype software application for evaluation by NASA and industry.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA aeronautics defined eight challenge problems for which the Aircraft Aging and Durability (AAD) Project can deliver specific research products to address aeronautics community needs. While the re-search challenges address different aircraft components and specific aging-related issues, the research results will improve the ability to detect, predict, and manage aging hazards. One of these eight challenge problems is "Durability of Engine Superalloy Disks". The research focus is the durability of new disk alloys at higher operating temperatures to enable improved engine efficiency. To improve durability of these new superalloy disks, the issues of microstructural instability, hot corrosion, and fatigue durability must be addressed. Goals include establishment of a long-term database and derivation of analytic models to predict the degradation of new alloys due to microstructural instability and corrosion. The proposed research effort directly addresses these important challenges.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The initial Non-NASA commercialization strategy is straightforward and significantly bolstered by the strength of the research team, the numerous industry contacts, and the existing DARWIN software infrastructure and support. The commercial product output of the proposed SBIR effort will be DARWIN-HC --- an extension of an existing FAA-sponsored software tool that predicts the probability of fracture of titanium aircraft turbine rotor disks to model and predict the effects of Type II hot corrosion. DARWIN is rapidly gaining acceptance in the aerospace community and DARWIN-HC will further expand the applicability and reach of the DARWIN product line. The most direct commercialization route is via collaboration with the major airframers. Fortunately, Barron Associates has strong, existing working relationships with these companies. As parallel research advances at the major aerospace companies, BAI will pursue commercialization and collaboration opportunities. Although it is difficult to predict the rate of advancement of the ongoing research activities upon which future commercialization may depend, even a relatively small market can play a significant role in our growth as a company.

TECHNOLOGY TAXONOMY MAPPING
Aircraft Engines


PROPOSAL NUMBER: 09-2 A1.04-9447
PHASE-1 CONTRACT NUMBER: NNX10CE68P
SUBTOPIC TITLE: Aviation External Hazard Sensor Technologies
PROPOSAL TITLE: Molecular Air Data Clear Air Turbulence Sensor: MADCAT

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Michigan Aerospace Corporation
1777 Highland Drive, Suite B
Ann Arbor, MI 48108-2285
(734) 975-8777

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Doninique Fourguette
dfourguette@michaero.com
1777 Highland Drive, Suite B
Ann Arbor,  MI 48108-2285
(734) 975-8777

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Clear air turbulence (CAT), often referred to as "air pockets," is attributed to Kelvin-Helmholtz instabilities at altitudes usually above 18,000ft, often without visual cues (clouds, etc.), making it difficult to avoid. The vortices produced when atmospheric waves "break" can have diameters of 900-1200ft and tangential velocities of 70-85 ft/sec. CAT is dangerous to aircraft, recently demonstrated by United flight 967 from Washington-Dulles to Los Angeles on July 21, 2010, which encountered severe turbulence and landed in Denver with over 30 injured passengers, 21 requiring a hospital visit. Many other turbulence incidents have caused injuries or deaths to passengers and crew. Another recently-highlighted hazard is the inadequacy of current airspeed sensors on commercial aircraft. Federal investigators have reported that on at least a dozen recent flights by U.S. jetliners, malfunctioning equipment made it impossible for pilots to know how fast they were flying. A similar issue is believed to have played a role in the June 2009 crash of Air France 447 that killed all 228 people aboard. Michigan Aerospace Corporation (MAC) proposes the Molecular Air Data and Clear Air Turbulence (MADCAT) system which will be capable of providing not only a look-ahead capability to predict clear air turbulence but also a full air data solution (airspeed, angle of attack, angle of sideslip, pressure and temperature). The technology has already been demonstrated in-flight, confirming its ability to measure these air-data parameters. In addition, ground units based upon the same core technology have demonstrated the ability to detect atmospheric turbulence. MAC's direct-detection UV LIDAR technology uses molecular backscatter and does not require airborne particles and/or vapor to be suspended in the air, as other proposed solutions based on radar and LIDAR do. This Phase 2 project will result in a laboratory test model of MADCAT and a plan for subsequent airborne testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MADCAT will allow NASA aircraft the benefit of having a clear-air turbulence warning system and an optical air data system in one package, suitable for general use by NASA aircraft as well as for flight research concerning clear-air turbulence and scientific studies of atmospheric processes. Ground-based research uses include measuring wind speed and direction along with air temperature and density while also detecting and characterizing turbulence; this could find use in large wind tunnels and near airports.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Clear-air turbulence represents a significant hazard and passenger-comfort issue, and the proposed MADCAT system will be very useful for commercial aircraft not only as a turbulence-warning solution, but also as an air data system that is more reliable than current speed-sensing technologies. Information on winds near aircraft, if downlinked and compiled, will be of significant value to weather forecasters, especially from aircraft flying over areas (oceans, etc.) where balloon radiosonde releases and other wind measurements are sparse or non-existent; the National Weather Service lists the lack of more comprehensive wind-profile data as a major unmet data need for accurate, longer-range forecasts. Turbulence detection with wind speed and direction data will find ground-based uses for wind farms (to detect approaching turbulence, gusts and direction changes, allowing corrective action) and for the military (in artillery and other munitions delivery and in the airdrop of supplies).

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Optical


PROPOSAL NUMBER: 09-2 A1.05-8718
PHASE-1 CONTRACT NUMBER: NNX10CE69P
SUBTOPIC TITLE: Crew Systems Technologies for Improved Aviation Safety
PROPOSAL TITLE: Simulator Evaluation of a Joint Human/Automated Upset Recovery System and Training Aid

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2559
(434) 973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Neha Gandhi
barron@bainet.com
1410 Sachem Place, Suite 202
Charlottesville,  VA 22901-2559
(434) 973-1215

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Loss of control is a significant cause of aviation accidents attributed to a large percentage of fatalities in the commercial aviation sector. Recently, Barron Associates, Inc. (BAI) has developed a system for unmanned aerial vehicles that autonomously executes recovery strategies to rapidly restore nominal flight. During Phase I, BAI sought to extend this system to manned vehicles by developing a joint human-automated (H/A) system. The goal of this system is to assist the crew during the recovery process by conveying information about recovery procedures in an intuitive and unobtrusive manner. BAI developed crew-specific extensions to the automated system both at the architecture and interface level. The architecture defines what information is delivered to the crew. The interface defines how this information is presented to the crew. Metrics were defined to measure the quality of the recovery and crew experience. Phase I pilot-in-the-loop experiments have shown there is the potential for significant performance gains and workload reduction if the joint H/A recovery system is used to guide the pilot through the recovery process. Phase I experiments were limited in scope. During Phase II, BAI would like to build upon these results by demonstrating that gains become even more pronounced in a realistic cockpit environment. This will require migrating to a higher-quality simulator and more accurately simulating the duties of the crew. The team will target ATPs (Airline Transport Pilots) during Phase II and expand the subject population so that the benefit of the system can be explicitly quantified. While integration into the cockpit is the ultimate goal for this system, BAI believes that the joint H/A recovery system can be of immediate use as a training aid. As part of the experimental build-up, BAI would also like to show that the use of the joint H/A recovery system during training translates into improved pilot recoveries when the system is not active.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
One of the overarching goals of the NASA's Aviation Safety Program is to improve aircraft safety for current and future aircraft. As loss of control accounts for a significant percentage of the fatal accident rate, developing systems that improve the response to upset conditions in flight are critical to achieving this goal. Joint H/A upset recovery research sits as the junction of two integral components of the Aviation Safety Program: Integrated Resilient Aircraft Control research and Integrated Intelligent Flight Deck research. The former seeks to "arrive at a set of validated multidisciplinary integrated aircraft control design tools and techniques for enabling safe flight in the presence of adverse conditions (e.g. faults, damage and/or upsets)." The latter seeks to "establish transformative integrated display concepts, decision support functions, on-board/off-board information management, high-integrity external hazard detection, and effective mechanisms for human-automation interaction that enable safer flight deck systems for NextGen." The current research seeks to not only transform state-of-the-art automated methods for upset recovery into a powerful decision aid system but to extend human-automation interaction to create a system capable of exploiting H/A collaboration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The immediate application for the proposed technology is in the civilian aerospace sector to improve aviation safety and security. However, the technology will readily extend to military aviation and space exploration. The increasing prevalence of remotely-piloted UAVs for military and homeland security applications, their consideration for terrestrial science missions and planetary exploration in the near-to-mid term, and the likely ubiquitous commercial roles of these vehicles in the longer-term, provide numerous opportunities for the transition of the proposed SBIR technologies. Application potential is not limited to the aerospace industry, but is extensible to all systems where a human operator can be assisted by an automated agent. Another application is the use of the joint H/A recovery system as a training aid. The low revenues in the regional airline industry have led to hiring practices that bring in unseasoned pilots with minimal flight experience and training. During Phase II, the authors will have gathered initial data on the utility of training with the joint H/A recovery system in both a desktop simulator as well as higher-fidelity fixed-base simulator. Armed with positive results, the authors can aggressively market this system to regional carriers as a low-cost training solution.

TECHNOLOGY TAXONOMY MAPPING
Attitude Determination and Control
Guidance, Navigation, and Control
Pilot Support Systems


PROPOSAL NUMBER: 09-2 A1.06-8711
PHASE-1 CONTRACT NUMBER: NNX10CC01P
SUBTOPIC TITLE: Technologies for Improved Design and Analysis of Flight Deck Systems
PROPOSAL TITLE: Integrated Design and Analysis Environment for Safety Critical Human-Automation Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2559
(434) 973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael DeVore
devore@bainet.com
1410 Sachem Place, Suite 202
Charlottesville,  VA 22901-2559
(434) 973-1215

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Numerous advances have been made in recent years in the areas of flight deck design, aircraft modeling, resilient control, and vehicle health management. The combination of these complementary technologies promises to revolutionize aircraft systems and operations safety in the decades ahead. However, the task of safely integrating these technologies is becoming increasingly difficult as their level of complexity, degree of automation, and demands from their operational environment grow. The Next Generation Air Transport System (NextGen), while providing significant benefits in terms of increased capacity and safety, will exacerbate this situation due to the large numbers of new and existing systems that will be required to interoperate. The multidisciplinary nature of these systems is a significant factor that makes analyzing their safety characteristics extremely difficult. While many development tools exist to conduct deep analyses within individual disciplines, there is a lack of tools available for deep analysis of complex multidisciplinary designs. The proposed research seeks to create a new class of development tool that will allow designers of complex systems-of-systems to explore the dynamic interactions between system components to uncover systemic vulnerabilities, precursory conditions, and likely outcomes. The Phase I project generated an initial implementation of the software package Idea, an Integrated Design and Analysis Environment that could be used to model complex interdependencies between flight deck operations, flight deck controls and display, and the underlying physical components of the aircraft. The proposed Phase II effort will mature this software and expand its capabilities, resulting in a flexible, standards-compliant tool that is ready for beta testing and subsequent commercialization. It will focus on enhancements that support cross-disciplinary modeling and analysis of safety-critical human-automation systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Initial applications of the proposed technology are envisioned to be within NASA's Aviation Safety Integrated Intelligent Flight Deck program. The software has direct application in the design and analysis of flight deck systems and of distributed systems that intersect with flight deck operations. The tool's features are motivated by the particular combination of challenges encountered in flight deck design (complex, safety critical, multidisciplinary, mixed human and automation systems, etc.), and this same combination arises in many other contexts related to aircraft and spacecraft operations. Moreover, the software is highly customizable and can be modified to support a wide variety of engineering disciplines. The software can therefore be of significant benefit to a wide variety of systems engineering projects, especially those that involve integration of multiple subsystems for which safety analyses are difficult to conduct manually, including projects associated with the NextGen Air Transport System.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
As the tool is intended to initially support design of commercial flight deck systems, the closest non-NASA commercial application will be in the design of military flight deck systems and related components. Other directly related applications include UAV, UGV, and UUV operator interfaces and supporting systems. Because of the tool's flexibility and general applicability to large-scale systems engineering projects, there is an essentially unlimited number of potential applications outside the government. The best candidates are those that involve complex system-of-systems designs. Examples include the automotive industry, the health care and medical device industries, the telecommunications industry, and large portions of the information technology sector. Many of these have already begun to adopt model-based design and other system engineering technologies that are consistent with the use of this tool.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Human-Computer Interfaces
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A1.07-9237
PHASE-1 CONTRACT NUMBER: NNX10CC56P
SUBTOPIC TITLE: Adaptive Aeroservoelastic Suppression
PROPOSAL TITLE: Real-Time Methods for Adaptive Suppression of Adverse Aeroservoelastic Dynamics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Systems Technology, Inc.
13766 Hawthorne Blvd.
Hawthorne, CA 90250-7083
(310) 679-2281

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Cecy Pelz
cecy@systemstech.com
13766 Hawthorne Blvd.
Hawthorne,  CA 90250-7083
(310) 679-2281

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Adverse aeroservoelastic interaction is a problem on aircraft of all types causing repeated loading, enhanced fatigue, undesirable oscillations and catastrophic flutter. Traditionally, to suppress adverse aeroservoelastic interaction, notch and/or roll off filters are used in the primary flight control system architecture. This solution has pitfalls; rigid body performance is degraded due to resulting phase penalty and it is not robust to off nominal behavior. In Phase I, an approach was developed that is entitled, Modal Isolation and Damping for Adaptive Aeroservoelastic Suppression (MIDAAS). This adaptive technique determines an optimal blend of multiple outputs that effectively isolates a problematic lightly damped mode and simultaneously determines an optimal blend of multiple inputs to suppress the problematic mode via feedback. Adverse effects on aircraft rigid body performance are minimized, resulting in virtually no phase penalty. MIDAAS was validated against aeroservoelastic F/A-18C aircraft models with varying stores configurations and demonstrated very successful performance. In the proposed Phase II program, a robust real-time adaptive aeroservoelastic suppression solution will be developed with a buildup approach that includes further MIDAAS enhancements, extensive validation studies utilizing a high-fidelity CFD-based aeroelastic model of the NASA X-53 aircraft, and extensive validation studies utilizing real-time pilot in the loop simulation capability.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is a research leader in the areas of aeroelasticity, flight dynamics, control, and flight testing. The proposed work here naturally follows from and compliments these areas with a specific focus on adaptive suppression of adverse aeroservoelastic phenomena. This program also fits the needs of the NASA Integrated Resilient Aircraft Control (IRAC) project by supplying a robust adaptive solution to controlling adverse conditions in the presence of off nominal system variations. Safe flight is further ensured by the comprehensive validation approach that includes real-time piloted simulations. NASA aeronautics centers (DFRC, LaRC, ARC) have the most potential benefit but the program may also be beneficial to NASA space programs (i.e., suppression of high frequency resonance in spacecraft and rocket systems). The proposed program will lead to a commercial software and hardware simulation product targeted at aeroservoelastic aircraft systems providing a valuable asset for many NASA programs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Performance degradation due to adverse aeroservoelastic effects is ubiquitous and hence the core methodology can be applied in a variety of areas. Other aerospace applications include rotorcraft systems, rocket booster and spacecraft structural mode detection and control. Outside of aerospace, other areas of application include automotive (for engine and vehicle dynamic monitoring and control), industrial manufacturing (for rejection of machine noise and structural vibrations), infrastructure (for monitoring buildings, bridges, etc., for changes in stiffness and damping and subsequent active suppression of adverse dynamics), and alternative energy (aeroservoelastic suppression for wind turbine technology). Beyond industry there are potential post applications within the US military. Aeroelastic analysis and testing will benefit from the proposed program at military facilities such as the Air Force Flight Test Center at Edwards AFB, the Air Armament Center at Eglin AFB and the Naval Air Warfare Center Weapons Division at China Lake.

TECHNOLOGY TAXONOMY MAPPING
Controls-Structures Interaction (CSI)
Simulation Modeling Environment
Structural Modeling and Tools
Guidance, Navigation, and Control
Sensor Webs/Distributed Sensors


PROPOSAL NUMBER: 09-2 A1.08-9406
PHASE-1 CONTRACT NUMBER: NNX10CC64P
SUBTOPIC TITLE: Engine Lifing and Prognosis for In-Flight Emergencies
PROPOSAL TITLE: Aircraft Engine Life-Consumption Monitoring for Real-Time Reliability Determination

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nastec, Inc.
5310 West 161 Street, Suite G
Brook Park, OH 44142-1601
(216) 464-8388

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Zaretsky
dczaretsky@gmail.com
5310 W. 161st Street, Suite G
Brook Park,  OK 44142-1601
(216) 464-8388

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The object of this research is to develop an in-service life-monitor system for the prediction of the remaining component and system life of aircraft engines. The embedded system will monitor the engines thrust, exhaust gas temperature, the engine efficiency, the speed and the time of operation of the engine in flight. Based upon this data, the life-estimation analog of the system will calculate the remaining lives of the components of the engine and combine these into a prediction of the remaining life of the engine. The calculations will be based on the statistical life distribution of the engine components and their relationship to load, speed, temperature and time. The monitoring device will be built for use with an operational aircraft engine.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA GRC is currently pursuing an overall agency-wide goal of increasing the flight safety of commercial aircraft. This is part of the NASA Aviation Safety Program. In pursuit of that goal, the analytical life prediction codes that are currently used to predict the service life of aircraft engines are being investigated; so that, NASA GRC can establish appropriate programmatic plans to address the deficiencies that now exist in those methods and approaches. By addressing these deficiencies, NASA and industry can cooperatively achieve the increase flight safety goals through a better understanding of the service life of aircraft engines. Our SBIR effort will provide NASA and industry a mechanism to improve the safety, reliability and maintainability of commercial aircraft. It will improve the cost-effective design and manufacturing of new production engines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA GRC is currently pursuing an overall agency-wide goal to increase flight safety of commercial aircraft as part of the NASA Aviation Safety program. In pursuit of that goal, analytical life prediction codes currently used to predict the service life of aircraft engines are being investigated, so that, NASA GRC can establish appropriate programmatic plans to address the deficiencies that now exist in those methods and approaches. By addressing these deficiencies, NASA and industry can cooperatively achieve the increased flight safety goals through a better understanding of the service life of aircraft engines. This effort will provide industry a mechanism to improve the safety, reliability and maintainability of commercial aircraft. It will affect cost-effective design and manufacturing for new production engines and can reduce life cycle and maintenance costs.

TECHNOLOGY TAXONOMY MAPPING
Aircraft Engines


PROPOSAL NUMBER: 09-2 A1.09-9235
PHASE-1 CONTRACT NUMBER: NNX10CC02P
SUBTOPIC TITLE: Pilot Interactions with Adaptive Control Systems under Off-Nominal Conditions
PROPOSAL TITLE: Smart Adaptive Flight Effective Cue (SAFE-Cue)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Systems Technology, Inc.
13766 South Hawthorne Blvd.
Hawthorne, CA 90250-7083
(310) 679-2281

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Klyde
dklyde@systemstech.com
13766 S Hawthrone Blvd.
Hawthorne,  CA 90250-7083
(310) 679-2281

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To enhance aviation safety, numerous adaptive control techniques have been developed to maintain aircraft stability and performance in the presence of failures or damage. Flight evaluations of various adaptive controllers conducted by NASA and others have shown great promise. In some cases unfavorable pilot-vehicle interactions including pilot-induced oscillations have occurred. Susceptibility to such interactions is more likely when the pilot interacts with a highly nonlinear vehicle that may no longer have predictable response characteristics. To alleviate these unfavorable interactions, Systems Technology, Inc. proposes the Smart Adaptive Flight Effective Cue or SAFE-Cue. This innovative system provides force feedback to the pilot via an active control inceptor with corresponding command path gain adjustments. The SAFE-Cue alerts the pilot that the adaptive control system is active, provides guidance via force feedback cues, and attenuates commands, thus ensuring pilot-vehicle system stability and performance in the presence of damage or failures. Phase 2 will build upon a successful Phase 1 demonstration wherein SAFE-Cue configurations eliminated pilot-vehicle system oscillation tendencies allowing the evaluation pilots to focus on the task rather than maintaining control. In this proposed program, a prototype SAFE-Cue will be developed and evaluated with exemplar adaptive controllers using the Calspan Learjet In-Flight Simulator.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The SAFE-Cue directly addresses a concern of the Integrated Resilient Aircraft Control topic under NASA's Aviation Safety Program to prevent pilot-vehicle system loss of control in the presence of an active adaptive control system. A successful Phase 2 will produce a prototype SAFE-Cue system that will alert the pilot regarding flight control system adaptations due to failures/damage and constrain the pilot via active inceptor force feedback and command path gain attenuation as a means to mitigate loss-of-control. While the SAFE-Cue system is designed to work with adaptive systems, the concept is general and has application to any flight control system. The interest in preventing loss-of-control is based on a very real problem that has caused loss of life and property throughout the history of flight. This system can be applied to NASA fixed wing and rotorcraft to provide an enhanced level of safety to NASA's flight test activities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Following the successful completion of a Phase 2 in-flight evaluation program, a prototype SAFE-Cue system will be ready to transition into a commercially viable product. For other government agencies, specifically the Department of Defense, the SAFE-Cue system will have high-value due to its potential to reduce loss-of-control accidents in the more extreme military operational environment. This includes the F-35 (all three variants), V-22 tilt-rotor, C-17 military airlifter, and the CH-53K helicopter. The F-35 and the forthcoming CH-53K both feature active pilot inceptors and are thus SAFE-Cue ready with this important technology piece in place. Regarding commercial aviation, the system will be particularly applicable to aircraft with modern FBW flight control systems. Initially, it will be targeted for use in the commercial aircraft fleet where it can add a significantly increased level of safety at a reasonable incremental cost.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Pilot Support Systems


PROPOSAL NUMBER: 09-2 A1.10-8957
PHASE-1 CONTRACT NUMBER: NNX10CC65P
SUBTOPIC TITLE: Detection of Aircraft Anomalies
PROPOSAL TITLE: In-Flight and Pre-Flight Detection of Pitot Tube Anomalies

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Analysis and Measurement Services Corporation
9111 Cross Park Drive, Building A-100
Knoxville, TN 37923-4510
(865) 691-1756

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bradley Orme
brad@ams-corp.com
9111 Cross Park Drive Building A
Knoxville,  TN 37923-4510
(865) 691-1756

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The health and integrity of aircraft sensors play a critical role in aviation safety. Unfortunately, inaccurate or false readings from these sensors can lead to improper decision-making resulting in serious and sometimes fatal consequences. The research performed in Phase I demonstrated the feasibility of using advanced data analysis techniques to identify anomalies in Pitot tubes resulting from blockage such as icing, moisture, or foreign objects. The core technology used in this project is referred to as "noise analysis" since it relates a sensor's response time to the dynamic component (noise) found in the signal of these same sensors. This analysis technique has used existing electrical signals of Pitot tube sensors that result from measured processes during in-flight conditions and/or induced signals in pre-flight conditions to detect anomalies in the sensor readings. AMS has routinely used this technology to determine the health of pressure transmitters in nuclear power plants. The application of this technology for the detection of aircraft anomalies is innovative in that instead of determining the health of process monitoring at a steady state condition, this technology will be used to quickly inform the pilot when an air speed indication becomes faulty under any flight condition as well as during pre-flight preparation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Although the general target for the end product of this research is in the commercial and private aircraft sectors, NASA and other governmental/military facilities would greatly benefit from this technology. As all aircraft rely on the accurate and reliable performance of Pitot/static systems, improving the detection of inaccurate indications would increase the safety of aircraft passengers and crew, reduce the potential for accidents, and will lead to other advances in aviation technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The intended end product of a Phase I and Phase II project is the development of hardware and/or software that can be used for the detection of Pitot tube anomalies resulting from blockages either during in-flight or pre-flight conditions. This end product, which will be commercialized by AMS in a Phase III project with non-federal funding, will have wide applications in the commercial, private, and military aircraft industries. Furthermore, it is envisioned that this new technology would be used not only for new aircraft, but also for existing aircraft with only minor modifications.

TECHNOLOGY TAXONOMY MAPPING
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Data Acquisition and End-to-End-Management
Portable Data Acquisition or Analysis Tools


PROPOSAL NUMBER: 09-2 A1.12-9941
PHASE-1 CONTRACT NUMBER: NNX10CC03P
SUBTOPIC TITLE: Prognosis of Aircraft Anomalies
PROPOSAL TITLE: Physical Modeling for Anomaly Diagnostics and Prognostics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ridgetop Group, Inc.
6595 North Oracle Road
Tucson, AZ 85704-5645
(520) 742-3300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Neil Kunst
neil.kunst@ridgetopgroup.com
6595 North Oracle Road
Tucson,  AZ 85704-5645
(520) 742-3300

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ridgetop developed an innovative, model-driven anomaly diagnostic and fault characterization system for electromechanical actuator (EMA) systems to mitigate catastrophic failures. Ridgetop developed a MIL-STD-1553 bus monitor and a MIL-STD-1553 bus controller that simulates the aircraft data bus, reads the environmental (i.e., altitude) and operational (i.e., response of system) data of a system and determines if a fault is manifesting; and if true determines the root cause and symptoms of the fault. Once an anomaly is detected, the Model-based Avionic Prognostic Reasoner (MAPR) solves a user-outlined state-space model, symbolically, using a Gauss-Newton optimization method and the information from the MIL-STD-1553 bus. This algorithm outputs a list of best fitting parameters to match the command to the actual performance. Rules are programmed in, based on results from principal component analysis . The rules determine both fault mode and the severity of that fault. The rules can distinguish between two failure modes: Mechanical jam and MOSFET failure, and healthy. The real-time processing will allow for critical evolutions in flight safety and provides a game-changing approach to condition-based maintenance. Once deployed, flight safety can be improved by allowing the on-board flight computers to read from the MAPR and update their control envelope based on its evaluations, reducing damage propagation and increasing operational safety. In Phase 2, we will develop a functioning ground-based prototype of the technology to show the efficacy of the method. A ground-based version of the tool is the best candidate for development to ease adoption by testing in a low-risk environment; this tool will be demonstrated at the end of Phase 2. The MAPR concept is also applicable to any system with a state-space representation but at this point it has been developed with EMAs in mind. The MAPR prototype is at TRL 5 and will reach a TRL 7 by the end of Phase 2.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Vehicles within the Europa mission, the International Space Station (ISS), and Mars Exploration Rover Project. The Europa mission has been designated by the Decadal Study as the highest-priority flagship mission for the next decade, and the Europa Geophysical Explorer (EGE) is likely to be the next large mission to the outer planets after Cassini. Applications in this program include fault-tolerant EMAs. Ridgetop plans to collaborate in the NASA IVHM program to aid in the detection, diagnosis and prognosis of avionics faults and malfunctions, actuator failure and damage, and avionics transient effects resulting from operation in a harsh environment (neutron particles, electromagnetic fields, lightning), including the Deep Space mission, and Exploration Technology Development Program Integrated Systems Health Management (ETDP-ISHM) and the X-37 program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Target markets for non-NASA commercial applications that utilize standard MIL-STD-1553, ARINC 429 communications between subsystems, and include government and commercial aerospace, automotive markets, satellites, and factory automation applications. For the aerospace market, Ridgetop will strategically partner with Boeing to integrate the technology at the component level (physical product) and the system level (aircraft platform). Leveraging existing relationships with key auto manufacturers such as Daimler, Ridgetop plans to integrate the proposed technology to add value to existing on-board diagnostic platforms with the consolidated sensor network and advanced reporting/data capabilities. The UAV market is growing, evidenced by increased demands and requirements for operational efficiency and duration. Recent breakthroughs in UAV power systems have presented a dynamic integration opportunity for the proposed fault detection software. From a marketing analysis, the total forecasted revenues from these markets are projected to reach $39 million over five years.

TECHNOLOGY TAXONOMY MAPPING
Intelligence
Mobility
Perception/Sensing
Guidance, Navigation, and Control
On-Board Computing and Data Management
Autonomous Control and Monitoring
Data Acquisition and End-to-End-Management
Expert Systems
Portable Data Acquisition or Analysis Tools
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A1.14-8756
PHASE-1 CONTRACT NUMBER: NNX10CC05P
SUBTOPIC TITLE: Verification and Validation of Flight-Critical Systems
PROPOSAL TITLE: A Software-Assurance Design Approach for NextGen Enabling Technologies

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2559
(434) 973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Aeillo
barron@bainet.com
1410 Sachem Place, Suite 202
Charlottesville,  VA 22901-2559
(434) 973-1215

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The United States air transportation system is not performing adequately even as aircraft operations increase. To address this problem, the Federal Aviation Administration and the Joint Planning and Development Office are developing the Next Generation Air Transportation System (NextGen). NextGen will enable critical advances to the current management of the National Airspace (NAS). The technologies that comprise NextGen offer the possibility of compelling new systems of systems that, if properly designed, will not only enhance the capabilities of the NAS but also improve its safety. At the same time, these fundamental changes bring with them implications for safety and security. In order to address these concerns, new techniques for the certification of software systems will be required to ensure that certification cost will not limit the safety innovations offered by NextGen advances. In Phase I, Barron Associates investigated the integration of ADS-B and TCAS as a representative NextGen system of systems and investigated the application of the system safety case to the system. In the proposed Phase II research, Barron Associates will develop a new collision-avoidance system and conduct an empirical study of the system safety case compared to DO-178B compliance as a certification approach. Throughout the development of the new collision-avoidance system, evidence in support of DO-178B compliance as well as in support of the safety case will be gathered. Using the data from this evidence collection together with the data collected during development, the team will answer key research questions that center on the use of the system safety case as an alternative means for airworthiness certification.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Barron Associates anticipates a number of opportunities to apply this SBIR-developed technology to NASA programs. With NASA's ongoing efforts for the development of the NextGen airspace, and their continued progress in both manned and unmanned space exploration, there is renewed emphasis on increased levels of safety, reliability, and affordability for these new and emerging systems and concepts. To address hardware component failures and faults, control and flight operational systems for advanced platforms will need to be intelligent, adaptable, reconfigurable, and often nondeterministic in their behavior in order to provide the required levels of safety and reliability. Current certification approaches have served well in the past but may not scale adequately for envisioned future systems. Our proposed empirical study of the system safety case as an alternative means for certification will lay the groundwork for its acceptance as a viable path to certification. Additionally, Barron Associates' proposed demonstration of a modular collision-avoidance system based on ADS-B presents an opportunity to use NextGen emerging technology to develop a collision-avoidance system that is accurate, safe, and future-proof. As surveillance technologies advance, cost-effective upgrades to the collision-avoidance system will be possible, allowing those advances to improve the performance of the overall system, enabling further separation reductions without additional nuisance warnings.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Barron Associates envisions significant near- and far-term uses for the proposed use of the system safety case for certification. The Food and Drug Administration, for example, requires the delivery of an assurance argument --- a synonym for the safety case --- with any new direct-injection drug pumps. The increase in the amound of software present in unmanned systems make traditional certification approaches both challenging and expensive; the results of the empirical study will inform future decision making regarding how certification should be pursued. Beyond air vehicles, other classes of unmanned systems, including ground and underwater vehicles will also benefit from the technology. Finally, the nuclear industry depends upon software for the control of its power plants and propulsion systems. Techniques like the system safety case, which directly argue software safety, may bring benefit as compared to prescriptive approaches, which only claim software quality. The proposed new, modular collision-avoidance system also has applications beyond those envisioned for NASA. In addition to its applications for civil air transport, the modularity of the system make it suitable for Department of Defense use in sense-and-avoid applications: ADS-B could be replaced by an active surveillance capability, such as one that relied on an on-board radar.

TECHNOLOGY TAXONOMY MAPPING
Pilot Support Systems


PROPOSAL NUMBER: 09-2 A2.01-8248
PHASE-1 CONTRACT NUMBER: NNX10CC67P
SUBTOPIC TITLE: Materials and Structures for Future Aircraft
PROPOSAL TITLE: Shape Memory Alloy-Based Periodic Cellular Structures

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Transition45 Technologies, Inc.
1963 North Main Street
Orange, CA 92865-4101
(714) 283-2118

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Edward Chen
transition45@sbcglobal.net
1963 North Main Street
Orange,  CA 92865-4101
(714) 283-2118

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR Phase II effort will continue to develop and demonstrate an innovative shape memory alloy (SMA) periodic cellular structural technology. Periodic cellular structures (PCS) will be designed and tailored to determine if additional shape memory performance benefits can be derived from the underlying macro-structure when fabricated from SMA's. These structures will be manufactured using an advanced reactive metal casting technology that will allow complex-shaped, integral bulk structures to be fabricated with the requisite composition-microstructure-properties needed for shape memory performance. Casting also offers a relatively low-cost approach for fabricating near net-shape components. The fabricated SMA structures will be characterized for resulting microstructure-properties in order to determine how to best design such PCS to better exploit SMA's for use in aerospace applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA commercial applications include aeroengine and airframe structural components, particularly those that could benefit from shape memory behavior, light weight, acoustic dampening, and impact resistance. For example, SMA's are being considered for flexible (morphing) wings and wing tips for aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA commercial applications include structures and components for armor, automotive and land vehicle (e.g., spoilers), shipboard structures, sporting goods, biomedical implants, and building structures. A practically limitless list of potential applications could essentially be put together if large-sized SMA material with the requisite shape memory properties can be manufactured affordably.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Erectable
Kinematic-Deployable
Launch and Flight Vehicle
Modular Interconnects
Structural Modeling and Tools
Waste Processing and Reclamation
Fluid Storage and Handling
Metallics
Multifunctional/Smart Materials
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.01-8833
PHASE-1 CONTRACT NUMBER: NNX10CC69P
SUBTOPIC TITLE: Materials and Structures for Future Aircraft
PROPOSAL TITLE: Interfacial Design of Composite Ablative Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Cooling Technologies, Inc.
1046 New Holland Avenue
Lancaster, PA 17601-5688
(717) 295-6061

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tapan Desai
tapan.desai@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5688
(717) 295-6061

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research (SBIR) project proposes the development of a computational software package to provide NASA with advanced materials development capabilities for existing and new ablative materials used in the next generation thermal protection systems (TPS) of space vehicles. This materials development software package (MDSAM) can be used to optimize properties (high strength and low thermal conductivity) for both the virgin material as well as the char that forms during the operating conditions. It will provide atomistic-level information on char evolution and the degradation of thermo-mechanical properties. The proposed MDSAM will consist of the following two modules: (i) an experimentally validated, atomistic-level simulation engine capable of predicting the role of interfacial structure on the resin-to-carbon process and (ii) atomistically-informed continuum-level thermo-mechanical performance analyzer for composite ablative materials subjected to transient pyrolytic conditions. The underlying methodology and the software package will be transitioned to NASA scientists working on ablative materials development. In addition to developing a computational software package, we will address open, unsolved problems in the literature to support NASA's ablative materials development requirements. In the course of developing this methodology, we will produce significant scientific results on pyrolysis and materials properties that will be important to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Ablative material development requires fundamental understanding of the molecular processes involved during the pyrolysis reaction and char evolution under transient conditions to accurately predict the effective insulation properties. The proposed software package is primarily focused towards providing this fundamental understanding to assist NASA with advanced materials development capabilities for the ablative materials to be used in the next generation space vehicles. The composite ablative material system studied in this project is derived from phenolic resins and fillers such as carbon fibers, in which NASA has strong interests. However, the software package will have the ability to study a wide range of existing ablative materials and design novel ablative materials. Furthermore, the developed methodology can be applied towards studying reaction mechanisms in high temperature combustion processes. These methodologies can probe reactions at high temperature and high pressure environments that are not easily accessible to experiments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Light weight materials such as reinforced plastics are rapidly replacing the traditional structural materials such as metals, woods etc. However, in many instances, these materials are flammable and they require modifications to decrease their flammability through addition of flame-retardant components. Environment regulations have restricted the use of halogenated flame-retardant additives, initiating a search for alternative flame-retardant additives. Carbon nanotubes have shown that they can simultaneously improve both the physical and flammability properties of the polymer nanocomposite. Our multiscale software package will explain the underlying physical mechanisms and accurately predict the thermo-mechanical behavior of the protective char layer. Thus it will directly help in development of the next generation commercial fireproofing materials. In addition, this software package technology can be applied to study high temperature oxidation and pyrolysis processes in materials that are of interest to the chemical, petrochemical, aerospace and defense industries, thus providing ACT a wide customer base.

TECHNOLOGY TAXONOMY MAPPING
Ablatives
Thermal Insulating Materials
Composites


PROPOSAL NUMBER: 09-2 A2.01-9131
PHASE-1 CONTRACT NUMBER: NNX10CC70P
SUBTOPIC TITLE: Materials and Structures for Future Aircraft
PROPOSAL TITLE: SiC Matrix Composites for High Temperature Hypersonic Vehicle Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Hyper-Therm High-Temperature Composites
18411 Gothard Street, Units B&C
Huntington Beach, CA 92648-1208
(714) 375-4085

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Shinavski
robert.shinavski@htcomposites.com
18411 Gothard Street, Units B&C
Huntington Beach,  CA 92648-1208
(714) 375-4085

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Durable high temperature materials are required for reusable hypersonic structural thermal protection systems. In particular, temperatures exceeding 2700F, and approaching 3000F, are targeted for capable structural materials that can survive stresses on the order of 10 ksi (70 MPa) for at least 100 hours in an oxidizing environment. Such materials have been identified as an enabling material for future hypersonic vehicles As this application is structural, a strong degree of damage tolerance is desired, and thus ceramic matrix composites are the primary choice due to the desire for reduced weight, high temperature strength and oxidation resistance. Silicon carbide fiber-reinforced silicon carbide matrix (SiC/SiC) composites are believed to be the most suitable solution due to meeting the requirements with the limitations of creep at the highest temperatures/loads, and oxidative attack at stresses that exceed the materials proportional limit. The proposed effort will define the temperature-stress limit of SiC/SiC composites, and examine methods to further extend this limit.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The development of advanced ceramic composite materials and components with enhanced thermal-structural performance over those currently available directly supports future enabling technologies for hypersonic thermal protection systems that are durable and reusable. Applications for SiC/SiC composites in advanced airbreathing combined-cycle propulsion systems and control surfaces for reusable hypervelocity and exo/transatmospheric aerospace vehicles are directly addressed by this technology. These potential applications are critically dependent on the development of advanced materials capable of high-performance load-bearing operation up to and beyond 1500<SUP>o</SUP>C (2700<SUP>o</SUP>F). Successful demonstration of the life at temperature of the CMC concept could result in a valuable near term increase in airframe performance and reliability for a variety of hot structures and thermal protection systems critical to both DoD and NASA high-speed aircraft and re-entry vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other viable near-term applications for SiC/SiC composites with enhanced temperature capability include expendable chemical rocket thrusters for orbital insertion, attitude control system and/or divert thrust chamber components for commercial and military communication spacecraft and/or various ballistic missile defense KE intercept weapons. Opportunities for application in turbine engine augmentors (e.g., converging/diverging exhaust nozzle flaps and seals) and internal turbine engine components for military and civilian aero-propulsion systems also exist.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Reuseable
Thermal Insulating Materials
Ceramics
Composites
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.01-9471
PHASE-1 CONTRACT NUMBER: NNX10CC71P
SUBTOPIC TITLE: Materials and Structures for Future Aircraft
PROPOSAL TITLE: Lightweight, Efficient Power Converters for Advanced Turboelectric Aircraft Propulsion Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MTECH Laboratories, LLC
P.O. Box 227
Ballston Spa, NY 12020-0227
(518) 885-6436

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Hennessy
mjhennessy@mtechlabs.com
831 Rte. 67, Bldg. 45C
Ballston Spa,  NY 12020-0227
(518) 885-6436

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA is investigating advanced turboelectric aircraft propulsion systems that utilize superconducting motors to drive a number of distributed turbofans. Conventional electric motors are too large and heavy to be practical for this application, and so superconducting motors are required. In order to improve maneuverability of the aircraft, variable speed power converters would be required to throttle power to the turbofans. The low operating temperature and the need for lightweight components that place a minimum of additional heat load on the refrigeration system opens the possibility of incorporating extremely efficient cryogenic power conversion technology. This Phase II program will develop critical components required to meet NASA's size, weight, and performance goals.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Apart from turboelectric aircraft propulsion systems and high-power drives for superconducting motors, other NASA applications include high-power and high-power-density cryogenic and wide-temperature-range power conversion systems for interplanetary and interstellar spacecraft, satellites, landers, and surface base stations on a number of planets or moons in the solar system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial applications include industrial utility projects to develop superconducting power transmission, superconducting wind turbine generators, and distribution systems for large buildings such as data centers and manufacturing plants based on superconducting cables. MTECH is currently working toward a demonstration site of such a distribution system, which could utilize the components developed in this NASA program. Other non-NASA federal government applications include a cryogenic motor drive system for the Navy's All-Electric Ship program, and equipment for superconducting accelerators at DOE national accelerator labs.

TECHNOLOGY TAXONOMY MAPPING
Semi-Conductors/Solid State Device Materials
Superconductors and Magnetic
Power Management and Distribution


PROPOSAL NUMBER: 09-2 A2.01-9895
PHASE-1 CONTRACT NUMBER: NNX10CC72P
SUBTOPIC TITLE: Materials and Structures for Future Aircraft
PROPOSAL TITLE: SiC-SiC and C-SiC Honeycomb for Advanced Flight Structures

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ultracor
136 Wright Brothers Avenue
Livermore, CA 94551-9240
(925) 454-3010

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Stan Wright
stan@ultracorinc.com
136 Wright Brothers Avenue
Livermore,  CA 94551-9240
(925) 925-3010

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed project builds upon the work done in Phase I with the development of a C-SiC CMC honeycomb material that was successfully tested for mechanical properties at both ambient and high temperature. The further study expands to include the development of an SiC-SiC honeycomb using the proven infiltration process of the Phase I project. In the proposed project, an SiC prepreg will be engineered that can be formed into a honeycomb and then infiltrated with SiC to form a ceramic SiC-SiC honeycomb. The honeycomb will then be tested mechanically at ambient temperature and high temperature. This testing will include cycling the material to determine property falloff. C-SiC and SiC SiC will be compared in this study. The thermal characteristics, such as conductivity and emissivity, will also be tested. The integration of such a material into hypersonic and other structures is a key area of the research; therefore a bonding study is included in the current proposal. Several bonding technologies and processes will be investigated and tested mechanically as well as cycled to determine durability. The goal of the study is to provide a sandwich level technology that can be integrated into hypersonic vehicle structures and acreage.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary commercial application for such materials is in hypersonic flight vehicles. A durable, lightweight material that can be integrated into acreage and structures is a key enabler of designing and building a multi-cycle hypersonic vehicle. These materials could also be considered for integration into a variety of other thermal protection systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The material could be useful in any application where the weight of SiC is an issue. For example, mirror structures made from SiC could be significantly lightweighted using SiC-SiC honeycomb.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Reuseable
Thermal Insulating Materials
Ceramics
Composites


PROPOSAL NUMBER: 09-2 A2.02-8867
PHASE-1 CONTRACT NUMBER: NNX10CC74P
SUBTOPIC TITLE: Combustion for Aerospace Vehicles
PROPOSAL TITLE: A Compact Safe Cold-Start (CS2) System for Scramjets using Dilute Triethylaluminum Fuel Mixtures

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ACENT Laboratories, LLC
3 Scott Lane
Manorville, NY 11949-2623
(631) 801-2616

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Gallimore
scott.gallimore@acentlabs.com
11917 Ricketts Battery Dr
Hampton,  VA 20136-2815
(571) 248-0134

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal leverages a highly successful Phase 1 feasibility effort to further develop a system that satisfies the cold-start requirements of scramjet engines. The system provides energy-dense, low volume hydrocarbon fuel conditioning based on the hydrolysis reaction of triethylaluminum (TEA) with water. TEA is an organometallic liquid that reacts exothermically with water and burns readily in air. In Phase 1, we demonstrated the hydrolysis of TEA in JP fuel within an integrated mixing/injection apparatus to heat and vaporize the liquid hydrocarbon fuel prior to injection in a regeneratively cooled scramjet, as well as auto-ignition of the mixture at elevated TEA concentrations. In Phase 2 we propose to more completely characterize the performance capability of the Phase 1 system using several hydrocarbon fuels to gather data for the design and fabrication of a palletized system. Testing of the palletized system in a direct connect scramjet rig will then be conducted to demonstrate engine ignition capability and to compare the system to other ignition systems under consideration for scramjet vehicles. Packaging in candidate flight vehicles will be carried out using 3D solid modeling to provide gravimetric and volumetric information and to provide designs for practical integrated, safe storage and dispense arrangements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A TEA based scramjet cold start system is expected to have significant mass and volume savings compared to traditional scramjet cold start techniques such as silane and ethylene when compared on an equivalence ratio basis. These mass and volume savings translate directly into additional capability and can alleviate some of the system packaging requirements of future hypersonic vehicle systems. In addition, the potential low Mach capability of a TEA based system helps extend the utility of scramjet engines proposed for turbine-based combined cycle hypersonic vehicles to lower Mach numbers, providing flexibility in selecting high-speed turbines capable of generating the required Mach number for scramjet takeover. NASA is interested in these types of vehicles as potential solutions for cheaper, reusable, more effective access to space.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The key advantage of a TEA based system over currently used single-function engine start techniques is that it provides multi-faceted benefits such as intense energy release, readily ignitable ethane gas, atomization of the fuel through effervescence, and pyrophoricity for ignition. As such, it likely has utility to assist in the high altitude re-light of turbojets with minimal modifications. If developed for such an approach, the TEA based system would be capable of providing engine start functionality for both the turbojet and scramjet in a turbine-based combined-cycle vehicle, significantly reducing overall system complexity. Companies such as Pratt & Whitney Rocketdyne that develop both turbojets and scramjets would find such a capable and simplifying system to be of great benefit in meeting the system requirements of a combined-cycle hypersonic vehicle. The DoD is interested in developing these types of vehicles to gain a hypersonic strike capability to stay ahead of competing foreign entities.

TECHNOLOGY TAXONOMY MAPPING
High Energy Propellants (Recombinant Energy & Metallic Hydrogen)
Propellant Storage
Feed System Components
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.02-9291
PHASE-1 CONTRACT NUMBER: NNX10CC76P
SUBTOPIC TITLE: Combustion for Aerospace Vehicles
PROPOSAL TITLE: Novel Active Combustion Control Concept for High-Frequency Modulation of Atomized Fuel Flow

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Jansen's Aircraft Systems Controls, Inc.
2303 W. Alameda Drive
Tempe, AZ 85282-3102
(602) 438-4400

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Matt Caspermeyer
matt.caspermeyer@jasc-controls.com
2303 W Alameda Dr.
Tempe,  AZ 85282-3102
(602) 889-3711

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal by Jansen's Aircraft Systems Controls, Inc. presents an innovative solution for Active Combustion Control. Relative to the state of the art, this concept has the ability to provide frequency modulation (greater than 1000[Hz]) in combination with high amplitude modulation (in excess of 30% flow) and can be adapted to a large range of fuel injector sizes. Existing state-of-the-art valves tend to have low flow modulation strength or the size of the valves with higher flow modulation seem too large or consume too much electrical power to be practical. The proposed Active Combustion Control valve has high frequency and amplitude modulation, consumes low electrical power, is closely coupled with the fuel injector for modulation strength, and is practical in size and weight.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has been involved in evaluating the need for such technology and continues to pursue it through SBIR-sponsored and other programs. As a result there are numerous applications that can benefit from this technology, including but not limited to,engines for prime propulsion, auxiliary power, and power generation where higher performance and lower exhaust emissions are desired.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Large frame power generating gas turbine manufacturers such as Honeywell, United Technologies, Rolls-Royce, General Electric, and Siemens are in need of this technology for their low-emission combustion systems and the market for such a proven device is world-wide. NASA's technology taxonomy has been developed by the SBIR-STTR program to disseminate awareness of proposed and awarded R/R&D in the agency. It is a listing of over 100 technologies, sorted into broad categories, of interest to NASA.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power


PROPOSAL NUMBER: 09-2 A2.02-9410
PHASE-1 CONTRACT NUMBER: NNX10CC77P
SUBTOPIC TITLE: Combustion for Aerospace Vehicles
PROPOSAL TITLE: Ultra High Temperature Capacitive Pressure Sensor

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sporian Microsystems, Inc.
515 Courtney Way, Suite B
Lafayette, CO 80026-8821
(303) 516-9075

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kevin Harsh
harshk@sporian.com
515 Courtney Way, Suite B
Lafayette,  CO 80026-8821
(303) 516-9075

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To improve the working performance, increase efficiency, reduce cost, and track system health status and failure modes of advanced propulsion systems; miniaturized, robust sensing systems for measuring and monitoring physical parameters, such as pressure, would be highly advantageous. Technical challenges for developing reliable sensing systems lie in extremely harsh working conditions the micro sensors must operate. In addition to high temperatures and pressures, these conditions include oxidation, corrosion, thermal shock, fatigue, fouling, and abrasive wear. High temperature (300-1350oC) capacitive pressure sensors are of particular interest due to their inherent suitability for wireless readout schemes. The objective of this proposed work is to develop a capacitive pressure sensor based on SiCN, a new class of high temperature ceramic materials, which possess excellent mechanical and electric properties at high temperatures (up to1600 C). The Phase II effort will include: the development of materials formulations and fabrication processes to realize optimized devices, device prototyping, and laboratory scale/relevant environment testing such as to achieve TRL 5-6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed sensor could be directly applicable to a planetary exploration mission to Venus. A high temperature sensor that does not require cooling will significantly reduce payload weight, volume and complexity. The sensor has the potential to support integrated vehicle health management for several types of onboard systems. Propulsion systems including launch and station keeping both exhibit high temperatures and could potentially benefit. For example, turbo pump assemblies and thrust chamber assemblies in liquid rocket motors could benefit from health monitoring via the proposed sensor. Energy generation systems such as fuel cells and nuclear reactors also have high operational temperatures that could be monitored by the proposed sensor. Derivative sensor technology could potentially be applied for sensing conditions in thermal protection systems and ceramic matrix composites.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aero propulsion turbine engines, communally used in commercial and military jets, would benefit significantly by having a non invasive, small mass, on engine component sensor allowing for visibility of the conditions of the turbine engine. The technology and sensor product described in this proposal would allow exactly that, while existing sensors fall well short of the application's demand. The conditions in this application are harsh, and sensors must be able to withstand high temperatures, high pressures, high flow rates, jet fuel and exhaust. In order for existing and future aero propulsion turbine engines to improve safety, reduce cost and emissions while controlling engine instabilities, more accurate and complete information is necessary. The technology described in this proposal would allow the next boundary in sensing technology to be achieved: direct measurement from the point of interest within the turbine. Commercial applications abound for the successful results of this proposal in commercial and military turbine engine industries, which are made up of companies such as Pratt & Whitney and Rolls-Royce. Additional potential market areas include: marine propulsion, rail locomotives, land based power generation turbines, automotive, oil and gas refining, and government and academic laboratories.

TECHNOLOGY TAXONOMY MAPPING
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Control Instrumentation
Sensor Webs/Distributed Sensors
Ceramics
Composites
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.03-9603
PHASE-1 CONTRACT NUMBER: NNX10CE74P
SUBTOPIC TITLE: Aero-Acoustics
PROPOSAL TITLE: Adaptive Drainage Slots for Acoustic Noise Attenuation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
2750 Indian Ripple Road
Dayton, OH 45440-3638
(937) 320-1877

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Hermiller
hermillerjm@crgrp.com
2750 Indian Ripple Road
Dayton,  OH 45440-3638
(937) 320-1877

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cornerstone Research Group, Inc. (CRG) demonstrated feasibility in the reduction of noise attributed to drainage slots in jet engine acoustic liners. This was accomplished through the development of design rules for optimum slot design and concept development of the implementation of adaptive material technologies to control slot dimensions. CRG brought this technology to a technology readiness level (TRL) 2 after the Phase 1 effort and will bring a TRL 4 after the Phase 2 effort. The Phase 1 effort provided simulated data for the acoustic designer to start to understand and develop preliminary models on the effects of drainage slots to the liner's acoustic impedance characteristics. This data has provided justification to pursue adaptive solutions that will counteract the adverse effects of drainage slots through adaptive means. In Phase 2, CRG will refine the design, scale up fabrication, demonstrate a full-scale operationally relevant aircraft part, and analyze manufacturing costs as part of a comprehensive Technology Insertion Plan.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Supporting NASA's mission, this project's technologies directly address requirements for improvements in noise reduction, prediction, measurement methods and control for subsonic and supersonic vehicle systems including fan, jet, turbomachinery, and airframe noise sources. This project's technologies offer system level improvements in noise, emissions, and performance.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
As locations in direct proximity to airports, both civilian and military, become more densely populated, noise pollution has become more of a concern for aircraft operators. Acoustic noise attenuation technologies apply directly to both government and commercial market segments, and more specifically to DoD and civil, commercial aviation applications that use gas turbine engines. Subsets of the technology also have direct application in maritime power-plants and stationary power generation equipment that use similar turbine engine configurations.

TECHNOLOGY TAXONOMY MAPPING
Composites
Multifunctional/Smart Materials
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.04-8558
PHASE-1 CONTRACT NUMBER: NNX10CE75P
SUBTOPIC TITLE: Aeroelasticity
PROPOSAL TITLE: State-of-the-art, Multi-Fidelity Modeling and Simulation (M&S) Tool for Nonlinear Aeroelasticity

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Dynamics, Inc.
1500 Bull Lea Road, Suite 203
Lexington, KY 40511-1628
(859) 699-0441

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Patrick Hu
patrick.g.hu@gmail.com
1500 Bull Lea Road, Suite 203
Lexington,  KY 40511-1628
(859) 859-0441

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Research is proposed for the development of a state-of-the-art computational aeroelastic tool. This tool will include various levels of fidelity and the ability to perform computational uncertainty quantification for data-driven risk analysis and certification. A number of novel reduced-order in time methods will be implemented into the code allowing for efficient and accurate aeroelastic simulation which will enable both the exploration of complex physics, point design and fast generation of "training data" for reduced order spatial aeroelastic models. The various levels of fidelity available in the code for aeroelastic modeling will range from CFD-based (both grid-based and a novel particle-based method) simulation to reduced-order aeroelastic models based upon Volterra series representations and Proper Orthogonal Decomposition (POD). The application of the proposed innovations spans the range of flight, from high-speed transport vehicles, to small-scale, flapping Micro-Air vehicles. Anticipated results include 1) the further validation and implementation of the proposed novel time-reduced order models into the existing ASTE-P solver framework (which already includes the various level fidelity mentioned above), 2) application of the proposed work to large-scale simulation and comparison with experiment, and 3) advancement of the state of knowledge for nonlinear problems in aeroelasticity in both the subsonic, low Reynolds number regime and transonic high Reynolds number regime.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are a number of applications for the resulting software and technologies to various NASA Centers, ARMD, Subsonic Rotary Wing, Subsonic Fixed Wing, Supersonics, and Hypersonics Projects, and potentially CLV projects may find use. Fundamental Aeronautics Program, Exploration Program both would have applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Based on our contacts with the US non-NASA government agencies such as US Air Force, Navy, Army, DARPA, etc., and aerospace companies such as Boeing, Bae Systems, Lockheed Martin, and Northrop Grumman, etc., we are aware of their needs for advanced aeroelastic/aero-structural modeling and simulation software for the design and analysis of the next generation aircraft. The general capability of resulting software can be routinely applied to generate aero-structural database and assess stability for aircraft and UAV/MAV under flutter/buffet/LCO. Several possibilities exist for transition including direct engagement with contractors supporting DoD acquisition programs, performing research in support of government air vehicle technology development programs, or using resulting program documentation to construct or tailor an application to provide demonstrated analytical and design capability for commercial airplanes.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Structural Modeling and Tools
Guidance, Navigation, and Control
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A2.04-9806
PHASE-1 CONTRACT NUMBER: NNX10CE76P
SUBTOPIC TITLE: Aeroelasticity
PROPOSAL TITLE: On-Line Flutter Prediction Tool for Wind Tunnel Flutter Testing using Parameter Varying Estimation Methodology

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ZONA Technology, Inc.
9489 E. Ironwood Square Drive
Scottsdale, AZ 85258-4578
(480) 945-9988

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jie Zeng
jzeng@zonatech.com
9489 E. Ironwood Square Drive
Scottsdale,  AZ 85258-4578
(480) 945-9988

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA Technology, Inc. (ZONA) proposes to develop an on-line flutter prediction tool using the parameter varying estimation (PVE) methodology, called the PVE Toolbox, to ensure the flight safety during the flight flutter test and to prevent the damage to the wind tunnel hardware from the structural failure of the flutter model during wind tunnel flutter test. This tool can be applied to rapidly identify parameters, such as modal damping and frequency from test data measured at pre-flutter flight/wind tunnel conditions, then subsequently to assess the flutter boundary of aircraft/wind tunnel model in real time. In this PVE Toolbox, several system identification techniques are employed to consistently estimate the damping/frequency of the physical modes, followed by the implementation of Zimmerman-Weissenburger flutter margin, damping trends extrapolation, linear parameter varying modeling combined with mu-analysis, and thin plate interpolation method for flutter boundary prediction. Seamlessly integration of the PVE Toolbox into IADS (a real-time flight test data acquisition software system) will significantly improve the on-line flutter prediction capability of the PVE Toolbox. This robust, production-ready, and flight test demonstrated PVE Toolbox will provide flight/wind tunnel test engineers an on-line flutter prediction capability in the control room for decision-making during flight/wind tunnel flutter tests.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Comprehensive flutter prediction software is still non-existing; leading to cautious and expensive flight/wind tunnel flutter test programs. ZONA envisions that the proposed Phase II research effort will result in a commercial product, called the PVE Toolbox. The PVE Toolbox will be a crucial technology for the flight flutter test of the next generation aircraft such as the NASA Hybrid Wind Body Configuration and Quiet Supersonic Transport.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential non-NASA customers for this tool include the R & D arms of USAF, Navy, Army, and the defense industry complex. It can be readily adapted by a wide class of aerospace vehicles ranging from current to next-generation designs such as: (a) USAF's F-22 and F-35 aircrafts at Edwards AFB, (b) UASF's Hilda and/or sensorcraft aircrafts, (c) USAF's next generation stealth and morphing UAV/UCAV, (d) DARPA's new Switchblade Flying Wing Program, and for (e) Micro Air Vehicle (MAV) with enhanced control/maneuver capability.

TECHNOLOGY TAXONOMY MAPPING
Structural Modeling and Tools
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A2.05-9058
PHASE-1 CONTRACT NUMBER: NNX10CE78P
SUBTOPIC TITLE: Aerodynamics
PROPOSAL TITLE: Simulation Tool for Dielectric Barrier Discharge Plasma Actuators at Atmospheric and Sub-Atmospheric Pressures

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tech-X Corporation
5621 Arapahoe Avenue, Suite A
Boulder, CO 80303-1379
(303) 448-0727

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alexander Likhanskii
likhansk@txcorp.com
5621 Arapahoe Ave
Boulder,  CO 80303-1379
(303) 996-7520

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Traditional approaches for active flow separation control using dielectric barrier discharge (DBD) plasma actuators are limited to relatively low-speed flows and atmospheric conditions. It results in low feasibility of the DBDs for aerospace applications, such as active flow control at turbine blades, fixed wings, rotary wings and hypersonic vehicles, which require a satisfactory performance of the DBD plasma actuators at wide range of conditions, including rarified flows and combustion mixtures. An optimization of the DBD plasma actuators should be achieved using efficient, comprehensive, physically-based DBD simulation tool for different operation conditions. We propose to develop a DBD plasma actuator simulation tool for a wide range of ambient gas pressures. The proposed tool will treat DBD using either kinetic, fluid or hybrid model, depending on the DBD operational condition. The proposed tool will be validated by comparison with the experimental and numerical data on the DBD investigations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA applications of the proposed DBD simulation tool are active flow control concepts for both subsonic and hypersonic flights. Predictable active flow separation control, achieved using the proposed tool, will benefit many NASA Projects, such as Subsonic Fixed Wing Project, Subsonic Rotary Wing Project and Hypersonic Project. In addition to the flow separation application, DBD simulation tool can be used for a number of NASA problems, associated with gas discharges at different pressures. For example, DBD simulation tool can be used for the description plasma-assisted combustion for the reduction of carbon emissions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Active flow control using DBD plasma actuators is of interest to a number of government agencies, private industry and universities. Proposed tool will be beneficial for subsonic/hypersonic programs which involve active flow separation control. These programs include, but are not limited to, flow separation control at commercial airplanes during take-off or landing, increase in lift for tiltrotor aircrafts, improvement of engine performance, active flow control at hypersonic vehicles. Besides the primary application for a description of DBD operation, DBD simulation tool can be used for a wide range of plasma aerodynamics applications, such as plasma-assisted combustion, flow control using different types of discharges, reduction of carbon emission, optimization of air vehicle operation, MHD and EHD application as well as in plasma-processing and plasma medicine applications.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Operations Concepts and Requirements


PROPOSAL NUMBER: 09-2 A2.05-9389
PHASE-1 CONTRACT NUMBER: NNX10CE79P
SUBTOPIC TITLE: Aerodynamics
PROPOSAL TITLE: Uncertainty Quantification for Production Navier-Stokes Solvers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Combustion Research and Flow Technology
6210 Keller's Church Road
Pipersville, PA 18947-1020
(215) 766-1520

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Peter Cavallo
cavall@craft-tech.com
6210 Keller's Church Road
Pipersville,  PA 18947-2010
(215) 215-1520

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The uncertainty quantification methods developed under this program are designed for use with current state-of-the-art flow solvers developed by and in use at NASA. The Phase I program demonstrated the CRISP CFD<SUP>REG</SUP> error quantification and reduction code with simulations conducted using the NASA unstructured solvers FUN3D and USM3D. Phase I provided evidence supporting the suspected need for an error prediction code that matches the finite volume scheme of the Navier-Stokes solver itself. Phase II will continue this work by expanding our Error Transport Equation (ETE) solver to treat both classes of unstructured grid finite volume schemes. Support for the CGNS standard will be implemented and permit use of the Phase II product by a broader spectrum of potential users. Specific issues that affect numerical accuracy of the error predictions and how they propagate into integrated quantities such as lift and drag coefficients will be addressed. Reduction of error for large scale meshes is a matter of equal importance, and improvements are planned that will provide for anisotropic grid refinement within the existing CRISP CFD<SUP>REG</SUP> mesh adaptation code. Finally, error quantification approaches for transient applications will be explored to expand these developments to problems that involve inherent unsteadiness and/or moving boundaries.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research is directly relevant to the application of CFD analysis to aircraft and re-entry vehicles of current and future interest to NASA. CFD simulations are playing an increasing role in air vehicle analysis and design assessment, and numerical predictions often supplement the databases obtained in ground and flight tests. The proposed research will impact the use of CFD analysis tools by NASA personnel in verifying the accuracy of force and moment predictions, surface pressures, heat flux distributions, etc., providing not only numerical error bars and certifiable confidence levels in simulated results, but also quantifiable reduction of error through automated mesh modification. As the research effort addresses fundamental issues in numerical simulation accuracy, numerous applications of interest to NASA exist. Potential applications of the proposed error quantification and reduction research include simulation of launch vehicles, planetary re-entry capsules, attitude control jets, liquid fuel feed systems, rocket nozzle performance, etc.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA-developed Navier-Stokes solvers are heavily used by a number of private companies and organizations within the aerospace and defense industries. Engineers at these corporations and government laboratories rely on the accuracy of NASA CFD tools in the development of small business jets, commercial airliners, and next generation fighter aircraft. Error quantification is a necessity widely recognized by this community, and providing adequate grid resolution is a perennial challenge. To date, research in error quantification has largely been limited to academic research groups and government laboratories, and no commercially available package for error quantification and reduction currently exists. This offers a unique opportunity to assume the leading role as the first player in the market for such software. Outside of the aerospace and defense sectors, the proposed error quantification research finds ready application in the areas of biofluid flows, automobile engines, power generation and turbomachinery, chemical processing, etc.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Cooling
Feed System Components
Expert Systems
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.06-8042
PHASE-1 CONTRACT NUMBER: NNX10CE82P
SUBTOPIC TITLE: Aerothermodynamics
PROPOSAL TITLE: Fiber-Coupled Spectrometer for TPS Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ElectroDynamic Applications, Inc.
P.O. Box 131460
Ann Arbor, MI 48113-1460
(734) 786-1434

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dean Massey
massey@edapplications.com
3600 Green Court Suite 300
Ann Arbor,  MI 48105-1570
(734) 786-1434

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
EDA, Inc., in partnership with Penn State, has shown previously that the concept of embedding fiber optics within ablative TPS material has merit and should yield a successful implementation of a spectrometer "window" during a Phase-II development program. Optical instrumentation, such as optical spectrometers would provide benchmark data for fundamental flow, radiation, and materials modeling as well as provide operational correlations between vehicle reentry drag and radiation if implemented in a TPS flight test program. Without flight spectral data, and the appropriate modeling efforts, the power of prediction to assist in new heat shield design does not exist for reentry into other planetary atmospheres. This is a severe limitation for future space exploration missions which FiberPlug helps address.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This program will see important applications in upcoming NASA missions involving re-entry spacecraft. EDA, in collaboration with Penn State, intends the development of a flight system for NASA TPS technology development programs and demonstration missions. The system can also be used in ground testing facilities such as the AHF at NASA Ames to explore the local plasma environment (density and temperature) surrounding articles under test

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Hypersonic vehicles using thermal protection systems (TPSs) are an active area of interest to the department of defense and aerospace contractors developing commercial space vehicles. There are weapon systems presently under development which would benefit from the FiberPlug technology, both at the demonstration level where verification of TPS performance will be critical, and for operational vehicles where the mission can be adapted real time in response to performance data provided by FiberPlug. EDA anticipates working with the Air Force to develop FiberPlug solutions for this area as well. EDA will also pursue terrestrial applications. High energy plasmas are used in a variety of industrial processes, as well as for energy generation technology. Improved characterization capabilities that can survive extreme environments will find a market in these fields as well.

TECHNOLOGY TAXONOMY MAPPING
Launch Assist (Electromagnetic, Hot Gas and Pneumatic)
Ablatives
Launch and Flight Vehicle
Simulation Modeling Environment
Thermal Insulating Materials
Optical
Ceramics
Composites
Optical & Photonic Materials
Aerobrake


PROPOSAL NUMBER: 09-2 A2.07-9816
PHASE-1 CONTRACT NUMBER: NNX10CC07P
SUBTOPIC TITLE: Flight and Propulsion Control and Dynamics
PROPOSAL TITLE: Flight Dynamic Simulation with Nonlinear Aeroelastic Interaction using the ROM-ROM Procedure

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ZONA Technology, Inc.
9489 E. Ironwood Square Drive
Scottsdale, AZ 85258-4578
(480) 945-9988

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ping Chih Chen
pc@zonatech.com
9489 E. Ironwood Square Drive
Scottsdale,  AZ 85258-4578
(480) 945-9988

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 6
End: 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA Technology, Inc. proposes to develop an integrated flight dynamics simulation capability with nonlinear aeroelastic interactions by combining a flight dynamics model and an add-on nonlinear aeroelastic solver in a Simulink environment. This nonlinear aeroelastic solver is generated by interacting a nonlinear structural Reduced Order Model (ROM) with a Neural-Network-based (NN-based) aerodynamic ROM and a gust ROM to provide the incremental aeroelastic forces and moments of a classical flight dynamics model. In this way, the flight dynamics model is kept with minimum changes so that this integrated flight dynamics simulation remains in the frame work of a 6-degrees-of-freedom simulation environment. The nonlinear structural ROM employs an ELSTEP/FAT procedure that operates on a commercial nonlinear finite element software to construct the nonlinear stiffness matrices. The NN-based and gust aerodynamic ROM is generated using a system identification technique operating on a CFD code to evaluate the weights and biases in a two-layer feed-forward NN system. The end product is called FuNL-DFS that can simulate the key aeroelastic coupling mechanism between nonlinear structural dynamics and nonlinear unsteady aerodynamics with classical rigid body dynamics and can be used for control law development, maneuvering flight simulation, flight loads prediction and handling quality assessment. The FuNL-DFS system will be validated with the flight test data of the Predator B Aircraft.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has been working for many years towards achieving a software package that accurately predicts the interaction between flight dynamics and nonlinear aeroelastic effects in closed-loop flight dynamic simulation. NASA's current and next generation aircraft design concepts such as the N+1 Conventional, N+2 Hybrid Wing Body, and N+3 Generation are more flexible, more slender and/or more sizable where there may be insufficient frequency separation between the rigid body dynamics and the relatively low frequency elastic modes. The flight control law based on the rigid model may result in an unacceptable stability or an undesirable response characteristic due to control input or turbulence. The FuNL-DFS system can provide an expedient multidisciplinary nonlinear flight simulation tool to perform an efficient flaw debugging for advanced control laws as well as to promote physical understanding of these revolutionary designs in a cost-effective manner; while increasing performance and confidence in the control law designs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ZONA's business plan for FuNL-DFS will follow ZONA's flagship software, called: ZAERO, product/service sales strategy. The added capabilities developed in FuNL-DFS will strengthen ZONA's market position in the aerospace industry. FuNL-DFS will be marketed towards flight test applications on a wide class of aerospace vehicles such as: (a) USAF's F-22 and F-35 aircrafts at Edwards AFB, (b) UASF's Hilda, sensorcraft as well as stealth and morphing UAV/UCAV, (c) DARPA's Morphing Aerostructure, (d) Boeing 787 and future executive jet designs of Cessna, Raytheon, etc. The proposed FuNL-DFS can also be applied to validate health management strategies specifically designed for aircraft designs with prominent aeroelastic characteristics.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Structural Modeling and Tools
Guidance, Navigation, and Control
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A2.08-8224
PHASE-1 CONTRACT NUMBER: NNX10CC78P
SUBTOPIC TITLE: Aircraft Systems Analysis, Design and Optimization
PROPOSAL TITLE: Design Environment for Multi-Fidelity and Multi-Disciplinary Components

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mechanical Solutions, Inc.
11 Apollo Drive
Whippany, NJ 07981-1423
(973) 326-9920

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Platt
mjp@mechsol.com
11 Apollo Drive
Whippany,  NJ 07981-1423
(973) 973-9920

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Many of the most challenging categories of propulsion system development are related to the prediction of interacting effects between the fluid loads, thermal loads, and the structural deflection. In practice, the interactions between technical disciplines are often not fully explored analytically, and the analysis in one discipline often uses a simplified representation of other disciplines as an input or boundary condition. For example, the fluid forces in an engine generate static and dynamic rotor deflection, but the forces themselves are dependent on the rotor position and its orbit. This practice ignores the interaction between the physical phenomena where the outcome of each analysis can be heavily dependent on the inputs (i.e., changes in flow due to deflection, changes in deflection due to fluid forces). Such a rigid design process also lacks the flexibility to employ multiple levels of fidelity in the analysis of each of the components. The goals for this project are to develop and validate an innovative design environment that has the flexibility to simultaneously analyze multiple disciplines, multiple components, with multiple levels of model fidelity. Development and demonstration of such a system will provide substantially superior capabilities to current design tools.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
By providing an integrated framework for turbomachinery analysis, the work in this project will reduce the time and complexity of the multiphysics analyses (job setup, solution control, pre- and post-processing). This work directly addresses NASA design environment goals as engineering teams will have the capability to employ multi-fidelity physics-based tools to reduce the failure rate and development cost of propulsion systems. The numeric zoom functions in NPSS will be enhanced with fluid-structure interaction capability. Similarly, the high-fidelity analysis will be leveraged by the system/cycle functions in NPSS.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The accomplishment of all Phase I objectives will demonstrate the significant benefits of the combined multi-fidelity / multi-disciplinary design environment. This capability would be immediately useful for the design and development of civilian and military gas turbine engines and chemical propulsion turbomachinery. Such an analytical capability will also assist the wider turbomachinery community with avoidance of advanced designs, leading to a successful commercialization of the new tool.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Aircraft Engines


PROPOSAL NUMBER: 09-2 A2.08-8824
PHASE-1 CONTRACT NUMBER: NNX10RA72P
SUBTOPIC TITLE: Aircraft Systems Analysis, Design and Optimization
PROPOSAL TITLE: Discrete Geometry Toolkit for Shape Optimization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimal, LLC
181 Summertree Road
Starkville, MS 39759-9761
(662) 325-2286

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Greg Burgreen
burgreen@o-ptimal.com
181 Summertree Road
Starkville,  MS 39759-9761
(662) 662-2286

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Simulation-based design optimization has been steadily maturing over the past two decades, but not without its own unique and persistent challenges. The proposed project will develop a novel solution to one of the long-standing bottlenecks in simulation-based design optimization. Particularly, we will develop a flexible geometry toolkit for shape parameterization and modification as required for design optimization. With our discrete geometry toolkit, shape modifications will be achieved via an elegant and intuitive "plug-and-play" approach, providing engineers with a wide variety of options for shape parameterization, shape deformation, and geometric constraint imposition. Our geometry toolkit will be composed of independent modules and will be easily integrated into existing or future analysis and design environments. Our approach will offer a modular and intuitive means to interactively synthesize appropriate modifications to discrete geometry shapes in a design optimization setting including the specification of geometric constraints and interdisciplinary data transfer.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Several design-oriented projects and design environments are being developed at the various NASA Research Centers, including the NPSS, CoHAVE, ADVISE, FUN3D, TetrUSS, and CART3D design environments. A common requirement of each of these design environments is the need for shape parameterization and modification. Our proposed geometry toolkit approach enables a very flexible and elegant means to construct, refine, and explore combinations of techniques that produce different final geometry shapes. Our project will make available componentized geometry-related technologies that address critical areas needs to enable next-generation design optimization. NASA can immediately benefit from our design-oriented components in its design efforts as well as in analysis-only environments in which rapid shape modifications are desired.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Design environments incorporating knowledge based engineering are increasingly being developed. Examples include the AVEC environment developed by the Air Force based on the commercially available Adaptive Modeling Language (AML) product as well as the commercial design frameworks of ModelCenter (Phoenix Integration) and MDICE (CFDRC). Our proposed componentized geometry toolkit will readily integrate within such environments, giving immediate relief to the needs that have crippled progress in design optimization for the past two decades. The potential markets for our software are very broad. Our software can be used for fluid dynamic applications in the aerodynamic, automotive, biomedical, turbomachinery, and hydroelectric fields as well as for structural and electromagnetic applications. Each of these markets can immensely benefit from automated design optimization, provided that flexible geometry manipulation is no longer an impediment.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Software Development Environments


PROPOSAL NUMBER: 09-2 A2.09-8823
PHASE-1 CONTRACT NUMBER: NNX10CC10P
SUBTOPIC TITLE: Rotorcraft
PROPOSAL TITLE: Flight Adaptive Blade for Optimum Rotor Response (FABFORR)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing, NJ 08618-2302
(609) 538-0444

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert McKillip, Jr.
bob@continuum-dynamics.com
34 Lexington Avenue
Ewing,  NJ 08618-2302
(609) 609-0444

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
While past research has demonstrated the utility and benefits to be gained with the application of advanced rotor system control concepts, none have been implemented to date on a production military or commercial rotorcraft. A key contributor to this fact is the inherent cost associated with installation and maintenance of these control systems, since many system designs require the replacement of a helicopter's rotor blades, rotor hub components, or both. The proposed work addresses this deficiency through the development of an on-blade full-span camber control system that reaps many of the known benefits of advanced rotor control in a retrofit design approach that has the potential to achieve production status due to its lower risks and costs compared to previous system concepts. The design leverages past work in the use of smart-material actuated bistable tabs for rotor blade tracking, with a newer integral actuation concept that will lead toward a more robust and flightworthy design.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
An adaptive ability to alter the spanwise loading of rotor blades could be used to optimize rotorcraft aeromechanics and identify improved operational profiles, maximizing the utility and cost-effectiveness of future helicopters incorporating this technology. Full development of this novel adaptive blade capability would support key aeromechanics aspects of the Subsonic Rotary Wing Project of the Fundamental Aeronautics Program, in particular active on-blade control for performance improvement and noise and vibration alleviation. Follow-on work would also enhance current analysis methods, which are presently unable to capture complex active-rotor response and thus are a barrier to selection of optimal active control approaches.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Retrofit blade controls of the type explored here can both enhance the performance and reduce the acoustic emissions and blade-induced vibrations of suitably equipped rotorcraft over baseline vehicles. Since this capability could be achieved using technology that does not require the re-blading of an existing helicopter, a significant commercial product improvement program for a variety of aircraft would be possible. Military operators would also realize improved mission capability and reduced aircraft downtime with these anticipated improvements. However, this actuation technology can also serve as a starting point for development of an evolved active control system that integrates the trailing edge active control devices into the blade structure, offering an alternative implementation path with potential advantages in robustness and reduced drag penalty.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Guidance, Navigation, and Control
Pilot Support Systems
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 A2.09-9940
PHASE-1 CONTRACT NUMBER: NNX10CC13P
SUBTOPIC TITLE: Rotorcraft
PROPOSAL TITLE: Embedded Data Acquisition Tools for Rotorcraft Diagnostic Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ridgetop Group, Inc.
6595 North Oracle Road
Tucson, AZ 85704-5645
(520) 742-3300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Justin Judkins
justin.judkins@ridgetopgroup.com
6595 North Oracle Road
Tucson,  AZ 85704-5645
(520) 742-3300

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ridgetop's innovation addresses the need for improved capabilities for detecting wear in the drive gears inside helicopter gearboxes. Rotorcraft drive trains must withstand enormous pressure while operating continuously in extreme temperature and vibration environments. Captive components, such as planetary and spiral bevel gears, see enormous strain but are not accessible to fixed instrumentation such as a piezoelectric transducer. Thus, it is difficult to directly monitor components that are most susceptible to damage. Ridgetop has developed an embedded data acquisition module that overcomes these limitations. This innovation is a self-contained data processing unit within a specialized fixture that installs directly inside the hubs of rotating gear parts. From this location, it and detects and transmits high fidelity prognostic data to a fixed transceiver. The sensor is based on MEMS technology and uses innovative circuit designs to capture high bandwidth data and transmit it wirelessly from inside an operational helicopter transmission. In Phase 2, Ridgetop will build the module and acquisition system, and demonstrate it at the NASA Glenn Rotorcraft transmission testbed. We will provide evidence that the innovation gives superior fidelity by making side-by-side comparisons with current fixed-sensor setup. Ridgetop will tie in data collection with prognostics and advanced diagnostic approaches, make enhancements, and show an improvement in failure detection horizon times. We will also develop a data interface between the wireless sensor port and a standard HUMS communication bus. Finally, Ridgetop will develop a commercialization path by demonstrating the technology to airframe manufacturers.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Improved vibration sensors will support the Subsonic Rotary Wing thrust of the NASA Fundamental Aeronautics Program, as well as NASA's IVHM goals for future aircraft, satellites, and similar systems. The proposed technology will significantly help monitor and diagnose harmful vibration effects inherent to flight operation. With strong existing relationships with several NASA sites and a reputation for excellent service and products among the NASA community, Ridgetop anticipates collaboration with NASA SRW testbeds at Glenn Research Center to help optimize the technology through Phase 2 and into actual implementation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial rotorcraft have been known to suffer significantly from structural and electronic stress as a result of the vibration levels caused by routine flight. The proposed innovation, which will be able to collect and process critical diagnostic data, will be highly advantageous for manufacturers and operators. For manufacturers, the tool will be very useful during field testing as a measurement utility for vibration and accumulated stress. For commercial operators such as Bell Helicopter and Sikorsky, the proposed innovation will be instrumental in the real-time efficient analysis of diagnostic routines critical to safe flights.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Testing Requirements and Architectures
On-Board Computing and Data Management
Data Acquisition and End-to-End-Management
Portable Data Acquisition or Analysis Tools
Tribology


PROPOSAL NUMBER: 09-2 A2.10-9062
PHASE-1 CONTRACT NUMBER: NNX10CC82P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Design Concepts for Cooled Ceramic Matrix Composite Turbine Vanes

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
N&R Engineering
6659 Pearl Road, #201
Parma Heights, OH 44130-3821
(440) 845-7020

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Boyle
rbrjboyle760@gmail.com
6659 Pearl Road, #201
Parma Heights,  OH 44130-3821
(440) 845-7020

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The work proposed herein is to demonstrate that the higher temperature capabilities of Ceramic Matrix Composites (CMC) can be fully utilized to reduce emissions and improve fuel consumption in gas turbine engines. The work involves closely coupling aerothermal and structural analyses for the first stage vane of a high pressure turbine (HPT). These vanes are actively cooled, typically using film cooling. Ceramic materials have different structural and thermal properties than conventional metals used for the first stage HPT vane. Vane configurations which satisfy CMC structural strength and life constraints, while maintaining vane aerodynamic efficiency and increasing mainstream gas temperature for improved engine performance will be identified. The proposed work will examine modifications to vane internal and external configurations to achieve the desired objectives. Thermal and pressure stresses are equally important, and both will be analyzed. Three dimensional fluid and heat transfer analyses will be used to determine vane aerodynamic performance and heat load distributions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work advances the goals of the NASA Aeronautics program. The proposed work furthers the adoption of materials which can be used to increase turbine inlet temperatures. This is beneficial for a wide rang of gas turbine engine applications. The primary benefit of increased turbine inlet temperature is in the reduction of SFC. Reducing fuel consumption reduces CO2 emissions, and for every pound of fuel saved nearly three pounds of CO2 are not produced in the combustion process. Using the higher temperature capabilities of CMC materials to reduce vane cooling can be used to reduce combustor outlet temperature without decreasing rotor inlet temperature. Just slightly reducing the combustor outlet temperature significantly reduces NOx. Since the rotor inlet temperature is not reduced, there is no negative impact on fuel consumption. The higher temperature capability of CMC materials has a beneficial impact on gas turbine engines for a wide range of applications. Small gas turbines, for rotary wing applications, have relatively high SFC, and are likely to experience the greatest reduction in SFC for a given increase in gas temperature. Commercial transport aircraft consume large amounts of fuel. Even a slight improvement in SFC for these aircraft saves significant amounts of fuel and emissions. Supersonic aircraft have very high fuel-to-payload ratios. For these aircraft a small reduction in fuel burn gives a large payload improvement.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Improvements in SFC for commercial transport aircraft through the application of CMC components would be used by the complete range of gas turbine engines used in military applications. Using CMC components in ground power gas turbines can significantly reduce CO2 emissions. Current combined cycles and future clean coal cycles use gas turbine components, and operate as base load plants. Their continuous operation at maximum power consumes very large quantities of fuel. Even a small improvement in fuel rate, (kg/kW), significantly reduces emissions. Any reduction in the fuel consumption yields substantial cost savings. The combined cycle gas turbine overall pressure ratio is only about half that of an aircraft gas turbine. Consequently, pressure loads are lower. Hence, ground power gas turbines might adopt CMC components in the near future. Recuperated turbines, such as those marketed by Solar Turbines Inc., have high cycle efficiencies, but low overall pressure ratios(less than 20). However, they require a large heat exchanger, which causes the capital cost to be greater than the cost of a simple cycle gas turbine for ground power applications. The efficiency of recuperated turbines improves markedly with a rise in gas temperatures. N&R Engineering intends to provide design and analysis services for the evaluation of CMC components in gas turbine engines. In addition, N&R Engineering would provide these services to operators of these engines.

TECHNOLOGY TAXONOMY MAPPING
Structural Modeling and Tools
Ceramics
Composites
Aircraft Engines


PROPOSAL NUMBER: 09-2 A3.01-8137
PHASE-1 CONTRACT NUMBER: NNX10CC14P
SUBTOPIC TITLE: NextGen Airspace
PROPOSAL TITLE: Statistical Decision Support Tools for System-Oriented Runway Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimal Synthesis, Inc.
95 First Street, Suite 240
Los Altos, CA 94022-2777
(650) 559-8585

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
P. K. Menon
menon@optisyn.com
95 First Street, Suite 240
Los Altos,  CA 94022-2777
(650) 650-8585

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The feasibility of developing a statistical decision support system for traffic flow management in the terminal area and runway load balancing was demonstrated in the Phase I research. The methodology employed an advanced estimation algorithm based on a queuing network model of the runway and the terminal area, and statistical decision theory to formulate traffic flow decisions. Radar data from the San Francisco terminal area was used in the feasibility demonstration. Component technologies developed in Phase I work can be used for synthesizing real-time statistical decision support tools for runway configuration management and arrival/departure scheduling. Phase II work will use the Phase I algorithms for developing decision support tools for NASA's System-Oriented Runway Management program elements. Queuing networks of runways, taxiways, gates, and terminal airspace will form the foundation of the decision support tool. Predicted demand, historic traffic data and real-time measurements will be combined in an estimator to generate the statistical distributions of the queuing network parameters. These will then be used in conjunction with methods from Statistical Decision Theory to generate actionable decisions. Phase II research will develop a software package implementing these algorithms, which can be evaluated in human-in-the-loop and operational settings during the Phase III work.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Statistical decision support tools for runway configuration management and arrival/departure scheduling developed under the Phase II work will be useful in NASA's SORM program. The methodology for developing queuing network based estimators are useful in several traffic flow management concepts being considered under the NextGen program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Queuing network models for describing traffic flow, queuing network parameter estimation methods, and statistical decision support tools developed under the Phase II research are useful in a wide variety of road and rail traffic flow control problems. These methods also have several applications in logistics, production planning and control, and in other problems in Operations research.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Airport Infrastructure and Safety
Autonomous Reasoning/Artificial Intelligence
Human-Computer Interfaces
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A3.01-8419
PHASE-1 CONTRACT NUMBER: NNX10CC15P
SUBTOPIC TITLE: NextGen Airspace
PROPOSAL TITLE: Estimation and Prediction of Unmanned Aerial Vehicle Trajectories

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Numerica Corporation
4850 Hahns Peak Drive, Suite 200
Loveland, CO 80538-6010
(970) 461-2000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shawn Herman
shawn.herman@numerica.us
4850 Hahns Peak Drive, Suite 200
Loveland,  CO 80538-6003
(970) 461-2000

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
There is serious concern about the introduction of Unmanned Aerial Vehicles (UAV) in the National Air Space (NAS) because of their potential to increase the risk of collision between aircraft. At present, many UAV platforms lack a Sense and Avoid (SAA) capability to mitigate collision risk, and this has prevented both the government and private contractors from using these platforms in critically needed reconnaissance, surveillance, and security enforcement missions. To demonstrate a SAA capability that is applicable to a wide range of UAV platforms, advanced trajectory estimation and prediction algorithms are developed and used to exploit a small collision avoidance radar currently under development for UAV operation. Collision prediction algorithms will assess potential risk in probabilistic terms using adaptive techniques that permit accurate predictions across long time horizons. Techniques to ensure these predictions are robust to modeling uncertainty increase the utility the developed SAA capability for realistic scenarios.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed could form the basis of systems designed to predict and prevent loss of separation between unmanned aerial vehicles and other aircraft. As NASA and the FAA continue development of the NextGen Airspace program through 2025, the need to safely integrate UAV's into the NAS will only grow. One possible application would be integrating the technology into a NASA simulation environment such as the Future ATM Concept Evaluation Tool (FACET). Discussions with NASA Ames Research Center have also indicated potential interest in the trajectory prediction innovations that could be applicable for tactical collision avoidance tools.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial Vendors Colorado Engineering Inc. is developing the USTAR collision avoidance radar for use in the Global Hawk and other UAV platforms. Expanded SAA capability is achievable when the developed algorithms are used to exploit the USTAR. Ultra Electronics-Advanced Tactical Systems offers the Advanced Fusion and Tracking System (AFTS). The US Army's Tactical Airspace Integration System (TAIS) already uses Ultra's AFTS product for airspace management. Numerica's technology could be a plug-in for AFTS trajectory estimation and prediction modules, as well as Ultra's TacView user interface to automatically alert operators to potential airspace conflicts. US Military UAV Given the interest in developing UAV platforms, there is significant need to develop a sense and avoid for Navy UAV platforms. One development activity is the MQ-8B Fire Scout Vertical Take-Off and Landing Tactical Unmanned Aerial Vehicle (VTUAV). Another ongoing Navy development program is for the Broad Area Maritime Surveillance (BAMS) platform.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Control and Monitoring


PROPOSAL NUMBER: 09-2 A3.01-8549
PHASE-1 CONTRACT NUMBER: NNX10CC16P
SUBTOPIC TITLE: NextGen Airspace
PROPOSAL TITLE: Stochastic Queuing Model Analysis to Support Airspace Super Density Operations (ASDO)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimal Synthesis, Inc.
95 First Street, Suite 240
Los Altos, CA 94022-2777
(650) 559-8585

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Monish Tandale
monish@optisyn.com
95 First Street, Suite 240
Los Altos,  CA 94022-2777
(650) 559-8585

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has been involved in extensive research efforts to develop advanced concepts and technologies, for the Next Generation Air Transportation System (NextGen) under different Research Focus Areas (RFAs). The Airspace Super Density Operations (ASDO) RFA seeks to develop efficient terminal area operations. It is expected that multiple ASDO concepts will be interacting with one another in a complex non-deterministic manner. Therefore, the overall terminal system performance may not be a straightforward combination of individual performance indices. It is also crucial that the overall system performance be robust to wind and operational uncertainties. The proposed research effort seeks to develop a fast-time, stochastic analysis tool based on queuing theory that can be used to evaluate the interaction and combined performance of multiple ASDO concepts. The utility of the approach was demonstrated under Phase I research. Phase II research seeks to achieve the following: (i) make enhancements to the modeling and simulation aspects of the approach, (ii) accelerate the stochastic simulation execution time using high-performance computing solutions, (iii) create software plug-ins for existing NASA research tools, (iv) conduct studies of NextGen terminal area concepts using the queuing simulation, and (v) develop a conflict free scheduling algorithm based on the queuing simulation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application of the queuing model developed in the course of this research is to serve as a stochastic analysis tool to evaluate proposed NextGen concepts in the terminal area. The proposed queuing model provides a transformation between the terminal area routes, procedures and runway configurations, to the traffic flow efficiency. This model can be used in rapid prototyping tools that design terminal area routes and procedures, to evaluate the efficiency of the designed route. The queuing model and the associated simulation framework can be used to evaluate the performance of various sequencing, scheduling, pairing, and merging & spacing algorithms being developed under NASA's Airspace Super Density Operations (ASDO) program. During Phase II research a plug-in will be developed for the STASS software that is currently being used by the ASDO group. Interfaces will also be identified to other NASA software tools such as TRAC and CTAS.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed queuing model shows potential for the following non-NASA applications: 1. The Phase II research effort proposes to develop queuing model based sequencing, scheduling and merging & spacing algorithms. Such algorithms can be a part of a decision support automation used by air-traffic controllers in the terminal area and metroplexes. 2. The fast-time stochastic queuing simulation framework developed using high-performance computing framework can provide near real-time forecasts of the state of the terminal area taking into account wind and weather uncertainties. Such a forecast capability can be vital to Traffic Flow Management (TFM) decision-making algorithms under adverse weather conditions. 3. This model can be used by the Airline Operations Center (AOC) to make decisions on canceling, re-routing or re-scheduling flights in response to an adverse weather event.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Requirements and Architectures


PROPOSAL NUMBER: 09-2 A3.01-8820
PHASE-1 CONTRACT NUMBER: NNX10CC17P
SUBTOPIC TITLE: NextGen Airspace
PROPOSAL TITLE: Market Mechanisms for Airspace Flow Program Slots

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron Aviation, Inc.
45300 Catalina Court, Suite 101
Dulles, VA 20166-2335
(703) 456-0123

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Brennan
Michael.Brennan@metronaviation.com
45300 Catalina Court, Suite 101
Dulles,  VA 20166-2335
(703) 234-0743

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron Aviation, Inc. proposes to design a system to support a marketplace in which flight operators can exchange arrival slots in traffic flow management (TFM) initiatives such as airspace flow programs (AFPs) and ground delay programs (GDPs) while requiring no changes in FAA automation or procedures. The advent of AFPs in 2006 has generated many more potentially exchangeable resources that would be valued sufficiently differently by their owners to make a trade desirable. We believe that NAS users and the FAA would embrace such a marketplace and that it would enable users to collectively reduce their operating costs resulting from NAS congestion. Both FAA and NASA research has highlighted the need for efficient and equitable allocation of NAS resources and increased operational flexibility. Market-based mechanisms have been suggested for transferring system-imposed delay from more critical to less critical flights. No such capability is available to NAS users today. In this SBIR, we will show how the advent of AFPs changes the forces at work in a slot-trading marketplace, making its functions much more valuable to flight operators.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed SBIR directly benefits NASA's Next Generation Air Transportation System (NextGen) Air Traffic Management Airspace Project, whose primary goal is to develop integrated solutions for a safe, efficient and high-capacity airspace system. Efficient airspace allocation requires early research in market-based mechanisms for design of the next-generation air transportation system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed marketplace has application in commercial ATM both in the U.S. and abroad. In the U.S. ATM market, any resource broker attempting to establish a slot market will require the tools and procedures output by Phases 2 and 3 of this SBIR to act as a central processor and tracker of ATM-induced flight controls. At the same time, U.S. air carriers will require tools with which to monitor and manage their flight schedules and make informed, effective decisions for exchanging resources. Estimates of costs due to delays range from hundreds of millions to billions of dollars per year. The opportunity to save even a fraction of these costs creates significant motivation for airline participation. It is reasonable to assume that the number of carriers willing to participate in this system will be comparable to the number signed up as active members of the collaborative decision making (CDM) program.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control


PROPOSAL NUMBER: 09-2 A3.01-8821
PHASE-1 CONTRACT NUMBER: NNX10CC18P
SUBTOPIC TITLE: NextGen Airspace
PROPOSAL TITLE: Unmanned Aerial Vehicle Integration into the NAS

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron Aviation, Inc.
45300 Catalina Court, Suite 101
Dulles, VA 20166-2335
(703) 456-0123

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Hoffman
Robert.Hoffman@metronaviation.com
45300 Catalina Court, Suite 101
Dulles,  VA 20166-2335
(703) 234-0760

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Technological innovations have enabled a wide range of aerial vehicles that can be remotely operated. Viable applications include military missions, law enforcement, border patrol, weather data collection, telecommunications, land use imaging, and cargo transport. NASA and other organizations have invested heavily in this unmanned aerial vehicle (UAV) research. UAVs can be flown in the National Airspace System (NAS) today, but only with special permission from the FAA ? a process that often takes 60 to 90 days. Moreover, permission is often contingent on heavy restrictions, such as accompanying the UAV with a manned chase plane, thereby nullifying the cost savings of a UAV. Full fruition of UAV technology will require incorporation of UAVs into mainstream air traffic management (ATM) practices, including traffic flow management flow control programs and possible creation of special use airspace (SUA). In this SBIR, we propose a UAV-to-traffic flow management (AIM-UAS) interface. This allows traffic managers to anticipate and track UAVs. In turn, this allows UAV operators to understand their impact on commercial air traffic and their involvement in traffic management activities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This SBIR benefits NASA in three ways. (1) It furthers one of the main goals of NASA's Strategic Airspace Usage project, the increase of capacity and the enhancement of throughput in the national airspace system via development of long-term operational concepts for collaborative traffic management. (2) This SBIR preserves the integrity and applicability of NASA research and development of UAV technology by helping to overcome a primary obstacle to integration of UAVs into today's national airspace system. In particular, this research will encourage policy makers to accept the viability of UAVs. (3) NASA decision support tools developed for ATM, such as CTAS, TMA, FAST, and SMS will benefit from recommendations for how to account for UAV traffic into their logic.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The FAA will benefit from this innovative research in several ways. (1) They will have a greater understanding of how they can grapple with changing traffic demand patterns and NAS user needs stemming from remote operation of vehicles. (2) The FAA will have access to a tool and operational paradigm for data exchange between UAV operators and FAA traffic managers. (3) The FAA will partially achieve one of the NextGen programmatic goals, equitable access to NAS resources for all NAS users. (4) This research will help the FAA set UAV operation policies by providing insight into and feasibility of UAV integration into the NAS. (5) Our proposed tool could be integrated with the FAA's special use airspace system (SAMS), due to strong relation between UAVs and special use airspace. Several other government agencies share responsibility for UAV integration, such as DOT, DoD, DHS, US Forest Service, and Coast Guard.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Pilot Support Systems


PROPOSAL NUMBER: 09-2 A3.02-8211
PHASE-1 CONTRACT NUMBER: NNX10CC21P
SUBTOPIC TITLE: NextGen Airportal
PROPOSAL TITLE: Integrated Testbed for Environmental Analysis of NextGen Concepts using ACES

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Intelligent Automation, Inc.
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2737
(301) 294-5221

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Frederick Wieland
fwieland@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville,  MD 20855-2737
(301) 294-5268

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation in this effort is the development of an industrial-grade analysis testbed to integrate simulation tools, such as ACES, with aviation environmental effects models, such as the Aviation Environmental Design Toolkit (AEDT), to provide a "360-degree" evaluation of new operational concepts. The testbed will be demonstrated by producing such a "360-degree" evaluation of advanced NextGen concepts such as time-based merging and spacing at ATL airport, high-density metroplex concepts, and the efficiency of new route structures with environmentally responsible aircraft using RNAV routing. The industrial-grade software will be implemented in Java and can potentially reduce the analysis time for combined performance/environmental analyses by several months over the current state of the art.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This tool enables NASA headquarters to make future research investment decisions about advanced aviation concepts using information about both their expected performance impact as well as their expected environmental impact. In addition, analysts at NASA centers that study advanced concepts (currently, Langley, Ames, and Glenn) can use this tool to fine-tune their ideas so that they meet performance and environmental objectives.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potentially the tool could be used by any airport, FAA analyst, or aviation consultant interested in performing a comprehensive analysis of new concepts under consideration. Thus all congested Metroplex areas (approximately fourteen in the United States), as well as large airlines and all large airports could benefit from using this tool for expansion planning.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Airport Infrastructure and Safety


PROPOSAL NUMBER: 09-2 A3.02-8812
PHASE-1 CONTRACT NUMBER: NNX10CE84P
SUBTOPIC TITLE: NextGen Airportal
PROPOSAL TITLE: Lidar Wind Profiler for the NextGen Airportal

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Masstech, Inc.
6992 Columbia Gateway Drive, Suite 200
Columbia, MD 21046-2985
(443) 539-1739

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Anand Radhakrishnan
anand@apmaldi.com
6992 Columbia Gateway Dr
Columbia,  MD 21046-2985
(443) 539-3102

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of a standoff sensor that can measure 3D components of wind velocity in the vicinity of an airport has the potential to improve airport throughput, safety and efficiency. The goal of this research is to develop a Lidar Wind Profiler (LWP) that uses multiple near-parallel lidar beams to track the motion of atmospheric aerosol structures and extract multi-component wind data. In Phase I, the measurement requirements were analyzed and used to develop a numerical model of the performance of a prototype system. In addition, an eye safety analysis was conducted and a conceptual design of the LWP prototype was developed. Studies were conducted with a breadboard in order to demonstrate improvements in spatial and temporal resolution of the system and to obtain more data to further refine the system requirement and algorithm. In Phase II, the LWP design will be finalized and a high power laser design will be combined with narrow pulse-width generation technology as well as an Optical Parametric Oscillator in order to generate a wavelength of 1550. The algorithm will be optimized and extended to measurements in all three dimensions using a multi-beam lidar system. Techniques to extract atmospheric turbulence and detect aircraft wake vortices will be developed. A software package will be developed that will include the following: a front-end GUI for displaying the data and for interfacing with the operator; a real-time data-processing module; a data acquisition module; a data storage and retrieval module. At the end of Phase II, the LWP prototype will be field tested and evaluated using validation data from ultrasonic anemometers.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A remote wind profiler for measuring winds, turbulence, cloud ceiling and aircraft wake vortex location and intensity can become an integral part of the multi-agency NextGen Aeroportal system, in order to increase throughput in airports and to detect aircraft external hazards. In addition, the ability to non-intrusively obtain 3-component concurrent winds can be used to study key NASA challenges in aerodynamics, acoustics and aero-flight dynamics as a part of ground test facilities such as wind tunnels, hover chambers and anechoic facilities. Other potential NASA applications include wind surveys for wind turbines and aerodynamic test facilities such as wind tunnels and ballistic correction equipment for launch vehicles. An airborne version of this instrument can potentially be used for sensing air speed and warning of external hazards such as turbulence and wake vortices.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA applications include small, inexpensive wind profiling systems for use at National Weather Service instrument stations, DoD ballistic correction cross-wind sensors of different sizes ranging from sniper rifles to heavy artillery, field surveys of wind profiles for wind turbines and atmospheric research. One example is the Marine Sniper School in Quantico, VA. Others are the PEO-Soldier and the Rapid Equip Force offices at Fort Belvoir, VA. We will propose a demonstration for them as soon as we have a working prototype system. The Army and Marine Sniper programs could use several thousand wind profilers if they can be made man-portable so they can be easily carried and used by 2-man sniper teams. Other commercial applications could include analyzing the effect of aircraft wakes on personnel and equipment at airports, offshore installations and building helipads, as well as measuring the flowfield in the vicinity of buildings and other structures.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Airport Infrastructure and Safety
Optical


PROPOSAL NUMBER: 09-2 A3.02-9691
PHASE-1 CONTRACT NUMBER: NNX10CC22P
SUBTOPIC TITLE: NextGen Airportal
PROPOSAL TITLE: ATC Operations Analysis via Automatic Recognition of Clearances

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mosaic ATM, Inc.
801 Sycolin Road, Suite 306
Leesburg, VA 20175-5686
(800) 405-8576

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Chris Brinton
brinton@mosaicatm.com
801 Sycolin Road, Suite 306
Leesburg,  VA 20175-5686
(800) 405-8576

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent advances in airport surface surveillance have motivated the creation of new tools for analysis of Air Traffic Control (ATC) operations, such as the Surface Operations Data Analysis and Adaptation (SODAA) tool, which is being used by NASA to conduct airport ATC operations analysis. What is missing from ATC operations analysis, however, is accessible and reliable data regarding the clearances issued by the controller and other communication conducted with the pilot that influences the behavior seen in the surveillance data. The reliance on voice communication in ATC operations presents challenges to the researcher who is trying to obtain data and conduct detailed analyses of ATC operations. During the Phase I effort, we designed and developed a prototype system to perform automatic speech recognition (ASR) of ATC clearances. We demonstrated the feasibility of recognizing ATC clearances from speech audio data and associating the clearance data with the flight that is the subject of the clearance. In the Phase II effort, we will create a complete prototype of the ATC speech recognition, processing and analysis capability in SODAA. In addition, we will integrate ATC speech recognition capabilities into a real-time application in the Surface Management System (SMS).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential applications for the research results beyond Phase II include use by NASA for continued research of ATC operations and by the FAA. These applications include both off-line analysis applications and real-time applications. NASA and other aviation community researchers can use this data to analyze ATC operations and to measure workload associated with ATC communication. Analysis of conformance to clearances can also be assessed and analyzed. In real-time application, NASA can use the speech recognition of ATC clearances to improve the performance of the Surface Management System at the NASA NTX facility.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The capability to perform automatic speech recognition of ATC clearances can provide commercial benefit to airlines in their efforts monitor airport operations and drive efficiencies into their operation. Mosaic ATM provides the surface management application that is being used operationally by UPS airline in Louisville, Kentucky. This speech recognition capability can be integrated into the UPS SMS system to improve data acquisition and prediction performance. Additionally, the automatic speech recognition capability of ATC clearances can be used in additional research and prototype capabilities for integration of Unmanned Aircraft Systems (UASs) into the National Airspace System (NAS). By using speech recognition and additional research, capabilities for UAS to autonomous react to ATC clearances may be possible.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Airport Infrastructure and Safety
Guidance, Navigation, and Control
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 A4.01-8214
PHASE-1 CONTRACT NUMBER: NNX10CE86P
SUBTOPIC TITLE: Ground Test Techniques and Measurement Technology
PROPOSAL TITLE: Blade Vibration Measurement System for Unducted Fans

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mechanical Solutions, Inc.
11 Apollo Drive
Whippany, NJ 07981-1423
(973) 326-9920

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Marscher
wdm@mechsol.com
11 Apollo Drive
Whippany,  NJ 07981-1423
(973) 973-9920

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With propulsion research programs focused on new levels of efficiency and noise, there are two emerging avenues for advanced gas turbine technology: the geared turbofan and ultra-high bypass ratio fan engines. Both of these candidates are being pursued as collaborative research projects between NASA and the engine OEMs. The high bypass concept from GE Aviation is an unducted fan which features a bypass ratio of over thirty, along with the accompanying benefits in fuel efficiency. The innovation being developed in this project is improvement is the test and measurement capabilities of the unducted fan blade dynamic response. In the course of this project, Mechanical Solutions, Inc. (MSI) will work with GE Aviation to define the requirements for fan blade measurements, to leverage MSI's radar-based system for compressor and turbine blade monitoring, and to develop, validate and deliver a non-contacting blade vibration measurement system for unducted fans.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The goals for this project are to design and construct an innovative and non-intrusive unducted fan blade dynamics measurement system with resolution capable of characterizing fan blade dynamic modes. Development and demonstration of such a system will provide substantially superior capabilities to current measurement technology. As the NASA / GE program moves ahead, the work in this project will deliver a unique non-contacting blade measurement system to improve the test and measurement technology in the NASA Glenn 9x5 and 8x6 wind tunnel facilities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology developed in this project will directly useful to the OEMs of turbofan and turboprop engines for military and commercial use. Beyond propulsion systems, there is great potential in blade health management systems for wind turbines and rotorcraft.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Testing Requirements and Architectures
Structural Modeling and Tools
RF
Microwave/Submillimeter
Aircraft Engines


PROPOSAL NUMBER: 09-2 A4.01-8257
PHASE-1 CONTRACT NUMBER: NNX10CE87P
SUBTOPIC TITLE: Ground Test Techniques and Measurement Technology
PROPOSAL TITLE: Piezoelectric MEMS Microphones for Ground Testing of Aeronautical Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Baker-Calling, Inc.
836 Brookside Drive
Ann Arbor, MI 48105-1100
(734) 645-0571

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Littrell
kgrosh@gmail.com
836 Brookside Drive
Ann Arbor,  MI 48105-1100
(734) 734-0571

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 6
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Improving the acoustical environment is critical in aeronautics. Airports and aeronautical systems manufacturers are facing ever-increasing demands to reduce noise levels. Aeronautical applications require the use of high quality microphones with a large dynamic range, sometimes in large arrays. These arrays are expensive. The advent of lower cost microphones that meet the users' specifications would dramatically improve the ability of engineers seeking to quantify the acoustic impact of either their designs or their facilities (e.g., airports) and to make data driven decisions to improve any adverse situation. In our Phase-I SBIR, we showed the technical feasibility of a commercially viable, piezoelectric micro-electro-mechanical systems (MEMS) microphones capable of withstanding adverse conditions found in ground testing of the acoustics of aeronautical systems. In the Phase II project, we will implement design changes to improve these sensors. We will develop efficient deep reactive ion etching (DRIE) procedures to increase our yield and lower costs. We will develop scalable packaging techniques so that the devices can be economically assembled into a completed device. Finally, the reliability and robustness of these microphones will be determined. Each of these tasks will advance us toward our goal of producing a commercially viable product with outstanding acoustical performance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are a great number of NASA test facilities where lower cost microphones are needed that can withstand harsh environmental conditions and acoustic loading. A partial listing includes: 1. Glenn Research Center: Acoustic Test Lab: phased array systems (e.g., 16 element linear array, 80 element microphone cage array, 63 element microphone spiral array); Nozzle Acoustic Test Rig; AeroAcoustic Propulsion Lab; Advanced Noise Control Fan Rig. 2. Langley Research Center: Structural Acoustics Loads and Transmission facility; Jet Noise Lab; Mobile Acoustics Research Capability; Anechoic Noise Facility. 3. Noise mapping at airports using large arrays. 4. Wallops Island Test Facility

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
More than 2 billion microphones are sold each year. A piezoelectric MEMS microphone can address the needs of the vast majority of this market but will need to be designed appropriately for each sector of the market. This market can be broken up into roughly three categories. About half of the market, 1 billion units per year, is for extremely inexpensive microphones for toys and other applications where size and performance are not crucial. Roughly 1 billion units per year are also sold for consumer electronics, mostly for mobile phone applications. There is also a small market of high-end microphones for instrumentation, recording studios and live events. Examples of large arrays of instrument quality microphones used in the aerospace industry include the wind tunnel measurements (where over 1000 microphone could be used) and in the ground test arrays (like the Boeing QTD2 array with over 600 microphones). We will first target the instrumentation microphone market.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Particle and Fields
Airport Infrastructure and Safety
Sensor Webs/Distributed Sensors
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 A4.01-8856
PHASE-1 CONTRACT NUMBER: NNX10CE88P
SUBTOPIC TITLE: Ground Test Techniques and Measurement Technology
PROPOSAL TITLE: A Novel, Portable, Projection, Focusing Schlieren System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MetroLaser, Inc.
8 Chrysler
Irvine, CA 92618-2008
(949) 553-0688

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Drew L'Esperance
dlesperance@metrolaserinc.com
8 Chrysler
Irvine,  CA 92618-2008
(949) 553-0688

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The schlieren technique has been used for flow diagnostics in wind tunnels since the beginning of aerospace research due to its ability to make airflows ? especially shock waves and turbulence ? visible. This proposal describes a novel type of schlieren system that would increase efficiency, capability, and productivity for ground test facilities. The concept and the availability of state-of-the-art components make the system more portable, easier to align, and more versatile than existing systems. A major drawback of current schlieren systems, and one that has restricted their widespread commercial use, is that they require exact alignment between a pair of widely separated mirrors or grids, which takes time and limits portability, and costs are prohibitive for most such applications. This problem is partially relaxed by focusing schlieren methods. The proposed concept incorporates features of existing schlieren systems while removing the primary limitations. All of the elements that require precise alignment are contained within a camera body and can be relatively inexpensive. Very large fields of view are made possible. This is advantageous in wind tunnel facilities, since experiments are frequently installed only to be torn down shortly afterwards.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Applications exist in all forms of research and development associated with flow fields where schlieren viewing could be useful, including aero-optics, flow control, drag, boundary layer transition, and flow separation. The proposed developments could be extremely important in enhancing ground test facility capability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential commercial applications include aero-optics, flow diagnostics, flow control, free-space laser communication, active laser imaging, high bandwidth video transmission, spectroscopy, and high-resolution imaging.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Optical


PROPOSAL NUMBER: 09-2 A4.02-9523
PHASE-1 CONTRACT NUMBER: NNX10CC59P
SUBTOPIC TITLE: Flight Test Techniques and Measurement Technology
PROPOSAL TITLE: Fiber Optic Pressure Sensor Array

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
VIP Sensors
32242 Paseo Adelanto, Suite C
San Juan Capistrano, CA 92675-3610
(949) 429-3558

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alexis Karolys
alex@vipsensors.com
32242 Paseo Adelanto, Suite C
San Juan Capistrano,  CA 92675-3610
(949) 949-3558

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
VIP Sensors proposes to develop a Fiber Optic Pressure Sensor Array System for measuring air flow pressure at multiple points on the skin of aircrafts for Flight Load Test applications. The array consists of multiple micro-miniature optical MEMS pressure sensors interconnected by a common optic fiber to an Interrogation Module located inside the airplane. The proposed optical pressure sensors are practically flat, light weight, fully passive (no electrical power), and EMI/RFI immune, they exhibit superior performance regarding accuracy, dynamic range and noise. They are inherently self identifiable; the interrogation system knows what data belongs to what sensor. The proposed sensor array technology is applicable to different types of optical sensors (accelerometers, strain, temperature, etc). Each sensor in the array is designed to work at preset optical wavelengths; they are read by the Interrogation Module using Wave Division and Time Division Multiplexing. Testing of aircrafts requires a large numbers of sensors. Each sensor needs four to six wires to interconnect to signal conditioners. For large measuring systems, this means very large numbers of wires that add weight and occupy space. The proposed FO sensor array system not only has the potential to significantly improve pressure measurements for Flight Load Testing, but its novel technology of micro-miniature networking sensors will benefit many other aircraft ground and flight testing applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Applications are in flight and ground/wind tunnel testing of aircrafts where surface pressure measurements are needed. The proposed system, for many applications, is a better alternative to the Electronic Scanner Pressure system, which are used across NASA wind tunnel facilities and flight test programs: 1. Subsonic Facilities: Low Speed Wind Tunnel at GRC, Subsonic Tunnel and Vertical Spin Tunnel at LaRC 2. Transonic Facilities: National Transonic Facility and Transonic Dynamics Tunnel at LaRC, Unitary Plan Facility at ARC 3. Supersonic Facilities: Supersonic Wind Tunnels at GRC and ARC, Unitary Plan Wind Tunnel (UPWT) at LaRC's 4. Flight Loads Laboratory (FLL) at Dryden Flight Research Center (DFRC). NASA fight & wind tunnel test scientists have shown a high degree of interest on the system as demonstrated by the participation of three Technology Infusion Application Advisers listed below: Organization Transition Program Mission Directive James Bell NASA/ARC Moffett Fundamental Aeronautics Aeronautics Research David Star Facility Manag. Planning Office Wind Tunnel Testing Aeronautics Research Allen R. Parker NASA Dryden SOFIA, Ikhana, 853 (one of Dryden's F-18), Global Hawk Aeronautics Research

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Fiber Optic Pressure Sensor Array System is applicable to many other fields where passive sensors of small size, high accuracy, and networking features are important. F/O Sensor Array technology developed in this program is directly applicable to other types of inertial sensors such as optical accelerometers, microphones, etc. Flight Testing ? Thousands of sensors to test and qualify aircraft; the networking feature drastically reduces cabling and testing costs. Wind Tunnel Testing ? Hundred of pressure and vibration measurement channels are used world wide Airplane and Satellite Monitoring ?Large number of sensors of different types are used for on-board monitoring. Naval Ship Monitoring ? Thousands of sensors are used on board military and commercial ships. Helicopter Condition Based Monitoring - Hundreds of sensors are used in Health Usage Monitoring Systems on board helicopters. Structural Testing ? Hundreds of sensors are used to test the modal behavior of airplanes, satellites, missiles and other structures.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Testing Requirements and Architectures
Optical
Sensor Webs/Distributed Sensors



PROPOSAL NUMBER: 09-2 X1.01-8239
PHASE-1 CONTRACT NUMBER: NNX10CC37P
SUBTOPIC TITLE: Automation for Vehicle Habitat Operations
PROPOSAL TITLE: Automation of Health Management, Troubleshooting and Recovery in Lunar Outpost

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Qualtech Systems, Inc.
99 East River Drive
East Hartford, CT 06108-3288
(860) 257-8014

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Marta Olenick
marta@teamqsi.com
99 East River Drive
East Hartford,  CT 06108-3288
(860) 761-9362

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall Phase-II goal is to develop the technologies and tools that can aid the automation of operation by providing intelligent decision support in situations when a mission plan needs alteration due to an event(s). The effort targets not only developing the algorithms, but also to implement them on QSI's TEAMS platform; this will transition the technologies into a useful tool for the A4O community.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
QSI is well positioned with its TEAMS products with NASA MSFC and ARC where those NASA centers have extensively utilized the TEAMS Designer product for functional failure analysis of the Ares vehicle and for onboard fault diagnostics for Orion. QSI had been working with Honeywell, Lockheed Martin and NASA JSC in that capacity as a technology provider. The proposed capability significantly enhances TEAMS Designer and runtime modules' suitability for deployment on board as well as on the ground for NASA's vehicles for mission information exchange and planning between the command module, mission control and ground operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to NASA, several other large military systems where automated real-time condition assessment, mission assessment and successful mission planning is critical for operations such as other Space Command ground segments, Ground Vehicles, the Navy shipboard platforms, the Joint Strike Fighter (JSF) fleet, and ballistic missile defense systems, as well as commercial industries such as semiconductor fabrication, industrial automation transportation, power generation and distribution, are potential applications.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Architectures and Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Expert Systems
Human-Computer Interfaces
Highly-Reconfigurable


PROPOSAL NUMBER: 09-2 X1.01-8474
PHASE-1 CONTRACT NUMBER: NNX10CC38P
SUBTOPIC TITLE: Automation for Vehicle Habitat Operations
PROPOSAL TITLE: Executable SysML Model Development Accelerator for the Constellation Program

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tietronix Software, Inc.
1331 Gemini Avenue, Suite 300
Houston, TX 77058-2794
(281) 461-9300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michel Izygon
mizygon@tietronix.com
1331 Gemini Ave., Suite 300
Houston,  TX 77058-2794
(281) 404-7256

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed project is aimed at investigating ways to accelerate the creation of SysML based models that can be used for model checking and more generally for Model-Based System Engineering. In the past few years, multiple projects in the ISHM domain as well as the operations domain (Procedure V&V) have started to leverage the power of model checking through the use of the Finite State Machines (FSM) formalism. These models have been typically developed manually by subject matters experts in the different spacecraft systems and subsystems. This is a significant hindrance to the widespread use of models for any targeted application. The envisioned suite of tools would allow non experts to derive the appropriate SysML models for their intended use. In addition to providing a generic library of space systems models, methods to customize these models to the specific target system, our proposal will also design tools that enable the automatic or semi automatic extraction of appropriate information from different source, thus significantly accelerating the development and the usage of such models.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A toolset for accelerated development of executable models of spacecraft systems has multiple applications in the NASA community, the DoD environment, as well as in the commercial arena. The envisioned toolset can be applied to any complex system that needs to use model-based techniques for design or validation. Desktop based tool support for such system is currently missing. In the short term, the tool can be used for NASA projects such as the Orion, the Small Pressurized Rover, and Lunar Habitat test bed . The tool should allow these projects to significantly reduce the need for prototyping activities and associated costly simulation. In the longer term, the tool can be directly applicable to all components of the Constellation program and any software intensive system supporting the new exploration vision.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The toolset for executable models development that can be customized to different systems will be useful within DoD organizations in which software intensive product lines are common. For example, the Unmanned Aerial Vehicles (UAV) Domain is enjoying a period of significant expansion. UAVs have progressed from target drones to reusable weapon systems. Their software systems have become complex and extremely diversified. Domain specific executable SysML models could reduce development risks by enabling many alternative operational concepts and designs to be evaluated before significant effort is expended developing poor designs. In the commercial arena, adopting the same type of approach for software intensive system can be used in a broad range of areas, such as airplane, power plant SCADA systems, and vertical business applications such as Human Resources applications. This type of technology can be adapted to these different domains and provide benefits similar to those provided to NASA.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Training Concepts and Architectures
Computer System Architectures


PROPOSAL NUMBER: 09-2 X1.01-8666
PHASE-1 CONTRACT NUMBER: NNX10CC39P
SUBTOPIC TITLE: Automation for Vehicle Habitat Operations
PROPOSAL TITLE: PM/IDE - An Integrated Development Environment for Planning Models

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Stottler Henke Associates, Inc.
951 Mariner's Island Blvd., Suite 360
San Mateo, CA 94404-1585
(650) 931-2726

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Ong
ong@stottlerhenke.com
951 Mariner's Island Blvd., Suite 360
San Mateo,  CA 94404-1585
(650) 931-2700

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a planning model integrated development environment (PM/IDE) that will help people construct, review, understand, test, and debug high-quality planning domain models expressed in the Action Notation Modeling Language (ANML) more quickly and effectively. PM/IDE will enable novice modelers to review and understand models more expediently, so they can learn modeling techniques more efficiently. PM/IDE also will enable experienced modelers to review the models of others more quickly, so they can share modeling techniques and best practices. Interactive graphical displays will enable modelers to describe planning domain models under construction and the plans they can generate to domain experts in order to facilitate more efficient knowledge elicitation and model review. Without PM/IDE, ANML modeling will remain a tedious and difficult task that can be carried out only by the small number of people who have the necessary specialized skills and patience. This, in turn, will severely limit the use of ANML-based automated planning systems. During Phase I, we characterized the planning domain modeling task to identify the types of analyses and decisions that modelers carry out and the kinds of information they review and assess. Based on this understanding of the task, we designed and prototyped PM/IDE capabilities and user-system interactions that help people develop ANML models. During Phase 2, we propose to develop a TRL 7 version of PM/IDE. Our design approach draws upon our experience using a top-down, decision-centered software requirements and design process to develop data visualization and decision support systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research effort will result in an operational IDE that NASA personnel can use to develop high-quality, large-scale ANML models more quickly and easily. After Phase II, Stottler Henke will market the IDE to NASA contractors and will enhance the IDE to support additional NASA and NASA contractor requirements. The technology developed during the project will also enable Stottler Henke to develop planning domain models for other modeling languages used by NASA, its partner space agencies, and its contractors. The technology will also enhance the domain modeling capabilities of Stottler Henke's Aurora<SUP>TM</SUP> intelligent scheduling tool suite, which is used by NASA, NASA contractors, and major aerospace manufacturers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting technology will also serve as an important new part of Stottler Henke's intelligent sensing and control solution offerings to the Department of Defense that support military operations, simulation, and training. For example, automated planning could be used to support more intelligent computer-generated forces used within training and wargaming exercises. It can also be used to control next-generation unmanned vehicles and intelligent software agents. The technology will also enhance the domain modeling capabilities of Stottler Henke's Aurora<SUP>TM</SUP> intelligent scheduling tool suite, which is used by NASA, NASA contractors, and major aerospace manufacturers

TECHNOLOGY TAXONOMY MAPPING
Autonomous Reasoning/Artificial Intelligence
Human-Computer Interfaces
Software Development Environments


PROPOSAL NUMBER: 09-2 X1.01-9674
PHASE-1 CONTRACT NUMBER: NNX10CC40P
SUBTOPIC TITLE: Automation for Vehicle Habitat Operations
PROPOSAL TITLE: Robotic Vehicle Proxy Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Energid Technologies
One Mifflin Place, Suite 400
Cambridge, MA 02138-4946
(888) 547-4100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James English
jde@energid.com
One Mifflin Place, Suite 400
Cambridge,  MA 02138-4946
(617) 401-7090

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Energid Technologies proposes the development of a digital simulation to replace robotic vehicles in field studies. It will model the dynamics, terrain interaction, sensors, control, communications, and interfaces of a robotic vehicle with the goal of supporting validation and training. The simulation will be very easy to use by simple execution on a networked PC. It will connect to NASA's robot-control frameworks and be easy to configure using a drag-and-drop interface. It will be thorough in its ability to model a range of environments, from terrestrial to lunar, and through its ability to provide accurate sensor and truth data for analysis. It will include simulation of communication latency and bandwidth restrictions. Sensors will be modeled through a powerful plugin interface that supports tying stimulation of new sensor modalities to terrain and objects. The effort will include the development of robot, sensor, and environment models tailored to the simulation of field-study vehicles, and it will emphasize mimicking the network interfaces used by NASA. The proxy simulation will be able to model multiple and disparate robots simultaneously. Energid will implement and deliver a complete, executable system and an underlying C++ software toolkit.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proxy simulation tool will have application to many of NASA's training exercises and studies. Many types of robotic vehicles will need to be simulated for testing, verification, and training prior to upcoming lunar and planetary missions. The tool Energid proposes will reduce cost and improve schedule in many efforts and is expected to be widely used by NASA. In addition to the direct tool for proxy simulation, the underlying capability will be developed as a C++ software toolkit. This toolkit will benefit NASA in ways other than just proxy simulation. It will also support verification and validation and stand-alone simulation to test hardware improvements, control algorithms, and interface software. It will support the injection of robot and communication faults. Energid will commercialize the results of this project through support contracts and extensions to meet NASA's developing needs. Energid will partner with larger NASA contractors to commercialize the capability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Energid will develop the proxy simulation as a software toolkit for resale and as a turnkey program. The toolkit will extend and augment Energid's Actin toolkit in its support for testing, training, and robot control. Robot developers in the government and in commercial entities will use the software to reduce development time and improve the quality of completed robotic systems. Potential toolkit customers will purchase the toolkit as software libraries and header files. By linking these libraries into their code, developers will have full access to all the simulation capability provided by the toolkit. Turnkey software customers will create new CAD models of robots in third-party software that can be loaded and used immediately. Energid currently sells its Actin robot control and simulation toolkit and its Actin Viewer turnkey software commercially, and is well positioned to commercialize the capability developed under this project.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Mobility
Perception/Sensing
Teleoperation
Operations Concepts and Requirements
Simulation Modeling Environment
Training Concepts and Architectures
Testing Requirements and Architectures
Human-Computer Interfaces
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 X1.03-9438
PHASE-1 CONTRACT NUMBER: NNX10CF01P
SUBTOPIC TITLE: Radiation Hardened/Tolerant and Low Temperature Electronics and Processors
PROPOSAL TITLE: Improved Design of Radiation Hardened, Wide-Temperature Analog and Mixed-Signal Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corp.
215 Wynn Drive, 5th Floor
Huntsville, AL 35805-1944
(256) 726-4858

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Marek Turowski
sxh@cfdrc.com
215 Wynn Dr.
Huntsville,  AL 35805-1944
(256) 726-4889

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA space exploration missions require the electronics for avionic systems, components, and controllers that are capable of operating in the extreme temperature and radiation environments of space and planetary surfaces. To design wide-temperature, radiation-hardened (rad-hard) electronics and predict the characteristics and reliability in these extreme environments, advanced models and simulation tools are required at multiple levels. Analog and mixed-signal circuits for space exploration have not been adequately addressed to date. The proposed project aims to design, develop, validate, and demonstrate novel Radiation Hardened By Design (RHBD) analog/mixed-signal, RF and digital integrated circuits (ICs) aimed for application in NASA relevant extreme environments. In Phase 1, CFDRC, in collaboration with Georgia Tech, accomplished the following: (1) enhanced and demonstrated CFDRC's unique physics-based mixed-mode simulation tools (NanoTCAD coupled with Cadence Spectre) for predicting transient radiation response of benchmark analog circuits based on silicon-germanium (SiGe) BiCMOS technology; (2) leveraged experimental radiation/temperature data collected under the NASA Exploration Technology Development Program (ETDP) SiGe project to validate new low-T device physics models in NanoTCAD and understand associated physical phenomena; and (3) developed preliminary RHBD concepts for single-event hardening, including the novel inverse-mode cascode (IMC) SiGe HBT. In Phase 2, we will demonstrate and validate the improved physics-based models for temperature range from -230<SUP>o</SUP>C to +130<SUP>o</SUP>C, and apply them to evaluate and develop RHBD designs over the expected operating range. New RHBD devices employed in analog, RF and digital circuits will be fabricated in prototype chips and tested over a wide temperature range and in a radiation environment, and delivered as a component library for NASA use.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Prediction of electrical performance and radiation tolerance of electronic components in extreme environments (wide temperature range, radiation) are crucial for designing reliable electronics for all NASA robotic exploration missions, such as planned Europa Jupiter System Mission, Titan Saturn System Mission, Venus In-Situ Explorer, sample return from Comet, Asteroids, and continued lunar and Mars exploration missions. Since electronic parts are getting smaller with technology evolution, the radiation/temperature effects are becoming more severe ? the lifetime and reliability are quickly becoming critical issues ? the physics-based capability to predict the behavior of electronic circuits increases confidence and reduces mission risk. Radiation-hardened and wide-temperature analog, mixed-signal, RF and digital circuits are essential for all the avionic systems used in the NASA exploration projects. The optimized, wide-temperature RHBD designs from this SBIR will add to the pre-existing NASA "component library". The wide-temperature, physics-based mixed-mode tools will help NASA to design rad-hard low-temperature electronics with better understanding and control of design margins, and will enable designers to better evaluate the wide-temperature performance and radiation response at an early design stage and set requirements for hardening and testing, thereby reducing the amount of testing time and cost.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Various critical analog, mixed-signal, RF and digital circuits are used in all space-based platforms, including DoD space systems (communication, surveillance, ballistic missiles, missile defense), and commercial satellites. Since modern electronics technologies and components are becoming increasingly sensitive to extreme environments, the mission lifetime and reliability are becoming increasingly critical, and the capability to predict their behavior dramatically increases confidence and reduces risk. The new RHBD designs and circuit/cell libraries, as well as the physics-based computer aided design (CAD) tools, can also be applied to cryogenic electronics for high-sensitivity, low-noise analog and mixed-signal applications, such as metrology, infrared (IR) imagers, sensors (radiation, optical, X-ray), radiometrology, precision instruments, radio and optical astronomy, infrared and photon detectors, and other high-end equipment. For all such devices and systems, predictive and accurate modeling and design tools reduce the amount of required radiation/temperature testing, thus decreasing their cost, and time to market or field application.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 X1.03-9811
PHASE-1 CONTRACT NUMBER: NNX10CF02P
SUBTOPIC TITLE: Radiation Hardened/Tolerant and Low Temperature Electronics and Processors
PROPOSAL TITLE: Unconditionally Stable Low Dropout Regulators for Extreme Environments

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SJT Micropower
16411 N. Skyridge Lane
Fountain Hills, AZ 85268-1515
(480) 816-8077

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Seth Wilk
swilk@sjtmicropower.com
16411 N. Skyridge Lane
Fountain Hills,  AZ 85268-1515
(602) 703-3730

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We have developed a low dropout (LDO) regulator using a patented MESFET transistor technology that can be manufactured in commercial CMOS foundries with no changes to the process flow. The regulator is stable under all load conditions without an external compensation capacitor, thereby reducing the mass/volume of the power management system and increasing reliability. The MESFET-based LDO component has very competitive figures of merit (dropout voltage, transient response, power supply rejection) compared to existing components. During Phase 1 we confirmed that the components were unconditionally stable without an external compensation capacitor over the temperature range -196C to +150C and for radiation doses up to 1 Mrad(Si). We shall build on the Phase 1 design effort to demonstrate two fully integrated LDO regulators rated up to 1A with dropout voltages of less than 50 mV. One part will be fabricated using a qualified rad-hard SOI CMOS foundry in collaboration with Honeywell, one of our commercialization partners. The other component will be fabricated using the low-cost/high-volume foundry available from IBM. Both parts will have a nominal output voltage of 1.8V with 1% accuracy. Other designs will target user adjustable voltages in the range 1.2-2V. The feasibility of using the MESFET technology for low voltage applications (e.g. 0.8V) will be explored. All parts will be tested over the temperature range -150C to +150C and after irradiation exposure to a TID of 1 Mrad from a Co-60 source. The enhanced low dose rate sensitivity (ELDRS) of the components will be studied using a low dose rate Cs-137 source. The characteristics of all the components will be documented, and parts made available to NASA and potential customers as deliverables from the Phase 2 activity. We shall work with our commercialization partners to have the LDO regulator design adopted as a licensed 'IP block' and to develop low cost versions for the wider consumer electronics market.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The MESFET-based linear regulator technology has the potential for widespread NASA applications in power management systems exposed to extreme environments. The high radiation tolerance we have demonstrated is attractive for orbital earth science studies as well as lunar and interplanetary missions. Our technology may even be suitable for spacecraft exposed to high radiation environments such as the Europa Jupiter System Mission. Missions to the outer reaches of the solar system that depend on a radiothermal generator are exposed to on-board radiation from the RTG and require the high level of radiation tolerance we expect from the final MESFET regulator component. We expect the MESFET technology to be relatively immune to single event effects and therefore suitable for solar observatories and lunar sensors exposed to solar flares. The MESFET technology can operate over the -196C<T<+150C temperature range, making it useful for robotic systems on the Moon or Mars. The current Martian rovers use a thermally controlled warm-electronics-box (WEB). Innovations on the Mars Science Laboratory have allowed wide temperature range electronics to be placed outside the WEB thereby reducing weight and increasing reliability. Our wide temperature range MESFET technology will enable further innovation for missions to hostile and extreme environments. This includes missions to Venus that employ environmental chambers with temperatures controlled to T<150C.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low dropout regulators are ubiquitous in commercial consumer electronics and automotive systems. A non-hardened version of the regulator we are proposing to develop will be inexpensive to manufacture using high volume commercial CMOS foundries. Our business models show that such a component can be manufactured at a cost per die that is competitive with existing products but without the need for an external compensation capacitor thereby reducing the overall costs and part count of the power management system. If this is confirmed our regulator component has the potential for widespread commercial adoption. We are working with our commercialization partners at On Semiconductor and Honeywell to develop these non-NASA applications. As well as a standalone product, we are developing the low dropout linear regulator as a scalable design that can be included in application specific integrated circuits (ASICs) as a licensed 'IP block'. ASICs are widely used for non-NASA applications by the Department of Defense and aerospace companies.

TECHNOLOGY TAXONOMY MAPPING
Radiation-Hard/Resistant Electronics
Power Management and Distribution


PROPOSAL NUMBER: 09-2 X1.03-9937
PHASE-1 CONTRACT NUMBER: NNX10CF03P
SUBTOPIC TITLE: Radiation Hardened/Tolerant and Low Temperature Electronics and Processors
PROPOSAL TITLE: Wide Temperature Rad-Hard ASIC for Process Control of a Fuel Cell System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ridgetop Group, Inc.
6595 North Oracle Road
Tucson, AZ 85704-5645
(520) 742-3300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Justin Judkins
justin.judkins@ridgetopgroup.com
6595 North Oracle Road
Tucson,  AZ 85704-5645
(520) 742-3300

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ridgetop Group developed a top-level design of a rad-hard application-specific integrated circuit (ASIC) for spacecraft power management that is functional over a temperature range of -180 to +130 <SUP>o</SUP>C. This ASIC is intended to work in conjunction with a fuel cell power system and battery backup to provide uninterrupted power to critical modules in space. Ridgetop has designed a novel integrated circuit for the power management of space systems. This design combines custom circuit modules with silicon-proven IP to create a system-on-chip solution. This application will be a single monolithic circuit designed for fabrication on the IBM 5AM SiGe process. The significance of this innovation is a single reliable component (ASIC) that will meet platform requirements for high voltage, wide operating temperature range, and radiation tolerance (minimum 100 krads total ionizing dose (TID), and 100 MeVcm2/mg single-event latchup (SEL)). Ridgetop has been working with a prime contractor to identify and flow-down mission requirements for the power management ASIC. During Phase 2, a final prototype unit will be fabricated to these specifications, and units will be packaged, tested, and silicon validation results will be produced. Estimated TRL at beginning and end of Phase 2 contract: Begin: 3, End: 6

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology will provide numerous tangible benefits to space vehicle programs, including; (1) lower power draw, (2) higher reliability, and (3) lower mass. Commercial applications include power management systems for remotely located telecom switches requiring critical, uninterrupted power management. Platforms include lunar and deep space exploration vehicles, International Space Station, and Ice-Penetrating Radar for Mars, Europa, and Ganymede Orbiter Missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Ridgetop has met with officials at Ballard Power systems to discuss the fit of this advanced technology into the next generation of fuel cells for ground-based and aircraft-based applications. The technology will be directly applicable to the alternative energy generation and addresses automotive markets, satellites, and portable fuel cells. In the electric vehicle market, stacks of fuel cells or batteries are used to power the drive motors. These fuel cell stacks, coupled with the technology from this SBIR Program, would be the ideal application for the work products from this program. Power management is essential during use, refueling, or battery recharging.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
On-Board Computing and Data Management
Autonomous Control and Monitoring
Radiation-Hard/Resistant Electronics
Earth-Supplied Resource Utilization
Semi-Conductors/Solid State Device Materials
Energy Storage
Photovoltaic Conversion
Power Management and Distribution


PROPOSAL NUMBER: 09-2 X1.04-9306
PHASE-1 CONTRACT NUMBER: NNX10CC42P
SUBTOPIC TITLE: Integrated System Health Management for Ground Operations
PROPOSAL TITLE: Fusion of Built in Test (BIT) Technologies with Embeddable Fault Tolerant Techniques for Power System and Drives in Space Exploration

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Impact Technologies, LLC
200 Canal View Blvd.
Rochester, NY 14623-2893
(585) 424-1990

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Antonio Ginart
antonio.ginart@impact-tek.com
200 Canal View Blvd
Rochester,  NY 14623-2893
(404) 526-6188

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Impact Technologies has proposed development of an effective prognostic and fault accommodation system for critical DC power systems including PV systems. Overall goal for this program is development of techniques that enable power system fault tolerance based on diagnostic features from the solar cells, power bus, and power transistors. After completion of Phase I efforts towards this goal, Impact has achieved substantial and promising results in several technical areas that provide opportunities for maturing PHM tools. The technical areas covered include: 1) solar cell modeling and characterization, 2) power system monitoring, 3) semiconductor device modeling and aging characterization, and 4) application of the leakage current sensing to DC systems. During Phase II, impact will apply and maturing phase I accomplishments to incorporate and embed effective PHM techniques and fault tolerance for power system reliability and extended operation. Impact also plans development of a prototype low cost dynamic leakage current sensor for solar cell and DC power system application. The long-term implications of a successful completion of this program will provide reliability and health management tools for the state-of-the-art technologies, such as advanced power systems based on solar power generation, contributing directly to NASA's ISHM efforts.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The development of the proposed prognostics and fault tolerant reconfiguration strategies will directly contribute to NASA's ISHM efforts, particularly for several components of the Constellation program. Although the Constellation program and its scope are uncertain at the moment, the techniques Impact is developing will be leveraged into systems that are a mainstay in space exploration such as satellites and solar power systems. The proposed technologies are generic in nature and are applicable to future generation aviation platforms, leading to benefits in the form of improved reliability, maintainability, and survivability of safety-critical electrical power and electro-mechanical systems. The long-term implications of a successful completion of this program will provide reliability tools for the state-of-the-art technologies in power generation, management, and intelligent control. Several of NASA's NextGen and current activities can take immediate advantage of these technologies. In the short term, the device level modeling and reconfigurable strategies to be developed in this program can be directly transitioned to ongoing research at the NASA research centers. The adaptable nature of modules presented in this program will allow them to act as design and development tools for a wide variety of NASA applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential benefits from the successful completion of this program are enormous and will significantly impact the way critical aerospace, power devices, controllers, and other systems are designed, particularly in the alternative power generation and management domains. Examples of key customers that could benefit through use of the developed technologies include power system manufacturers, commercial airlines, power semiconductor device and drive manufacturers, commercial power utilities, land and marine propulsion systems, unmanned air vehicles, Joint Strike Fighter (JSF), future combat systems (FCS), industrial actuation systems, and robotic applications. Particularly, the reliance on solar power generation and DC system in commercial applications specific requirements on health management performance for which these technologies can provide value by increasing reliability and safety for critical components. Impact has existing contracts with all these potential customers and has an excellent commercialization record.

TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data Management
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics
Photovoltaic Conversion
Power Management and Distribution
Renewable Energy


PROPOSAL NUMBER: 09-2 X2.01-8518
PHASE-1 CONTRACT NUMBER: NNX10CF24P
SUBTOPIC TITLE: Spacecraft Cabin Atmosphere Revitalization and Particulate Management
PROPOSAL TITLE: CO2 Removal from Mars EMU

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TDA Research, Inc.
12345 W. 52nd Avenue
Wheat Ridge, CO 80033-1916
(303) 940-2300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gokhan Alptekin
galptekin@tda.com
12345 W. 52nd Avenue
Wheat Ridge,  CO 80033-1916
(303) 940-2349

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A practical CO2 control system for ExtraVehicular Activity (EVA) on Mars have not yet been developed. TDA Research, Inc. proposes to develop a durable, high-capacity, continuously regenerable sorbent that can remove CO2 from the breathing loop. The energy for regeneration is provided by the metabolic load, and the sorbent can be regenerated at or above 6 torr, eliminating the potential for Martian atmosphere to leak into the regeneration bed and into the breathing loop. In Phase I, we demonstrated the feasibility of the concept in a series of bench-scale experiments and by conducting a preliminary system analysis. We showed the sorbent regeneration can be accomplished with a temperature swing of only 17C, The entire system runs at near ambient temperature, and the sorbent can be regenerated at 13 torr (well above the Martian atmospheric pressure). We also performed over 1,000 adsorption/regeneration cycles to demonstrate the life of these sorbents. The major objective in Phase II is to design and fabricate a full-scale breadboard prototype unit to demonstrate the merits of the new technology. We will also improve the sorbent formulation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The main attraction of our research to NASA is its ability to provide a lightweight, compact, and efficient CO2 removal system capable of regenerable, extended operation during the EVAs. Continuous regeneration during the EVAs eliminates the consumable requirement related to the use of LiOH canisters and the mission duration limitations imposed by MetOx system. If proven successful, the concept will minimize the amount of consumables brought from Earth and make the mission more affordable, while providing great operational flexibilities during the EVAs

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The sorbent developed in this project could potentially find use in a large commercial market in the removal of CO2 emissions from the coal-fired power plants. If regulations are put in place to curb carbon emissions from power plants the potential market for a successful sorbent is in the order of billions of dollars.

TECHNOLOGY TAXONOMY MAPPING
Portable Life Support


PROPOSAL NUMBER: 09-2 X2.01-8688
PHASE-1 CONTRACT NUMBER: NNX10CF25P
SUBTOPIC TITLE: Spacecraft Cabin Atmosphere Revitalization and Particulate Management
PROPOSAL TITLE: Novel Catalytic Reactor for CO2 Reduction via Sabatier Process

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Precision Combustion, Inc.
410 Sackett Point Road
North Haven, CT 06473-3106
(203) 287-3700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christian Junaedi
cjunaedi@precision-combustion.com
410 Sackett Point Rd.
North Haven,  CT 06473-3106
(203) 287-3700

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel short contact time Microlith Sabatier reactor system for CO2 reduction offers a significant advance in support of manned spaceflight. Compared to current and prospective alternatives (including microchannels), the reactor will be much smaller and lighter, more energy and resource efficient, and more durable. In the spacecraft cabin atmosphere revitalization system (ARS), the utilization of CO2 to produce life support consumables, such as O2 and H2O, via Sabatier process as part of the CO2 Reduction Assembly (CRA) is an important function for both low-earth orbit and long-term manned space explorations, and also has application for lunar/Martian ISRU concepts. The maturation of this technology will significantly reduce launch weight requirements and the need of re-supply from Earth. Precision Combustion, Inc. (PCI) proposes to build on Phase 1 proof of concept success to develop, demonstrate, and deliver an integrated Microlith<SUP>REG</SUP>-based ground test Sabatier reactor Development Unit (SDU) for CO2 reduction, with collaborative support from a systems integrator. The SDU will convert CO2 and H2 to methane and water, achieving close-to-equilibrium CO2 conversions at high throughputs and at low operating temperatures (&#8804;350<SUP>o</SUP>C). Major systems integrator participation will help guide the program. TRL is now 4 and will be advanced to 5.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
CO2 Reduction System/Methanation: Precision Combustion's Sabatier reactor will create oxygen in cabin closed-loop atmosphere revitalization systems (ARS) and Lunar/Martian ISRU concepts that are key for sustained space missions. The technology will provide an ultra-compact, high efficiency catalytic CO2 methanation reactor for converting cabin air or lunar/Mars-sourced CO2 with H2 to methane and water vapor, the latter for use with an electrolyzer to generate O2 for spacecraft cabin ARS and mobile EVA applications. The methane can be used as fuel, e.g. for surface operations or return thrust, or for other chemicals manufacture in advanced ISRU applications. Technology variants of the Microlith reactor may emerge for other ISRU manufacturing. The technology's minimized size and maximized efficiency and durability will significantly reduce launch weight for long missions, and offers high value added for NASA

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology offers a potential breakthrough that can also be integrated with process intensification techniques. Targeted non-NASA applications for a Microlith chemicals reactor include methanation reactors to be used in conjunction with solid oxide or molten carbonate fuel cells for power production, improved Haber process operations for producing ammonia for fertilizer or ammunition, and the general case of selectivity-sensitive chemicals manufacturing where temperature control and the unique Microlith geometry may offer advantages (including production of formaldehyde and methanol, and biogas conversion). Some of these processes currently require very large capital investments in large plants, allowing potential for a small, effective and selective reactor to find targeted applications of value.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning


PROPOSAL NUMBER: 09-2 X2.01-9873
PHASE-1 CONTRACT NUMBER: NNX10CF27P
SUBTOPIC TITLE: Spacecraft Cabin Atmosphere Revitalization and Particulate Management
PROPOSAL TITLE: Development of a Cathode Liquid Feed Electrolyzer to Generate 3,600 PSI Oxygen for Both Lunar and Space Microgravity Environments

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Giner Electrochemical Systems, LLC
89 Rumford Avenue
Newton, MA 02466-1311
(781) 529-0500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Timothy Norman
tnorman@ginerinc.com
89 Rumford Avenue
Newton,  MA 02466-1311
(781) 529-0556

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Giner Electrochemical Systems (GES) proposes to develop a cathode liquid feed, proton-exchange membrane electrolyzer stack and system capable of producing 3,600 psi oxygen. We propose to subcontract Hamilton-Sundstrand Human Space Systems (H-S) to share unique state-of-the-art technologies that provide the best path to meeting program objectives. GES will share their data and expertise with high balanced pressure electrolyzers and H-S will contribute their data and expertise in high differential pressure electrolyzer systems. Based on the high pressure anode design concept developed in Phase I, GES will further develop the electrolyzer cell and stack design. In parallel, H-S will develop the key subsystem and control components for a brassboard balance of plant. The program will culminate in the fabrication, assembly, and demonstration of a brassboard high oxygen pressure generation system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is charged with returning humans to the moon in a permanently occupied lunar station. This mission will require astronauts to conduct extravehicular activities while en route to the moon, and while on the lunar surface. To operate in these environments, the astronauts need an on-site source of pressurized oxygen to refill empty tanks. A very-high-pressure PEM water electrolyzer is proposed that can produce a minimum of 3,600 psi oxygen and hydrogen without the need for high-pressure pumps and/or compressors. A very-high-pressure water electrolyzer will permit smaller launch volumes, saving space aboard the Orion crew exploration vehicle. The electrolyzer might also be useful for the production of hydrogen and oxygen for space vehicle propulsion, enabling missions to Mars. Other electrolyzers of similar designs may be used to produce oxygen and hydrogen for energy storage purposes in regenerative fuel cells on the lunar and Martian surfaces. Other electrolyzers may be used for generation of oxygen on the lunar surface without a net consumption of water through in situ resource utilization (ISRU). By making all of these electrolyzers compatible with one another, if not identical, it may be possible for NASA to save significant development resources while improving astronaut life support safety margins by increasing redundancy.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Quiet and compact oxygen generators may be useful for Navy SEAL missions. Such electrolyzers as closed-loop regenerative fuel cells are potential battery substitutes for applications that require high energy density. Several agencies of the U.S. Government and several private businesses are engaged in development of long-endurance aircraft and airships. The high-pressure electrolyzer developed under this proposed program may be applicable to these vehicles. Large-scale power storage via regenerative fuel cells may have terrestrial applications in telecommunications and other industries that require uninterruptible power supplies.

TECHNOLOGY TAXONOMY MAPPING
Portable Life Support
Suits
In-situ Resource Utilization
Microgravity
Composites
Metallics
Energy Storage


PROPOSAL NUMBER: 09-2 X2.02-9461
PHASE-1 CONTRACT NUMBER: NNX10CC47P
SUBTOPIC TITLE: Spacecraft Habitation Systems, Water Recovery and Waste Management
PROPOSAL TITLE: High Efficiency, High Output Plastic Melt Waste Compactor (HEHO-PMWC)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Orbital Technologies Corporation
Space Center, 1212 Fourier Drive
Madison, WI 53717-1961
(608) 827-5000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeff Johnson
johnsonj@orbitec.com
1212 Fourier Drive
Madison,  WI 53717-1961
(608) 229-2828

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovative High Efficiency, High Output Plastic Melt Waste Compactor (HEHO-PMWC) is a trash dewatering and volume reduction system that uses heat melt compaction to remove nearly 100% of water from trash and reduce the volume by up to 11 times. The HEHO-PMWC system incorporates novel methods to compress the trash, recover water, and remove the resultant plastic tiles. This system requires access to power, data, and cooling interfaces. The system is suitable for recovering water and compacting all trash sources on the ISS. The system has also been designed to recover water from brine solutions produced by primary wastewater processing systems. The HEHO-PMWC works by heating and compressing trash simultaneously to first remove water and then to melt plastic in the trash. The melted plastic encapsulates the trash into a 16 inch square tile, approximately inch thick. The square tile is easier to store than a round tile and is a more effective radiation shield. Variables such as transport vehicle availability, ISS mass, power and space availability, and ISS cooling capabilities were considered. The resulting HEHO-PWMC system, proposed here, was sized to process 3-4 kg of trash per batch while operating three times per day.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application of this technology is for any long-duration human spaceflight mission, including microgravity and planetary surface operations. Besides the primary benefits of the HEHO-PMWC, which include waste volume reduction and water recovery, secondary benefits include additional health benefits from completely encapsulating the final compacted waste product, ultimately deterring microbial elements from entering the breathable airstream, and the plastic tile byproduct, which is high in polyethylene, can be used as an effective radiation barrier. The conceptual design for the Phase II was designed for implementation on the ISS, but the design can be easily modified for various waste model loads and mission architectures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The HEHO-PWMC will be a valuable system for commercial space vehicles and modules. A system that reduces waste volume, recovers water, and creates a useful byproduct can be a boon for commercial aerospace companies trying to reduce overall mission costs. The benefits of HEHO-PMWC are immediately known for LEO destination providers such as Bigelow Aerospace. With inflatables, no inherent radiation shielding is present on the outside diameter of the module; so radiation shielding (i.e., water) must be added post-inflation. The HEHO-PMWC would reduce the amount of water that must be launched by producing radiation tiles from trash. The PMWC could produce enough tiles to shield the entire module in less than a year. The recovered water could also function as a radiation barrier. The HEHO-PMWC would provide an effective and efficient waste management system, provide necessary radiation shielding products, assist in maintaining a clean environment, and minimize launch costs.

TECHNOLOGY TAXONOMY MAPPING
Inflatable
Waste Processing and Reclamation
In-situ Resource Utilization
Radiation Shielding Materials


PROPOSAL NUMBER: 09-2 X2.02-9562
PHASE-1 CONTRACT NUMBER: NNX10CC48P
SUBTOPIC TITLE: Spacecraft Habitation Systems, Water Recovery and Waste Management
PROPOSAL TITLE: Advanced Aqueous Phase Catalyst Development using Combinatorial Methods

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
UMPQUA Research Company
P.O. Box 609
Myrtle Creek, OR 97457-0102
(541) 863-7770

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Akse, Ph.D.
akse@urcmail.net
PO Box 609
Myrtle Creek,  OR 97457-0102
(541) 863-2653

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Combinatorial methods are proposed to develop advanced Aqueous Oxidation Catalysts (AOCs) with the capability to mineralize organic contaminants present in effluents from current and future primary wastewater treatment processes at temperatures less than 70?aC, pressures below 20 psig, and contact times under 30 minutes. The Phase II effort will build upon the successful Phase I feasibility demonstration and identify rate-limiting factors for contaminant oxidation identified in the best Phase I AOCs. A new series of combinatorial catalysts will be prepared with the goal to systematically improve catalyst performance. Improvements will focus on contaminant and reaction byproduct adsorption, mass transfer resistances, and reaction rate limitations associated with noble metal concentration, dispersion, and support interaction. A second-generation combinatorial library with 102 AOCs will be prepared based on this analysis. Oxidation activity will then be compared using a difficult to oxidize ersatz solution containing contaminants known to occur in the current U.S. water processor aboard the ISS. These tests will select the best AOC based upon analysis of oxidation kinetics. This AOC will undergo long-term testing to verify performance. Scale-up activities will follow, resulting in a full-scale, deliverable prototype. The advanced AOC will lower water processor ESM and provide multiple commercial opportunities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The NASA application for this technology will be as Flight Hardware for deployment in support of future, long duration exploration objectives beyond Low Earth Orbit (LEO) were efficient water recovery will play a critical role in reducing ECLSS logistics. The ability to mineralize organic contaminants present in effluents from current and future primary water processors at low temperature and pressure is an extremely valuable technology. Reduction in power usage, improvement in safety and reliability, and lower maintenance requirements are highly valued characteristics of this technology that will lower ESM for current and future water reclamation processes used aboard spacecraft and within lunar and planetary habitats.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercialization of this technology has many opportunities in environmental remediation, semiconductor production, and pharmaceutical industries as well as consumer products. AOCs that oxidize organic contaminants at low temperatures can be used to clean-up wastewater or groundwater, or for the production of ultra-pure water. AOCs are extremely attractive for in situ environmental clean-up using a pump and treat system, where energy usage must be minimized. Current ultra-pure water production systems are limited to specific oxidation technologies and will be challenged by more stringent requirements in the next generation semiconductor fabrication facility. Low temperature non-specific oxidation processes will help meet these water quality standards in a cost-effective manner.

TECHNOLOGY TAXONOMY MAPPING
Waste Processing and Reclamation


PROPOSAL NUMBER: 09-2 X2.03-8721
PHASE-1 CONTRACT NUMBER: NNX10CE26P
SUBTOPIC TITLE: Spacecraft Environmental Monitoring and Control
PROPOSAL TITLE: Micro GC's for Contaminant Monitoring in Spacecraft Air

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cbana Laboratories
2021 South First Street, Suite 206
Champaign, IL 61820-7477
(217) 239-1963

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Qingmei Chen
qingmei.chen@cbana.com
2021 South First Street, suite 206
Champaign,  IL 61820-7478
(217) 244-4872

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Based on the successful separation of 20 compounds using a 1 m coated microcolumn in Phase I, we propose to design a new micro-gas chromatograph (microGC) system to separate and detect of all contaminants listed in NASAs "Spacecraft Maximum Allowable Concentrations for Airborne Contaminants (SMACs)" using cabin air as the carrier gas, and to integrate the entire system to maximize the detection of the contaminants with high-sensitivity and accuracy. In order to attain these goals, we will use three sets of preconcentrators, columns, and detectors in parallel, each with the appropriate selectivity for a given class of gases. Light gases will use a packed column, and polar and non-polar gases with their respective stationary phases. The prototype micro-GC/FID will comprise preconcentrators with fast injection valves, microcolumns to separate different gas analytes, an air sampling pump, a water-hydrolysis hydrogen generator to provide enough oxygen and hydrogen for a micro-flame ionization detector, thermal management, controls and circuit board to drive the system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
If we are successful through Phase II, we will demonstrate that the Cbana microGCs can detect a broad range of contaminants in spacecraft air without needing externally supplied reagents. The devices will increase the number of contaminants that can be detected now and lower the need for unstable reagents or calibration mixtures. Further, the microGC's will be small enough and light enough, and be energy efficient enough to be included in Extravehicular Mobility Units.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The microGCs have a wealth of potential commercial opportunities. Examples include: indoor air quality (IAQ) monitoring and remediation, industrial pollution containment and elimination, narcotics detection, cargo monitoring, explosives detection, and lung cancer screening. Also, we will have a military device to detect chemical warfare agents that can support a 7-day mission packaged in the space of only a few cubic centimeters. This integrated device comprising a micro-GC, detectors, reagents and power supply will have the potential to: 1) identify chemical threats in a battlefield; 2) provide assessment of warfighter health status, chemical exposure, stress level, and hydration; and 3) detect human activity in caves and other structures. The use of Cbana components in NASA missions will aid the deployment of Cbana's sensors in the commercial market. One of the key milestones in Cbana's business plan is to secure independent groups to validate the technology. Inclusion of the Cbana equipment as an integral component of one or more NASA missions would facilitate our goal of independent validation, hence furthering commercial market acceptance.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Biomedical and Life Support
Biomolecular Sensors
In-situ Resource Utilization
Organics/Bio-Materials


PROPOSAL NUMBER: 09-2 X2.03-9435
PHASE-1 CONTRACT NUMBER: NNX10CE27P
SUBTOPIC TITLE: Spacecraft Environmental Monitoring and Control
PROPOSAL TITLE: A Miniaturized Sensor for Microbial Monitoring of Spacecraft Water Environment

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corp.
215 Wynn Drive, 5th Floor
Huntsville, AL 35805-1944
(256) 726-4858

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yi Wang
sxh@cfdrc.com
215 Wynn Dr.
Huntsville,  AL 35805-1944
(256) 327-0678

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Accurate real-time microbial monitoring of water environment is of paramount importance to crew health as well as to ensure proper functioning and control of the life support system during space exploration. The existing methods are time-consuming and labor-intensive, and the devices used are bulky, consumable-hungry, and ill-suited for spacecraft deployment. We propose to develop and demonstrate a novel, fully automated, milli-/micro-fluidics-based sensor cartridge for sample preparation and detection of microbes in water. The final product will be compact, accurate, fully integrated and automated, power-effective, and fieldable in space environments. In Phase 1, key technology elements have been successfully demonstrated. Major components of the sensor cartridge were designed using a computational virtual-prototyping approach followed by state-of-the-art microfabrication and engineering. Experiments with microbial samples commonly found in space water environment were undertaken to demonstrate component functionality and to establish proof-of-concept of the proposed technology. In Phase 2, efforts will focus along two lines. First, component design optimization will be carried out with fabrication enhancements and extended testing and characterization for technology validation. Second, an integrated microfluidic cartridge and instrumentation capable of automated operation (sample processing and detection) will be developed. The prototype instrument will be demonstrated in both terrestrial and hypogravity environments (in collaboration with NASA researchers/facilities). A multi-disciplinary team with experience in all aspects of the proposed effort including fluidic system design, fabrication and experimentation, systems engineering, microbiology and spaceflight has been assembled to ensure successful completion of project milestones.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The end product of the proposed SBIR effort will be a first-of-its-kind, compact, label-free, fully automated and integrated microbial sensor device for water monitoring. The device will provide NASA a powerful tool for real-time microbial detection and identification, and greatly aid in NASA's efforts to minimize microbial exposure/infection hazard, develop countermeasures, and ensure proper functioning and quality-control of life support system in spacecrafts, space shuttles and space stations. The device will be of direct use to NASA's ground-based research facilities and amenable for space deployment as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed sensor technology will have direct commercial value in both federal and civilian sectors. The device can be used for US Navy shipboard wastewater monitoring or on-field assessment of water quality during military mission. The anticipated civilian applications include: ? Pre-clinical and clinical diagnostics (e.g., microbial detection in body fluids) ? Public and natural water monitoring (e.g., hospital & health site, recreational and drinking waters) ? Industrial wastewater surveillance (e.g., water treatment and food-processing plants)

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Sterilization/Pathogen and Microbial Control
Biochemical
Optical


PROPOSAL NUMBER: 09-2 X2.04-8356
PHASE-1 CONTRACT NUMBER: NNX10CD24P
SUBTOPIC TITLE: Spacecraft Fire Protection
PROPOSAL TITLE: A Quantum Cascade Laser-Based CO Sensor for Fire Warning

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Maxion Technologies, Inc.
20 New England Business Center
Andover, MA 01810-1077
(301) 405-8426

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Bradshaw
jbradshaw@maxion.com
5000 College Avenue, Suite 3121
College Park,  MD 20740-3817
(301) 405-8426

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Maxion Technologies, Inc. (Maxion) proposes to develop and field test a Carbon Monoxide (CO)-sensor prototype for post fire cleanup and CO detection. The sensor will have the dynamic range required to detect and monitor CO from approximately 1 to 500 ppmv with a resolution to 1 ppmv. Maxion will grow, fabricate and test a Quantum Cascade Laser (QCL) at a unique single-mode wavelength ideal for CO detection. Maxion will team with Physical Sciences Inc. (PSI) to integrate the QCL into PSI's Wavelength Modulation Spectroscopy (WMS) platform. The WMS sensor board, previously developed for near-IR lasers, will be redesigned to accommodate QCL lasers. The QCL will be specially designed and fabricated for minimum power consumption. In Phase 1 the QCL was incorporated into the WMS platform and tested on a breadboard level. The breadboard sensor demonstrated the necessary dynamic range and easily surpassed the required minimum sensitivity. A Phase II prototype design was made based on the Phase I results for which dynamic range, sensitivity, SWaP, and operation with a high degree of reliability, minimal maintenance, and self-calibration under varying humidity and ambient pressures are primary design features. The sensor prototype will be tested in a relevant environment with controlled burns at a NASA test facility. Upon successful completion of all field tests, the TRL will be 6 at the end of Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed Carbon Monoxide (CO) sensor prototype design is targeted for monitoring the post-fire cleanup atmosphere of a crew cabin. The sensor also has sufficient sensitivity for monitoring the presence of CO at low levels. As such, the sensor has applications for upper atmospheric studies and environmental monitoring. More generally, the adaptation of PSI's control electronics package to include the Quantum Cascade laser technology allows for the further development of this package for detection of other trace gases using different QC Lasers to detect other chemical species of interest in other NASA programs. Further development of this technology for sniffer and hand held sensor applications are enabled as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The work reported herein represents the successful adaptation of PSI's wavelength modulation spectroscopy (WMS) system to incorporate the QC laser technology. This is the first step toward a successful Phase 3 implementation. First, the QC lasers for CO sensing are offered for sale by Maxion along with QC lasers for chemical sensing of other molecular species. Secondly, the incorporation of the QC lasers into PSI's WMS-board-based detection system will allow for more rapid commercialization of the combined technologies (the WMS board with the QCL source and other components) as it leverages the already well recognized potential of the QC lasers for chemical sensing. The combination of an integrated PC-board based sensing system and the commercial availability of the QC lasers will allow commercial users to more quickly develop the QC-WMS technique to chemical sensing applications of significant commercial interest. Faster commercial development for niche applications will promote volume pricing leading to accelerated adoption of the technology in higher volume applications.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Spaceport Infrastructure and Safety
Optical
Photonics


PROPOSAL NUMBER: 09-2 X2.04-9618
PHASE-1 CONTRACT NUMBER: NNX10CD25P
SUBTOPIC TITLE: Spacecraft Fire Protection
PROPOSAL TITLE: Nonflammable Crew Clothing Utilizing Phosphorus-Based Fire-Retardant Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Innosense, LLC
2531 West 237th Street, Suite 127
Torrance, CA 90505-5245
(310) 530-2011

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tania Betancourt
tania.betancourt-1@innosense.us
2531 West 237th Street, Suite 127
Torrance,  CA 90505-5245
(310) 310-2011

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For maintaining U.S. leadership in space exploration, there is an urgent need to develop nonflammable crew clothing with the requirements of comfort, ease of customization, durability and nontoxicity. The objective of this Phase II project is to continue the engineering development of heat and flame-resistant crew clothing (FRECLOTM) to satisfy NASA needs. FRECLO consists of InnoSense LLC (ISL) proprietary phosphorus-containing flame-retardant (FR) formulations permanently treated on synthetic, natural or blended fabrics as well as on the readymade garments. Phase I demonstrated the NASA use potential. Upon exposure to flame, FRECLO fabrics formed a carbonaceous char layer preventing further fire or heat-induced damage to the fabric. ISL's FR treatments are devoid of halogens, making the process environmentally-friendly and eliminating toxic byproducts during combustion. In Phase II, ISL will: (1) Optimize and scale-up FRECLO treatments, (2) Fine-tune FR formulations and application methods for performance optimization, (3) Perform rigorous evaluation of the treated fabrics, and (4) Evaluate off-gassing and biocompatibility of the treated fabrics. ISL has committed $100K as Phase II co-funding and has secured $300K as Phase III follow-on funding commitment from an industrial partner for successful technology transition. Large NASA prime contractors have strongly endorsed the FR materials.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's vision for the future focuses on missions beyond the Earth's orbit to Mars and throughout the Solar System. This vision will involve long duration, manned missions for which durable, easily customizable, and non-toxic FR clothing will be very important. While inherently-nonflammable fabrics are available in the marketplace, they do not offer the desired breathability, comfort, safety, ease of customization, and wardrobe flexibility to satisfy everyday needs of NASA astronauts. NASA's Environmental Control and Life Support (ECLS) division is actively searching for new technologies to produce crew clothing to meet the following requirements: (1) Sufficient comfort and breathability for everyday use in all types of clothing pieces, and (2) Ease of customization to permit creation of clothing with various colors, textures and weights for individual preferences of the crew, and (3) Resistance to multiple cycles of machine washing and drying, which may be required for long-duration missions. The FR treatments being optimized in this project aim to satisfy these needs. FR-treated fabrics also have potential applications in upholstery, bedding, and other textiles requiring low flammability for use in space habitats and exploratory vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Flammability is a severe limitation for electronics, transportation vehicles, buildings, furniture and clothing articles. ISL's phosphorus-based FR materials can be incorporated into fabrics used in apparel, protective clothing, curtains, drapes, upholstery, bedding, carpets, tents and transportation gear (seat and wall coverings, belts, etc) for NASA and the industrial/commercial sectors. FR garments are used by firefighters, electrical workers, especially foundry workers, and military personnel. Uniforms for firefighters and high-risk military crew commonly utilize Nomex or other high performance fibers. The ability to provide the military with cost-effective alternatives would be significant. Because currently, these materials are only utilized for soldiers engaged in specialized missions at a high risk of catastrophic fire injury. ISL's FRECLO technology would meet this need. ISL's nonhalogenated FR materials will also have application as treatments for paper (e.g., stocks, bonds, wills, etc.), coatings or fillers for structural and electrical components.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Operations Concepts and Requirements
Spaceport Infrastructure and Safety
Reuseable
Thermal Insulating Materials
Airport Infrastructure and Safety
Pilot Support Systems
Biomedical and Life Support
Portable Life Support
Suits
Earth-Supplied Resource Utilization
Composites
Organics/Bio-Materials
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X2.05-9202
PHASE-1 CONTRACT NUMBER: NNX10CE43P
SUBTOPIC TITLE: Spacecraft Thermal Control Systems
PROPOSAL TITLE: Nonventing Thermal and Humidity Control for EVA Suits

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-0071
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Izenson
mgi@creare.com
P.O. Box 71
Hanover,  NH 03755-0071
(603) 603-3800

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future manned space exploration missions will require space suits with capabilities beyond the current state of the art. Portable Life Support Systems for these future space suits face daunting challenges, since they must maintain healthy and comfortable conditions inside the suit for long-duration missions while minimizing weight and venting no consumables. We propose to develop an innovative system for thermal and humidity control in a space suit that is simple, rugged, lightweight, and nonventing. In Phase I we proved the feasibility of our approach by identifying the optimal materials, developing fabrication methods, building and testing a proof-of-concept system, and demonstrating by test that its performance is suitable for use in space suit life support systems. Results from these tests agree well with our design models, which we used to produce a conceptual design for a full-size system. In Phase II we will optimize the overall design for integration with space suit systems, produce a full-size prototype, and demonstrate operation in a prototypical environment.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system can be used in any future space suit, with applications that include lunar and Mars exploration or constructing/servicing next-generation space telescopes while maintaining a clean environment. The basic technology can also be used to provide rugged, nonventing thermal and humidity control for spacecraft, manned rovers, and habitats.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are numerous commercial and military applications for the proposed technology. Commercial applications include untethered personal cooling systems for law enforcement, nuclear/chemical plant workers, and heat-sensitive multiple sclerosis patients. Military applications include personal cooling systems for soldiers or marines wearing chem/bio protective gear, body armor, EOD suits, or level-A HAZMAT suits.

TECHNOLOGY TAXONOMY MAPPING
Portable Life Support


PROPOSAL NUMBER: 09-2 X2.05-9667
PHASE-1 CONTRACT NUMBER: NNX10CE44P
SUBTOPIC TITLE: Spacecraft Thermal Control Systems
PROPOSAL TITLE: Integrated Sublimator Driven Coldplate for use in Active Thermal Control System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Paragon Space Development Corporation
3481 E. Michigan Street
Tucson, AZ 85714-2221
(520) 903-1000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Leimkuehler
tleimkuehler@paragonsdc.com
1120 NASA Parkway Suite 505
Houston,  TX 77058-3320
(281) 957-9173

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The original Sublimator Driven Coldplate (SDC) design sought to provide significant mass savings over a traditional pumped fluid loop by combining the functions of a cold plate and a sublimator and eliminating the fluid loop (Leimkuehler, et. al., "Design of a Sublimator Driven Coldplate Development Unit," 2008-01-2169). The target application was to provide heat rejection for the ascent module of the Altair lunar lander vehicle during the lunar ascent mission phase. However, in order to provide heat rejection for the ascent module during the rest of the mission, it is desirable to keep the ascent module integrated with the fluid loop in the rest of the Altair vehicle. Therefore, we propose an Integrated Sublimator Driven Coldplate (ISDC) that can function as both a standard flow-through cold plate and a Sublimator Driven Coldplate. The ISDC builds on the original SDC concept by adding coolant layers so that it can be integrated with the pumped fluid loop on the rest of the vehicle. This approach provides mass savings by (1) combining multiple pieces of hardware into a single piece of hardware and (2) providing additional fault tolerance without the need for redundant hardware.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This SBIR could directly impact the current program of record, primarily the Altair Lunar Lander; in particular the ascent module. However, other NASA applications could benefit from this research program as well. For example, the Orion Crew Exploration Vehicle may see similar benefits as those described above for Altair. Instead of an ascent module and descent module on Altair, Orion has a crew module and a service module. Just like the Altair ascent module separates from the descent module before lifting off of the lunar surface, the Orion crew module separates from the service module before re-entering Earth's atmosphere. Alternatively, if Orion evolves into an ISS lifeboat, the vehicles primary mission would be a return to Earth profile in which the Orion stages from the ISS. Because of the analogous arrangement of these modules, Orion may see similar mass and reliability benefits from an ISDC due to combining multiple functions into one piece of hardware and/or strategic location of various components between the two modules and the associated "gear ratios" for launch propellant. Due to the benefits for short duration missions, this SBIR could directly impact the upper stages of small, medium, and heavy launch vehicles as well as boost stages for high altitude orbits. In addition, many of the planned technology demonstration missions will require simple, safe, and reliable platforms in which the ISDC would assist in reducing the weight and complexity.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to NASA space vehicles, commercial space vehicles may benefit from this technology as well. Paragon has been working with a number of commercial space companies to design their thermal control systems. Due to the nature of the vehicles and their concept of operations, coldplates and sublimators almost always end up being included in these systems along with a pumped fluid loop. The same mass and reliability improvements discussed previously may potentially be applied to these commercial space vehicles as well.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Reuseable


PROPOSAL NUMBER: 09-2 X3.01-8530
PHASE-1 CONTRACT NUMBER: NNX10CE45P
SUBTOPIC TITLE: Oxygen Production from Lunar Regolith
PROPOSAL TITLE: Contaminant Robust System for Oxygen Production from Lunar and Martian Resources

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Paragon Space Development Corporation
3481 E. Michigan Street
Tucson, AZ 85714-2221
(520) 903-1000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Straus
jstraus@paragonsdc.com
3481 E Michigan Street
Tucson,  AZ 85714-2221
(520) 382-4809

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Extended duration missions to the Moon and Mars will require the use of In-situ resources to generate propellants and life support consumables. Many of the processes for in-situ resource utilization (ISRU) produce water, along with a variety of acid gases and other water soluble contaminants. Paragon proposes to develop membrane technology to separate water vapor from contaminants in the ISRU systems. The water vapor can then be processed using Paragon's demonstrated Solid Oxide Electrolysis (SOE) technology to produce pure gaseous oxygen for life support and/or propulsion. The membrane and SOE subsystem has no moving parts, require no regeneration or resupply of subcomponents over component life time, rely on only single phase physics, and work independent of gravity. In Phase 1, Paragon demonstrated the potential of the membrane technology for use in the treatment of contaminated gas streams. Preliminary results indicate that the membrane is capable of generating a purified water vapor stream by extracting it from a second stream contaminated with hydrogen chloride gas as produced in lunar ISRU systems. In Phase 2, Paragon will perform the following: (1) Confirm lunar & Martian contaminants; (2) Predict performance and derive operating conditions / interface requirements of membrane and SOE units in ISRU systems via system analyses; (3) Experimentally verify impermeability of membrane to contaminants; (4) Demonstrate membrane performance does not hinder SOE performance through integrated testing; (5) Develop / test full scale membrane unit that meets ISRU requirements; and (6) Deliver additional membrane unit to NASA. At the end of the Phase 2 effort, Paragon aims to show that the membrane is impermeable to ISRU contaminants and integrates well with SOE. The technology will be advanced to a TRL of near 4 by designing / building a full scale unit that demonstrates water extraction at requirements specific to ISRU oxygen production systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology development can be applied to ISRU oxygen production systems on both the Moon and Mars. The membrane will remove acid contaminants from a moist stream received directly from a lunar regolith hydrogen reduction reactor or Martian water ice. This contaminant-free water stream can then be delivered directly to a high temperature solid oxide electrolysis (SOE) unit to produce pure, dry oxygen for life support consumables or surface exploration / Earth return propellant. The membrane technology can also be applied to processes where water needs to be separated from methane. Specific NASA examples include down stream of Sabatier reactors used in air revitalization systems, and lunar regolith methane reduction systems. In all, the water is separated and sent to an electrolyzer to recycle hydrogen and produce oxygen as a consumable. Finally, the membrane technology can be applied in bio-waste processing to separate water vapor from a contaminated stream as a step in the overall clean up process. SOE is currently being developed as a technology for air revitalization systems, enabling 100% oxygen regeneration from human metabolic byproducts alone. As SOE can electrolyze CO2 as well as H2O, SOE can also potentially be used in other lunar regolith reduction systems that use carbon monoxide or methane as the reducing agent.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The non-NASA applications and spin off of this technology development are significant. This technology is part of Paragon's recent efforts to develop a space flight air revitalization system for commercial spacecraft. That work is partially funded through a Commercial Crew Development (CCDev) Space Act Agreement with NASA. It provides a no-moving-part water removal system that can address the spacecraft water accumulation problem without using complex condensing heat exchangers or mass- and crew- intensive desiccant. More directly related, terrestrial based applications of Solid Oxide Electrolysis (and its other function as a solid oxide fuel cell) also are threatened by contaminants such as sulfuric acid. The membrane and SOE units developed under this contact may be used in carbon sequestration and oxygen reclamation systems installed in petroleum refining plants.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 X3.01-9113
PHASE-1 CONTRACT NUMBER: NNX10CE46P
SUBTOPIC TITLE: Oxygen Production from Lunar Regolith
PROPOSAL TITLE: Novel Instrumentation for Lunar Regolith Oxygen Production Facilities

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Los Gatos Research
67 East Evelyn Avenue, Suite 3
Mountain View, CA 94041-1518
(650) 965-7772

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Douglas Baer
d.baer@lgrinc.com
67 East Evelyn Avenue, Suite 3
Mountain View,  CA 94041-1518
(650) 650-7772

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this SBIR effort, Los Gatos Research (LGR) proposes to develop, test and deploy three novel compact, rugged and easy-to-use multi-gas analysis instruments, based on tunable diode laser absorption spectrometry and a patented cavity-enhanced laser absorption-based strategy called Off-Axis Integrated Cavity Output Spectroscopy (Off-Axis ICOS), for monitoring and control of extraplanetary regolith processing and oxygen production. The instruments will also prove useful for in situ surface analysis. The first instrument (Instrument #1), based on fast extractive sampling, will record measurements of several important gas-phase constituents in regolith processing facilities with extraordinarily high sensitivity, accuracy and specificity in real time. This instrument will integrate directly into NASA's hydrogen and carbothermal reduction test facilities at Mauna Kea, Hawaii. The measurement quantities of interest include the concentrations of HF, HCl, H2S, O2, H2, CH4, CO, CO2, H2O, and H2O isotopes (H2HO or HDO and H218O). The second instrument (Instrument #2) will provide measurements of H2O concentrations and gas temperature directly in the high temperature reactive flow and prior to hydrolysis. The third instrument (Instrument #3) will provide accurate quantification of the aforementioned gases in a compact, low-power form factor suitable for integration into the Regolith and Environment Science and Oxygen and Lunar Volatile Extraction (RESOLVE) project. This analyzer will be used to study both thermal desorption and hydrogen reduction of extraplanetary regolith.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future NASA extraplanetary exploration missions will require in-situ resource utilization (ISRU) technologies to manufacture fuels, life support gases, and minerals. One of key NASA technologies involves the processing of extraplanetary regolith to produce H2O and O2. This oxygen can then be used as a propellant or for habitation. NASA requires several diagnostics to assess the validity and viability of ISRU technologies. Foremost, the final oxygen product must be analyzed to determine the trace contaminant levels. This analysis will provide information regarding the regolith composition, sorbent efficacy, and sorbent aging. Additionally, in-situ measurements of gas composition and temperature in the hot reactor or downstream of the sorbent bed are required to monitor the efficiency and dynamics of reduction process. Finally, NASA is targeting robotic lunar mission that include the Regolith and Environment Science and Oxygen and Lunar Volatile Extraction (RESOLVE) project. This project necessitates the deployment of a lightweight, low-power gas analyzer. The proposed miniature Phase II prototype can complement existing technology to provide additional and verifying data. In addition to NASA's regolith processing monitoring needs, several other NASA programs can benefit from the technologies developed in this SBIR program, including the Hypersonic Airbreathing Propulsion Branch, the NASA Astrobiology Program, and the NASA Astronaut Health Monitoring Program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Besides its application to NASA, laser-based gas analyzers also have significant commercial application. Through several strategic partnerships, LGR is developing a suite of analytical instrumentation to measure trace gases for industrial process control, energy exploration, and military applications. The proposed work is essential in making these instruments more compact, rugged, and cost competitive, and will thus enlarge the potential market size significantly.

TECHNOLOGY TAXONOMY MAPPING
Optical
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 X3.01-9415
PHASE-1 CONTRACT NUMBER: NNX10RA67P
SUBTOPIC TITLE: Oxygen Production from Lunar Regolith
PROPOSAL TITLE: Advanced Carbothermal Electric Reactor

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Orbital Technologies Corporation
Space Center, 1212 Fourier Drive
Madison, WI 53717-1961
(608) 827-5000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Gustafson
gustafsonr@orbitec.com
1212 Fourier Drive
Madison,  WI 53717-1961
(608) 229-2725

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of the Phase 1 effort was to demonstrate the technical feasibility of the Advanced Carbothermal Electric (ACE) Reactor concept. Unlike state-of-the-art carbothermal reactors that use concentrated solar energy and/or laser energy to heat the regolith, the ACE Reactor uses an innovative method to electrically heat the regolith to temperatures over 1800C within a thermally insulted environment, either with or without a crucible. Commercial high-temperature heating elements made from molybdenum disilicide (MoSi2) are designed to only operate in oxidizing atmospheres where a protective layer of silicon dioxide (SiO2) will form. In Phase 1, the ACE reactor used MoSi2 heating elements with a protective coating to allow them to operate in any type of environment (oxidizing, reducing, or vacuum). The ACE Reactor concept eliminates the problems encountered with traditional carbothermal hot-wall reactors and offers significant advantages over current carbothermal reactor approaches. By eliminating the need for a concentrated solar energy system, the ACE reactor offers a significantly lowers system mass and removes the need to keep optical surfaces clean. In addition to efficiently producing oxygen, the ACE reactor separates the processed regolith into metallic iron and a silicate glass that can be formed into structural components or shielding materials.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The purpose of ISRU is to harness and utilize resources at the site of exploration to create products and services which can enable and significantly reduce the mass, cost, and risk of near-term and long-term space exploration. In particular, the ability to make propellants, life support consumables, fuel cell reagents, and radiation shielding can significantly reduce the cost, mass, and risk of sustained human activities beyond Earth. The ACE Reactor will meet this need by efficiently producing oxygen, metallic iron and glass from regolith. The oxygen produced could satisfy the needs of EVA, life support, and propulsion applications including orbital propellant depots. The metallic iron or silicate glass could be poured into molds to make building components, radiation shielding materials, or spare parts.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of ACE reactor is clearly focused on supporting the needs of the NASA human exploration program. However, there are several commercial companies making significant progress towards spaceflight, including Bigelow Aerospace, Scaled Composites, and Space-X. There are significant cost/propulsive savings associated with obtaining oxygen from local regolith versus bringing it from Earth, and systems have been proposed to use lunar oxygen to resupply vehicles anywhere from LEO down to the lunar surface. As commercial flight systems mature, the ACE reactor could provide an economical source of oxygen. In addition, the innovative electric resistance heaters developed for the ACE reactor could have a significant commercial market as the first high-temperature heating elements that can operate in oxidizing, reducing, and/or vacuum environments.

TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 X3.02-9169
PHASE-1 CONTRACT NUMBER: NNX10CD27P
SUBTOPIC TITLE: Lunar ISRU Development and Precursor Activities
PROPOSAL TITLE: Lunar Organic Waste Reformer

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pioneer Astronautics
11111 W. 8th Avenue, Unit A
Lakewood, CO 80215-5516
(303) 980-0890

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Zubrin
zubrin@aol.com
11111 W. 8th Avenue, Unit A
Lakewood,  CO 80215-5516
(303) 303-0890

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Lunar Organic Waste Reformer (LOWR) utilizes high temperature steam reformation to convert all plastic, paper, and human waste materials into useful gases. In the LOWR, solar thermal concentrators are used to heat steam directly to 600 C, after which the steam is mixed with a small amount of oxygen and injected into a reactor which is being fed with waste materials via a lock hopper. At the high temperatures, the oxygenated steam will react with all organic materials to produce a gas mixture largely composed of hydrogen, CO and carbon dioxide. After removing the remaining steam from the product stream via condensation, the gases are dusulfurized and then fed to a catalytic reactor where they can be combined with hydrogen to produce methane, methanol, or other fuels. Both the necessary hydrogen and oxygen for the process can be produced by electrolysis of part of the water content of the waste material, which is extracted from the wastes directly by the reformer itself. With effective recycling of the steam, no consumables are lost in the process. All products are liquids or gases, making the system highly reliable and subject to automation. In the proposed Phase 2 program, Pioneer Astronautics will build a full-scale end-to-end LOWR system capable of turning 10 kg of waste per day into methane and oxygen.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The LOWR can be a key component of the lunar exploration program by allowing available power sources to enable production of oxygen and fuel on a sufficient scale to significantly reduce Lunar base logistic requirements. Depending upon the rocket propulsion and transportation system employed, the fuel produced by the LOWR from recycled waste can comprise between 50% and 100% of a fuel required to operate a lunar ascent vehicle used to transport crew from the Lunar surface to orbit. The oxygen produced can also comprise a substantial fraction of all oxidizer required by a lunar ascent vehicle system, thereby minizizing further the propellant mass that needs to be transported at great expense from Earth, or alternatively, greatly reducing the mass and power requirements of a system designed to extract oxygen from lunar regolith. Therefore, the ability to produce fuel and oxygen in quantity on the lunar surface can have a major role in reducing total program costs. The LOWR is not limited to Lunar applications. It can be used on the Martian surface, or on any long duration piloted spacecraft, including the International Space Station or any deep space crewed vehicle used for example on human missions to Near Earth asteroids or Mars. In such latter applications it offers great advantages as a means of transforming crew wastes into useful propellants that can be used to enable station keeping, mid-course corrections, or other deep space maneuvers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Lunar Organic Waste Recycler can also be a valuable tool wherever organic wastes or other low cost biomass are available for conversion to synthesis gas. Corn stover, for example, is currently available commercially in large quantities for $40/tonne. If converted into synthesis gas, each tonne of corn stover can provide enough carbon monoxide and to make about 700 kg of methanol, which at current spot market prices would sell for about $200. Methanol is currently used as a major commodity in the chemical industry and could be used a motor vehicle fuel in flex fuel cars. The LOWR could similarly be used to transform other crop and forestry residues, as well as urban paper, plastic, and metabolic wastes into synthesis gas for production of methane or liquid hydrocarbon fuels via Fischer Tropsch processes. Thus LOWR technology could become the basis for highly profitable industries which make a significant contribution towards the vital national goal of freeing the nation from its dependence on foreign oil. The LOWR can be built on a modest scale making it readily transportable by truck, ship, or airplane. This makes it ideal for use in remote locations such as military outposts or third world villages which need to obtain fuel without ready access to ordinary commercial suppliers. Methane from remotely operated LOWR-derived units could be used to generate power in on site gas turbines, for motor vehicle fuel, or for cooking or other purposes

TECHNOLOGY TAXONOMY MAPPING
Chemical
Waste Processing and Reclamation
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Biochemical Conversion
Renewable Energy


PROPOSAL NUMBER: 09-2 X4.01-8079
PHASE-1 CONTRACT NUMBER: NNX10CF04P
SUBTOPIC TITLE: Advanced Radiation Shielding Materials and Structures
PROPOSAL TITLE: Improved Metal-Polymeric Laminate Radiation Shielding

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Powdermet, Inc.
24112 Rockwell Drive
Euclid, OH 44117-1242
(216) 404-0053

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Doud
bpdoud@powdermetinc.com
24112 Rockwell Drive
Euclid,  OH 44117-1252
(216) 404-0053

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this proposed Phase II program, builds on the phase I feaibility where a multifunctional lightweight radiation shield composite was developed and fabricated. This structural radiation shielding is high strength, syntactic polymeric where the polymer is filled with high strength low Z material. The phase II program will provide radiation modeling and testing for these new structural radiation solutions as well as a physical property database for using them in space habitats. The Phase II program will address issues including flammability, attachment, and incorporation of these new materials into existing and future space habitat designs. The accumulation of the phase II program will be prototype components that can be tested at TRL level 5 or flown for TRL level 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA Commercial applications include, Radiation shielding and structural members for space craft, landers, habitat structures and satellite components.The replacement of parasitic shielding, and enabling shielding to be used in sun, electronics, and reactor exposed areas where temperatures exceed 120 C is enabled (when using high temperature matrix solutions). The primary insertion target will be the an inflatable habitat structures but ridged habitats for near term missions will be considered, where we have time to reach the required TRL level consistent with program schedules, and mars missions (electronic boxes, reactor shielding, etc.). It is imperative that any new material development be downselected in the next few years to meet even these insertion opportunities, and the lightweight structures exploratory development investment must be made today to achieve any significant return on the investment prior to mars missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-Nasa Commercial application include habitat radiation shielding for space tourism applications. There are potential structural shielding uses for this material for electronics and components for both satellite and missile structures as well. Other non aerospace applications include use as medical shielding, nuclear shielding and for radiation hardened electronics.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Erectable
Inflatable
Launch and Flight Vehicle
Spaceport Infrastructure and Safety
Thermal Insulating Materials
Radiation-Hard/Resistant Electronics
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X4.01-8309
PHASE-1 CONTRACT NUMBER: NNX10CF05P
SUBTOPIC TITLE: Advanced Radiation Shielding Materials and Structures
PROPOSAL TITLE: Multilayer Polymeric Shielding to Protect Humans from Galactic Cosmic Radiation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
International Scientific Technologies, Inc.
P.O. Box 757
Dublin, VA 24084-0757
(540) 633-1424

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Churchill
intlsci@earthlink.net
P.O. Box 757
Dublin,  VA 24084-0757
(540) 633-1424

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In Sub-topic X4.01, NASA has identified a need for advanced radiation-shielding materials and structures to protect humans from the hazards of galactic cosmic radiation (GCR) and Solar Energetic Particles (SEP) on long-duration missions, outside the earth's magnetosphere. The radiation species of greatest interest are light ions (particularly protons), heavy ions (such as iron-56) and neutrons. International Scientific Technologies, Inc., in conjunction with the College of William and Mary, in its Phase I program developed lightweight, multi-layered, polymeric shielding against GCR and SEP. The Phase II objectives include analysis and design of single and multi-layered nanocomposite polymeric radiation shields using OLTARIS modeling protocols to supplement the empirical results of Phase I, fabrication of nanocomposite films and multi-layered structures, acquisition of families of test data to determine key parameters of single and multi-layered structures tailored to stopping GCR and SEP, optimization of prototype multi-layered polymeric shields using statistical design and OLTARIS modeling for a range of manned and unmanned NASA applications prior to commercialization in Phase III. The anticipated result of the Phase I and Phase II programs is the development of multi-layered shields with an outer layer of hydrogenous polymeric material for significant dose reduction of incident GCR ions and inner layers of polymeric composites containing additives chosen to moderate and absorb neutrons resulting from fragmentation of incoming heavy ions and to absorb short wavelength electromagnetic radiation resulting from the slowing of the GCR particles and capture of neutrons. The Technology Readiness Level (TRL) at the beginning of Phase II is 4. At the end of Phase II, the TRL will be 5.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed multilayered multifunctional high performance polymers, films, coatings and additives will find application in NASA missions in protecting astronauts and sensitive optical, electronic, thermal and acoustic components from space hazards, including radiation, dust and thermal transients, while, at the same time, providing lightweight structures for planetary rovers and habitats. It is expected that these multi-layered systems will provide a high-performance-to-weight radiation shield that can be used within human habitats, spacecraft and protective apparel. Other missions supported by NASA could also make use of the multifunctional materials for the International Space Station or in other orbiting vehicles involving long-duration small dose exposure.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Lightweight multifunctional radiation shielding will find application in the commercial (e.g., hospitals and nuclear power plants) and defense (e.g., nuclear-powered ships and surveillance satellites) sectors. The shields will provide protection for homeland security first responders employed by law enforcement agencies, fire departments and hospitals. It is also expected that the shielding can be fabricated into temporary shelters used by defense personnel and considered for use in the protection of individuals in case of nuclear or radiological events. The radiation-shielding material will be suitable for fabrication into protective clothing for healthcare professionals involved in X-ray and nuclear medicine.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Inflatable
Launch and Flight Vehicle
Thermal Insulating Materials
Manned-Maneuvering Units
Suits
Composites
Radiation Shielding Materials
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X4.02-8435
PHASE-1 CONTRACT NUMBER: NNX10CF09P
SUBTOPIC TITLE: Expandable Structures
PROPOSAL TITLE: Expandable/Foldable Structures for Habitat

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Folded Structures Company, LLC
1142a Old York Road
Ringoes, NJ 08551-1045
(908) 237-1955

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Daniel Kling
dkling@foldedstructures.com
1142a Old York Road
Ringoes,  NJ 08551-1045
(908) 237-1955

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Folded Structures Company (FSC) has developed an innovative design approach for multi-laminate, primary and secondary structures for planetary habitats that integrates the dynamic deployment means with the static structural design using an advanced mathematical folding theory. The design approach holds the promise of a much simpler expandable structure that is both lightweight and compactable (low delivery volume) and yet capable of extending into an expansive volume. FSC research supports the utilization of a new class of deployable, space-based structures that utilize an advanced folding methodology as the primary engineering and assembly method combined with the use of both single and multi-laminate sheet materials. The proprietary patterning algorithms create tessellations for planar sheets that articulate dynamically on the edges of the tessellation allowing for uniform deployment across the entire sheet. Previous to the development of these algorithms, there was no general system for generating doubly periodic folded structures. Based on results from a previous NASA SBIR project, FSC will apply its proprietary folding techniques and software to the broad topic of expandable habitat structures. The Phase I project has resulted in a design concept for the expandable bladder section of the proposed lunar habitat that also integrates the flooring into a single deployable structure.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The innovative folding method will make possible a technical break-through in tessellated architectures for expandable structures for planetary habitat applications. The new technology offers diverse capacity to design, manufacture, and self-assemble doubly periodically folded sheet material into structures that are lighter and more compactable than provided by current engineering practices. Some space-based applications include solar arrays, parabolic reflectors, sun and radiation shielding and extendable masts and booms. In addition to inflatable architectures, other strategies (including solar heating/radiation, elastic memory, and mechanical force) can be employed for self-activating and sustaining the unfolding process.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Material folding lends itself to a number of applications from very sophisticated (aerospace) to the ordinary such as packaging materials. Kraft paper cores based on the folding techniques could yield a superior product to corrugated cardboard. Multi-layer blocks made from recyclable materials could replace Styrofoam for use in space filling and shock absorbing. For aerospace using aluminum or composite materials, the folded structures could improve upon the existing honeycomb cores, which are used throughout the airplane in the floors, luggage compartments, and wings. For the transportation industry, aluminum or steel folded tessellations in flat laminated panels could be used for high strength but lightweight truck beds. Folded materials could be specifically designed for automobile floors to give a resilient strength to the frame while also serving to dampen the overall vibrations of the automobile. The lightweight strength and energy absorbing properties are also suited for bumpers, hoods, and crash protecting car doors. On highways, new crash barriers may be possible because of their low cost and high-energy absorption.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Inflatable
Kinematic-Deployable
Composites
Radiation Shielding Materials


PROPOSAL NUMBER: 09-2 X4.02-9611
PHASE-1 CONTRACT NUMBER: NNX10RA76P
SUBTOPIC TITLE: Expandable Structures
PROPOSAL TITLE: Self-Deploying, Composite Habitats

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
2750 Indian Ripple Road
Dayton, OH 45440-3638
(937) 320-1877

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Hermiller
hermillerjm@crgrp.com
2750 Indian Ripple Road
Dayton,  OH 45440-3638
(937) 320-1877

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cornerstone Research Group, Inc. (CRG), proposes to develop self-deploying, composite structures for lunar habitats, based on CRG's Veritex(TM) materials. These structures will provide a rigid, durable habitat that will reduce the risk of mechanical failure due to crew or environmentally induced damage compared with inflatable structures that are more susceptible to punctures and damage from micrometeoroid impacts. Veritex is a composite material consisting of common reinforcement fibers, such as e-glass, carbon, Kevlar(R), or high-strain capable fabrics, and one of CRG's shape memory polymers (SMP). Veritex materials will return to a memorized shape when raised above a specific activation temperature. This unique feature enables the use of Veritex(TM) as a primary lunar structure for its predictability and repeatability, which will offer quick, self-deploying lunar habitat that can return to a rigid enclosure after the deployment process. The development of expanding composite habitats will offer increased packing efficiency compared with fully rigid structures that lack expandable characteristics and waste valuable cargo space. This habitation structures technology will achieved Technology Readiness Level (TRL) 4 during Phase 1 with proof-of-concept feasibility studies and will achieve a TRL of 5 during Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Supporting NASA's Exploration Systems Mission Directorate, this project's technologies directly address requirements for expanding habitation systems for multi-gravity environments (micro and reduced gravity), multi-use work stations, and long duration, deep-space habitats. This project's technologies offer significant volume reduction potential that will utilize storage volume more efficiently in transit to its destination. The self-deploying habitat will also minimize manual labor required by astronauts during the deployment process.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This project's technologies developed for NASA systems would directly apply to systems operated by other government and commercial enterprises. In addition to space applications, the self-deployable structures could be used in various terrestrial commercial markets such as for semi-permanent shelters, emergency and relief shelters, deployable research facilities in extreme environments and mothballing and long-term storage of naval vessels and military equipment, such as aircraft, and potentially armor and artillery. Government systems that would derive the same benefits would include, but not be limited to, uninhabited space structures, barracks, mess halls, and operation centers operated by the Department of Defense.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Inflatable
Kinematic-Deployable
Modular Interconnects
Structural Modeling and Tools
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X4.02-9770
PHASE-1 CONTRACT NUMBER: NNX10CF10P
SUBTOPIC TITLE: Expandable Structures
PROPOSAL TITLE: Verification and Validation of an Innovative Inflatable Structure

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Paragon Space Development Corporation
3481 E. Michigan Street
Tucson, AZ 85714-2221
(520) 903-1000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Harrell
jharrell@paragonsdc.com
3481 E Michigan Street
Tucson,  AZ 85714-2221
(520) 382-4842

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An inflatable habitat is a pressure vessel with flexible shell. Notable features such as low weight, large inflated operational volume, and small pre-deployment volume offer significant advantages over traditional rigid metallic and composite habitat structures. Conventional designs suffer from indeterminacy of load sharing between meridional and circumferential members as well as the internally rigid metal support structure. The designs must functionally index the meridional and circumferential members to one another to minimize sensitivity to manufacturing, handling and operational trauma, all the while maintaining their independent load carrying roles. This design process results in oversized members to account for load uncertainties and substantially increases the handling, manufacturing, and integration risks. The unique Ultra High Performance Vessel (UHPV) technology provides the solution to the design and manufacture of robust inflatable structures with exceptional accuracy and dimensional stability. UHPV technology provides high shell load containment architecture with fully determinate load pathways that can be modeled mathematically. The lightweight, low cost inflatable fabric structure, consisting of barrier film layers, carrier cloth containment layers, and pressure restraint tendons can be designed and fabricated to provide an accurate geometry without the need for an internal skeletal frame. Eliminating the need for a rigid internal load-bearing frame allows the collapsed inflatable to be packaged in the smallest possible volume. To bring this innovative inflatable design to use for surface habitats, airlocks and myriad other space environment and containment applications, a verification and validation plan using both testing and predictive analytical models is proposed to conclusively demonstrate that the fully load-determinate UHPV can meet all structural design requirements thereby allowing for decreased mass and risk.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The potential post NASA applications are lunar/ Martian surface system habitats, airlocks and other crewed vessels, deployable antenna reflectors and radiators, solar collectors, solar sails, payload fairings, water storage tanks, cryogenic propellant tanks, greenhouse enclosures, debris shields, radiation shields, re-entry vehicles, large telescopes, propellant depots, rover vehicles, orbital debris removal systems, emergency escape vehicle (ISS), and Martian air ships.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential Non-NASA commercial applications are air bags, high altitude air ships, aerostats, compressed air energy storage. underwater habitat, underwater emergency escape system (submarine), portable storage tanks for oil transport, remote fuel depot stations, remote water storage tanks for forest fire control, cargo lift balloons, large, deep space antenna reflector for ground stations, antenna radome, emergency shelters, and troop shelters with integrated ballistic protection.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Airlocks/Environmental Interfaces
Inflatable
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Structural Modeling and Tools
Composites
Computational Materials


PROPOSAL NUMBER: 09-2 X4.03-8928
PHASE-1 CONTRACT NUMBER: NNX10CD85P
SUBTOPIC TITLE: Low Temperature Mechanisms
PROPOSAL TITLE: Lightweight High Efficiency Electric Motors and Actuators for Low Temperature Mobility and Robotics Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
QM Power, Inc.
4747 Troost Avenue, Suite 11
Kansas City, MO 64110-1727
(857) 350-3100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Charles Flynn
jflynn@qmpower.com
4747 Troost Avenue, Suite 11
Kansas City,  MO 64110-1727
(816) 235-5054

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
QM Power will build and empirically test Space and Cryogenic qualified preproduction Parallel Magnetic Circuit [PMC] 1-5 HP motor/actuators with electronic controllers. These preproduction prototypes will demonstrate lower operating power requirements for cryogenic motor/actuator components used in Space applications. PMC is an enabling technology having a broader peak power and high efficiency range than incumbent solutions for prime mover and dynamic suspensions used in space rovers and actuation in robotic systems. The PMC motors/actuators and electronic controllers to be built and empirically tested are those identified through the extensive modeling and analysis performed during the execution of QM Power's NASA Phase I contract NNX10CD85P demonstrating power densities greater than 0.050KW/lb with efficiencies greater than 90%. These PMC motor/actuator prototypes will undergo extensive testing in cryogenic and vacuum environments measuring performance, structural integrity, space radiation tolerance, and low out gassing. The prototypes will be optimized for manufacturing production under a Phase III effort for commercialization.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
PMC motor and actuators could be an enabling solution in virtually any space application where an electro-mechanical function is required. These could include but not be limited to propulsion and power, vehicle systems program, revolutionary aeropropulsion concepts, alternate energy foundation technologies, subsonic propulsion, lunar landers and rovers, servo positioning robotic actuators, thrust vector control actuators, fuel valve control actuators, solar array deployment, control moment gyroscopes, gimbal positioning, optic drives, open loop micropositioning, timer switching, space telescopes, cryogenic storage and transport and many others.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
QM Power is evaluating the commercialization of this technology in ambient temperature conditions for commercial refrigeration, wind and hydro renewable power generation, industrial motors, aerospace and military applications, power tools, electric or hybrid electric vehicles, non-renewable power generation, HVAC, linear actuators/pumps/clamps and a variety of other stand-alone applications.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Mobility
Manipulation
Launch and Flight Vehicle
Large Antennas and Telescopes
Guidance, Navigation, and Control
Fluid Storage and Handling
Instrumentation
Manned-Maneuvering Units
Tools
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Superconductors and Magnetic
Power Management and Distribution
Renewable Energy


PROPOSAL NUMBER: 09-2 X5.01-8081
PHASE-1 CONTRACT NUMBER: NNX10RA68P
SUBTOPIC TITLE: Composite Structures - Practical Monitoring and NDE for Composite Structures
PROPOSAL TITLE: Passive Wireless Temperature Sensors with Enhanced Sensitivity and Range

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Sensor Research & Development Corporation
1195 Baltimore-Annapolis Blvd., Unit #2
Arnold, MD 21012-1815
(410) 544-4664

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Leland Solie
leesolie@asrdcorp.com
1195 Baltimore Annapolis Blvd, Unit 2
Arnold,  MD 21012-1815
(410) 544-4664

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the development of a wireless multisensor system for NASA application to remote wireless sensing of temperature distributions in composite overwrapped pressure vessels (COPVs) and development flight instrumentation (DFI) for test facilities for large area composite component validation testing. Phase 1 demonstrated ASR&D's ability to produce temperature sensors with sensitivity controlled by device design, and to selectively read any one coded wireless sensor out of a set of up to 32 uniquely identifiable sensors. Phase 2 will further develop these passive wireless sensors for target applications, and will develop a miniaturized wireless electronic reader capable of autonomously reading up to 32 sensors operating simultaneously within its field of view. ASR&D has teamed with Metis Design Corporation for the Phase 2 electronics integration, miniaturization, and DAQ hardware development. After the Phase 1 program, the sensors and selected portions of the wireless reader are TRL 2-3. At the completion of the Phase 2 effort ASR&D will deliver to NASA a complete wireless multisensor temperature measurement system suitable for field testing (TRL 4+), including one wireless reader and 32 individually identifiable temperature sensors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application for the proposed sensor system would be the distributed wireless measurement of temperature as DFI for large area composite validation testing in facilities such as the thermal vacuum chamber (Plumbrook Facility), within cryogenic (and other) storage tanks, and around the vehicle during launch (with some sensors expendable). Numerous small, passive, lightweight sensors could be mounted in locations throughout the area to be monitored, and wireless reader systems could quickly scan through the sensors in their field of view, providing real-time temperature distribution information. Tanks would require only one tank feed-through for the antenna, minimizing heat transfer.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Identified commercial applications for the proposed sensor system include monitoring temperature in motors, gear boxes, and other hard to access locations in heavy industrial equipment, fixed wing aircraft, and rotorcraft. Vehicle health monitoring systems being developed utilize sensor data to predict component lifetime, detect incipient failure, and trim maintenance costs by reducing inspections and unnecessary component removal and replacement. Measurement of temperature is one key parameter measured in VHM systems, and ASR&D is discussing further development of the proposed technology with a major aerospace firm. Additional potential applications exist in down-hole drilling, military equipment, landfill monitoring, and civil infrastructure monitoring.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Inflatable
Launch and Flight Vehicle
Structural Modeling and Tools
Tankage
Sensor Webs/Distributed Sensors


PROPOSAL NUMBER: 09-2 X5.01-8105
PHASE-1 CONTRACT NUMBER: NNX10CE47P
SUBTOPIC TITLE: Composite Structures - Practical Monitoring and NDE for Composite Structures
PROPOSAL TITLE: Frequency Steered Acoustic Transducer

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Genziko, Inc.
3070 Windward Plaza, Suite F-275
Alpharetta, GA 30005-8782
(678) 297-0484

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Craig Near
craig.near@genziko.com
3070 Windward Plaza, Suite F-275
Alpharetta,  GA 30005-8782
(678) 558-7540

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research Phase II project is to fabricate, characterize, and verify performance of a new type of frequency steered acoustic transducer (FSAT) for structural health monitoring for impacts and leaks in aerospace structures. FSATs will be demonstrated both in the laboratory and on relevant NASA structure. Testing would be performed on both simple and complex parts. Multiple receivers would be tested to develop incoming signal analysis, angular distribution mapping, and source detection and localization. In addition, Genziko will evaluate the suitability of its integration into a wireless system, using a micro power generator and RF transceiver.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This Small Business Innovation Research Phase II project will allow the integrated vehicle health management or structural health monitoring of impacts and leakage of numerous NASA structures including airframes, airlocks, vehicles, space structures, spaceport infrastructure, fairings, and pressure vessels.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This Small Business Innovation Research Phase II project will allow commercial structural health monitoring, nondestructive evaluation, and leakage detection applications are numerous including pipelines, dams, levees, tanks, oil wells and rigs, industrial and biomedical equipment, and even HVAC equipment. In addition, FSAT may have benefits for other applications ranging from steered sonar to ultrasonic flow measurement to ultrasonic processing and characterization.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Airlocks/Environmental Interfaces
Launch and Flight Vehicle
Spaceport Infrastructure and Safety
Modular Interconnects
Tankage
Sensor Webs/Distributed Sensors
Ceramics
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X5.01-8826
PHASE-1 CONTRACT NUMBER: NNX10CE50P
SUBTOPIC TITLE: Composite Structures - Practical Monitoring and NDE for Composite Structures
PROPOSAL TITLE: Composite Structure Monitoring using Direct Write Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MesoScribe Technologies, Inc.
7 Flowerfield, Suite 28
St. James, NY 11780-1514
(631) 686-5710

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Smith
wsmith@mesoscribe.com
5445 Oceanus Drive
Huntington Beach,  CA 92649-1007
(714) 894-8400

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This NASA SBIR Phase II project seeks to develop and demonstrate a suite of sensor products to monitor the health of composite structures. Sensors will be made using the Companys Direct Write process based on Mesoplasma? deposition technology. This allows a wide variety of sensor materials and architectures to be deposited onto conformal components made from polymer composite, metallic, and ceramic materials. Sensors include strain gages, thermocouples, piezoelectric devices, damage detection systems along with shielded conductors and passive circuit components. Improving the compatibility of the Direct Write Process with advanced composites is essential for transitioning the technologies to NASA platforms. A principal objective is to demonstrate operability of Direct Write sensors under environmental conditions that may be expected on a NASA mission for which composite monitoring is necessary. Instrumented structures will be exposed to cryogenic and high temperature environments as well as requisite mechanical loading as anticipated in operation. Sensors will demonstrate their diagnostic capability and compatibility with existing data acquisition and health management infrastructure for NASA applications of interest. Furthermore, reducing cumbersome leadwire bundles through integrated wiring or passive wireless sensing approaches will make Direct Write technology an even more suitable solution for integrated health and condition monitoring.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed Direct Write sensors are applicable for both low temperature and high temperature (beyond 1500K) applications. NASA has a need for integrated vehicle health management capabilities for a number of space structures and systems. The technology development enables applications involving high temperature composite structures, instrumentation of inflatable space structures, cryogenic pressure vessels, and high temperature thermal protection systems. MesoScribes focus is the diagnostic sensing component of health management, providing innovative, deployable solutions for monitoring temperature, heat flux, deformation and structural integrity, wear, damage, and even aerodynamic properties. Applications for thermal and flow monitoring using these embedded sensors include measuring component temperature; insulation and heat shield integrity; blowby detection; and heat flux measurement. Applications for mechanical sensors include health monitoring, strain monitoring for pressurized tanks; launch load measurement; payload shock detection and measurement; and measuring deformation of shape-sensitive space structures e.g., telescopes, antennas.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications for composite instrumentation are extensive and diverse. Direct Write sensors have generated significant interest for military use within manned air vehicles, UAVs, rotorcraft, and armored transport vehicles. Applications include damage detection, vibration monitoring, gas turbine engine component monitoring, flight control, SIGINT, and communications. Next generation aircraft such as the Boeing 787 use composite materials for a number of critical structures. Monitoring of these structures is of considerable interest to the manufacturers and operators of these aircraft, particularly as neither have experience fielding such extensively composite-based systems over the timescales on which these aircraft are expected to be in service. Other applications include fuel cells for automotive applications, high speed rail, long term monitoring of infrastructure (bridges, tunnels), and certainly health management of existing commercial aerospace structures.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Ablatives
Control Instrumentation
Airframe
Controls-Structures Interaction (CSI)
Erectable
Inflatable
Kinematic-Deployable
Launch and Flight Vehicle
Operations Concepts and Requirements
Testing Facilities
Testing Requirements and Architectures
Large Antennas and Telescopes
Cooling
Reuseable
Thermal Insulating Materials
Modular Interconnects
Tankage
Feed System Components
On-Board Computing and Data Management
Autonomous Control and Monitoring
Instrumentation
Data Acquisition and End-to-End-Management
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Ceramics
Composites
Metallics
Radiation Shielding Materials
Multifunctional/Smart Materials
Power Management and Distribution
Wireless Distribution
Aircraft Engines


PROPOSAL NUMBER: 09-2 X5.02-8504
PHASE-1 CONTRACT NUMBER: NNX10CF11P
SUBTOPIC TITLE: Composite Structures - Cryotanks
PROPOSAL TITLE: Functionalized Graphene Sheets-Polymer Based Nanocomposite for Cryotanks

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nanotrons
12A Cabot Road
Woburn, MA 01801-1003
(781) 935-1200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Je Kyun Lee
jlee@agiltron.com
12A Cabot Rd
Woburn,  MA 01801-1003
(781) 935-1200

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In order to meet NASA's vision to develop sustainable and affordable solar system exploration strategies, NASA seeks advanced high-strength and high-toughness composite materials with the microcrack resistance at cryogenic temperatures. These materials must be suitable for use in fuel containment of liquid oxygen, hydrogen, and methane. The objective of this SBIR project is to develop advanced high microcrack-resistant composite cryotanks. In Phase I we successfully demonstrated the synthesis of functionalized graphene sheet (FGS) nanofillers in large scale, which exhibited significantly increased resin strength and toughness at both room and low temperatures, and reduced coefficient of thermal expansion (CTE). The further investigation of nanocomposite formulation and composite processing can result in FGS-polymer nanocomposite based carbon fiber reinforced polymer (CFRP) composites with significantly enhanced microcrack resistance at cryogenic temperatures in ways it has never done before. The new nanocomposite based CFRP composite materials also provide additional advantages in forming an impermeable barrier to gas and liquid molecules ideal for fuel tanks. Nanotrons' proposed new multifunctional nanocomposite based CFRP composite cryotanks will replace the currently used aluminum-lithium cryotanks providing significant weight savings and can be economically manufactured.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed composite material will demonstrate excellent multifunctional performance and durability at extreme environments reducing the weight of aeronautic and aerospace vehicle components. Decreasing the weight of a vehicle while improving materials performance will improve vehicle fuel efficiency and safety. The composite materials would be potentially applicable to EDS propellant tanks, Altair propellant tanks, lunar cryogenic storage tanks, Ares V tanks, and satellite propellant tanks. Other space and aerospace applications which require highly tough, low CTE composite matrixes may include space and aerospace structure and engine components and turbine.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed composite material will demonstrate excellent multifunctional performance and durability at extreme environments reducing the weight of aeronautic and aerospace vehicle components. Decreasing the weight of a vehicle while improving materials performance will improve vehicle fuel efficiency and safety. The composite materials would be potentially applicable to EDS propellant tanks, Altair propellant tanks, lunar cryogenic storage tanks, Ares V tanks, and satellite propellant tanks. Other space and aerospace applications which require highly tough, low CTE composite matrixes may include space and aerospace structure and engine components and turbine.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Tankage
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X5.03-8372
PHASE-1 CONTRACT NUMBER: NNX10RA79P
SUBTOPIC TITLE: Composite Structures - Manufacturing
PROPOSAL TITLE: Multifunctional Metal Matrix Composite Filament Wound Tank Liners

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Touchstone Research Laboratory, Ltd.
The Millennium Centre, 1142 Middle Creek Road
Triadelphia, WV 26059-1139
(304) 547-5800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Gordon
blg@trl.com
Touchstone Research Lab, Millennium Centre, 1142 Middle Cree
Triadelphia,  WV 26059-1139
(304) 547-5800

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Composite Overwrapped Pressure Vessels (COPVs) are used for storing pressurized gases on board spacecraft when mass saving is a key requirement. All future mass critical space applications will be designed to use COPVs to minimize vehicle mass. Saving mass is critical for facilitating deep space travel in which a series of space depots will be implemented as a means of providing fuel along the journey. These depots will require a means for long-term storage of fuel and other resources that can be placed in the appropriate locations ahead of time. Metal Matrix Composite (MMC) materials offer tremendous potential for lightweight propellant and pressurant tankage. Touchstone teamed with Carleton Technologies Inc. (a subsidiary of Cobham) to demonstrate feasibility of this technology in Phase I. A COPV with Al MMC liner was designed and a demonstration liner was produced. The proposed Phase II effort will address key technical risk items identified in Phase I, optimize the liner design and process, and extend the Technology Readiness Level to 5 by completing validation testing on a full-scale COPV demonstration article.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed project will provide advanced development of a new MMC technology for specific application to lightweight storage of pressurants for chemical propulsion systems. This same processing technology could help overcome technical hurdles in the areas of lightweight cryogenic tanks, ducting, and payload bays for space vehicles. Other applications include fairings, intertank structures, and truss members for both reusable and expendable launch vehicles. The Mechanics and Durability Branch at NASA Langley has also expressed interest in using the MMC prepreg tape technology in advanced aerodynamic and structures technologies for subsonic transport air vehicles, specifically for selectively reinforcing aircraft skins to obtain aeroelastic tailorability. Other aircraft structures such as stiffeners, wing skins, and wing spar caps could also be manufactured out of MetPreg.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This innovative technology will be useful in a broad spectrum of commercial applications ? wherever strength-to-weight performance is crucial, especially at elevated and/or cryogenic temperatures. Specific applications in the automotive market sector include selectively reinforced aluminum and magnesium castings, flywheels for hybrid vehicles, liners for lightweight composite tanks used on alternative fuel vehicles, and other types of storage tanks. This technology could also make its way into the sporting goods market incorporated into golf club shafts, tennis rackets, and bicycle frames. Touchstone has conducted preliminary discussions with True Temper Sports, the world's largest manufacturer of golf shafts. The proposed work will move the technology closer to a point to be tailored to meet the technical and manufacturing requirements for golf club shafts.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Tankage
Fluid Storage and Handling
Composites
Metallics
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X5.03-9295
PHASE-1 CONTRACT NUMBER: NNX10CF30P
SUBTOPIC TITLE: Composite Structures - Manufacturing
PROPOSAL TITLE: Smart Tooling for Manufacturing Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
2750 Indian Ripple Road
Dayton, OH 45440-3638
(937) 320-1877

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joel Everhart
everhartjj@crgrp.com
2750 Indian Ripple Road
Dayton,  OH 45440-3638
(937) 320-1877

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
CRG's shape memory polymer (SMP) tooling technologies, Smart Tooling, offer cutting-edge manufacturing solutions that can meet the construction needs of all future composite platforms and systems. Development and implementation of Smart Tooling, Smart Mandrels and SMP Bladders, offers end users significant opportunities to save direct expense for tooling cost and manufacturing labor to fabricate complex geometry and trapped composites. CRG's concept for a high temperature mandrel product is to leverage a proven Smart Mandrel process and replace the current material system with a novel SMP capable of remaining rigid at the 350 F laminate cure temperatures then softening following cure for extraction.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
CRG has identified multiple composite applications that stand to benefit from integration of Smart Tooling into the fabrication process. These composites include stringer stiffened skins, composite fairings, ducts, and tanks. In addition to these applications the demonstration of a high temperature Smart Mandrel product will result in the products applicability to large dry structures such as the Ares main body.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Applications of Smart Tooling to non-NASA applications includes primary aerospace structures, automotive components and body panels, structural architecture applications, wind energy, and others. CRG has had success selling the Smart Tooling product line to these industries as demonstrated by a total of 20 million dollars in sales over the last 4 years.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Composites


PROPOSAL NUMBER: 09-2 X5.03-9388
PHASE-1 CONTRACT NUMBER: NNX10CF32P
SUBTOPIC TITLE: Composite Structures - Manufacturing
PROPOSAL TITLE: Long Out-time, Out-of-Autoclave Cure Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Poleramic, Inc.
6166 Egret Court
Benicia, CA 94510-1269
(707) 747-6738

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Hayes
hayesb1@sbcglobal.net
6166 Egret Court
Benicia,  CA 94510-1269
(707) 707-6738

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As the size of composite parts exceed that of even the largest autoclaves, new out-of-autoclave processes and materials are necessary to achieve the same level of performance as autoclave cured composites. Many of the new out-of-autoclave prepreg systems can be used to manufacture high quality composites initially but the lay-up time for producing quality parts is limited by the short shelf-life at ambient conditions. The resin advancement, due to long lay-up times, commonly causes variations in fiber volume and higher void content in the cured structures. Also, current out-of-autoclave prepreg systems do not provide the same level of performance, especially damage tolerance, as many current autoclave cured prepreg systems. It is the objective of this work to develop a matrix and prepreg system for out-of-autoclave processing that possesses a year plus shelf-life while also providing an excellent balance of composite properties and damage tolerance. As an additional functionality, the out-of-autoclave prepreg system will be developed to have inherent skin-core self adhesive characteristics so that film adhesives may not be required for designs with honeycomb structures. It is expected that the TRL will be 6 at the end of this Phase 2 program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The successful completion of this research program will enable the development of high quality large composite structures that are produced out-of-autoclave and require long lay-up times. The utilization of this out-of-autoclave prepreg material was initially targeted for NASA Ares launch vehicle structures but other NASA applications could benefit from this technology as related to the topic "Low Cost and Reliable Access to Space" LCRAS. There are many cost advantages that will result from this specific technology for producing high performance composites including no autoclave capital equipment or consumables, no freezer storage (year plus shelf-life at ambient temperature), more damage tolerant structures (less repairs), and the possibility of no film adhesives required for honeycomb structures (lower weight and cost). This material may also find use in out-of-autoclave cryotank development.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Opportunities for this material may be found in commercial, defense, and civilian aircraft and helicopter applications that are trying to reduce material and processing costs of composite structures. Specific applications may be found in primary and secondary structures including fuselage, wing structures, fairings, engine core-cowl, and rotor blades. In comparison to current out-of-autoclave prepreg materials, the new technology will provide the avenue for development of much larger composite structures, requiring longer lay-up times, and with higher damage tolerance. The material system will also enable the development of lower cost honeycomb composite structures due to the advantage of inherent skin-core self adhesive properties. Applications may follow for lower temperature cure systems in the manufacturing of composite marine vessels and ships due to the large structures and long lay-up times.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Airframe
Launch and Flight Vehicle
Large Antennas and Telescopes
Tankage
Fluid Storage and Handling
Composites
Organics/Bio-Materials
Multifunctional/Smart Materials
Aircraft Engines


PROPOSAL NUMBER: 09-2 X5.03-9578
PHASE-1 CONTRACT NUMBER: NNX10CF33P
SUBTOPIC TITLE: Composite Structures - Manufacturing
PROPOSAL TITLE: Drastic Improvements in Bonding of Fiber Reinforced Multifunctional Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Integrated Micro Sensors, Inc.
10814 Atwell Drive
Houston, TX 77096-4934
(713) 748-7926

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Starikov
dstarikov@imsensors.com
10814 Atwell Drive
Houston,  TX 77096-4934
(713) 713-7926

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Achievement of a dramatic increase in the bond strength in the adhesive and composite/adhesive interfaces of existing fiber reinforced composite material joints and structures suitable for various NASA applications is the main goal of this project. The proposed technology developed at Integrated Micro Sensors Inc is based on laser-assisted fabrication of Micro Column Arrays (MCA) on the surface of the two materials prior to bonding. There are several advantages of the MCA technology in the drastic improvement of any bond: (i) mechanical strength increases due to interlocking of the adhesive or brazing material between micro columns, (ii) the bond strength increases due to the increase of the specific surface area by more than an order of magnitude, (iii) stability increases due to the inherent elasticity of the micro cones during a deformation, (iv) increase in the bond durability because of the repeated bend contours of the surface preventing hydrothermal failure, (v) wettability of the material surface significantly improves due to the highly developed surface morphology at the micro and submicron level and changes in local chemistry as a result of surface oxidation. Based on the feasibility proven in the Phase I project, this Phase II project will focus on implementation of the proposed technology for newest materials developed up to date and scaling of the proposed technology to large area and complex shape FRP composite structural joints. The investigation of the approach based on using the bond interface electrical properties for joint health monitoring initiated in the Phase I project, will be further developed into viable transducer device concepts.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Aerospace applications require novel and reliable material systems and structures to meet the increasing requirements of innovative designs. Lightweight composite materials have a high potential for applications in the areas of increased payload, reduced costs, and better survivability. Subsonic, supersonic, and especially hypersonic thrusts pose an extraordinary challenge for structures and materials. The airframe and engine require lightweight, materials and structural configurations that can withstand the extreme environment of the flight. One of the very important issues in the aerospace industry is bonding of dissimilar materials, since high bond resistance to high and rapid thermal and mechanical loads is required. Composite materials have very different coefficients of thermal expansion. In addition, structural properties and thermal conductivities are different too, which actually adds to the problem. Aerothermic heating, and high mechanical loads caused by ultra-high speeds, is one area of intensive research targeted by the current project.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The MCA technology is efficient, highly reproducible, environmentally safe, and can be applied virtually to any solid state material. In addition, the MCA technology is highly scalable to large areas and minimum processing times, as the MCA fabrication efficiency is proportional only to the average laser power. Lasers with average powers up to 5 kW are currently commercially available. In addition, precise CNC systems are currently available for providing the MCA fabrication process on curved and complex shape parts. As a result the MCA application range will expand to any area where reliable bonding between to materials is required. Such areas can include medical applications (dentistry and bone surgery), sport gear (golf and hockey clubs, boats), automobile (lighter and stronger parts), etc.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Thermal Insulating Materials
Structural Modeling and Tools
Ceramics
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X6.01-8031
PHASE-1 CONTRACT NUMBER: NNX10CE53P
SUBTOPIC TITLE: Robotic Systems for Human Exploration
PROPOSAL TITLE: Advanced Modeling Tools for Controlling Complex Assets Across Time Delay

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TRACLabs, Inc.
100 N.E. Loop 410, Suite 520
San Antonio, TX 78216-4727
(210) 822-2310

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Burridge
burridge@traclabs.com
100 N.E. Loop 410, Suite 520
San Antonio,  TX 78216-4727
(281) 281-7884

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is a hybrid simulation module to replace the current "Behavioral Sim" in JSC's Predictive Interactive Graphical Interface (PIGI). PIGI helps an operator compensate for lunar-scale time delay, and is part of NASA's "RAPID Workbench". The Behavioral Sim acts as an oracle, taking initial conditions and a sequence of commands and producing trajectories and expected final location of the robot. We propose to provide functionality to extend PIGI to manipulation activities. This includes modeling the robot's manipulation and perception capabilities and its environment. We will use NASA's R2 robot operating on ISS as our test case.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lunar Surface Systems (LSS). This program is developing concepts for lunar habitation and robotics infrastructure. Hardware testbeds such as the Habitat Demonstration Unit (HDU) and the Lunar Electric Rover (LER) are being produced and tested in analog environments. Our work will flow immediately into these tests, greatly enhancing remote commanding capabilities across time delay. LSS contacts are Dr. Robert Ambrose of NASA Johnson Space Center and Dr. Terry Fong of NASA Ames Research Center. NASA is also deploying the R2 robot to ISS in the near future. This work will be directly applicable to control of R2 from a ground controllers station. R2 contacts are Dr. Ron Diftler, Dr. William Bluethmann and Dr. Kimberly Hambuchen all of NASA JSC. NASA has already deployed the Dextre robot to ISS and it is currently in operation. We will explore the use of our robot operator interface with the Dextre robot in mission control. TRACLabs has substantial contacts within MOD for our other work and we will utilize those contacts to explore the potential for applying this technology to Dextre.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Department of Defense deploys large numbers of unmanned vehicles, all of which could benefit from increased capabilities in their operator control units. In particular, our work will provide greater situational awareness to the operators and enable them to explore the effects of actions before actually committing the commands. Congress has mandated that one-third of all military vehicles must be unmanned by 2015. Robotic customers such as US Army TACOM, US Navy SPAWAR, NAVEODTECHDIV, Joint Ground Robotics Enterprise (JGRE), as well as major robotics contractors such as iRobot and QinetiQ are striving to deliver more autonomy in their systems. Together these markets total several thousand potential licenses -- one for each platform. TRACLabs Inc. is a member of the JRGE-sponsored Robotics Technology Consortium (RTC), which gives us access to government and industry robotics customers.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Manipulation
Teleoperation
Autonomous Reasoning/Artificial Intelligence
Human-Computer Interfaces


PROPOSAL NUMBER: 09-2 X6.01-9100
PHASE-1 CONTRACT NUMBER: NNX10CE58P
SUBTOPIC TITLE: Robotic Systems for Human Exploration
PROPOSAL TITLE: Lightweight Robotic Excavation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Astrobotic Technology, Inc.
4551 Forbes Avenue
Pittsburgh, PA 15213-3524
(412) 682-3282

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Gump
david.gump@astrobotictech.com
4551 Forbes Avenue #300
Pittsburgh,  PA 15213-3524
(412) 682-3282

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lightweight robotic excavators address the need for machines that dig, collect, transport and dump lunar soil. Robust and productive small robots enable mining rich and accessible deposits of ice and other volatiles buried near craters at the lunar poles, delivering resources to produce propellant, and thus making space exploration sustainable. Lightweight excavators bridge the gap between prospecting and full-scale ISRU. A lightweight robot is proposed that excavates and delivers regolith with production so superior to the state of the art as to enable realistic lunar and planetary applications. Demonstration of light weight will be achieved by operating a low mass robot in Earth gravity reduced 5/6 by offloading. The significance of the proposed innovation is an approach that not only performs the required tasks but is low in mass (30 kg to 150 kg). Mass constraints make productive excavation challenging. However, innovative designs incorporating transverse bucket-wheels, high payload composite dump beds, and high-speed driving are game changers, enabling regolith operations in low gravity. Phase 1 experimental results show that payload ratio and driving speed govern productivity of small robots. Phase 2 will elevate TRLs from 3 at the beginning to an estimated 4 or 5 at end of contract.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Astrobotic Technology intends to develop the lightweight robotic excavator into several flight missions, selling its services to NASA on a per-task basis or proposing the excavator for NASA-operated missions. The initial mission will demonstrate delivery to a precursor ISRU processing plant and characterize the forces and time required to remove the dry overburden that protects polar volatiles in periodically illuminated regions. This is a crucial step in gathering the data required to determine whether propellant production from polar volatiles will be cost effective. Because solar power is available for this location at certain times of the year, a commercial approach is feasible -- no isotopes are required. Assuming propellant production from polar volatiles is economically justified, then Astrobotic excavators will be integral to the process. The excavator also will support scientific missions, because its precision control over digging depth will make it the first choice for revealing the regolith stratigraphy at investigative sites.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Any space-faring nation seeking to explore and settle the Moon will at least double the productivity of its lunar missions if they purchase the propellant needed to refuel their landers for return to Earth from ISRU plants on the Moon. The excavator is key to early ISRU because its solar power makes it suitable for exploiting the volatiles that are believed to exist in easily accessible locations outside crater floors. Polar volatiles eventually will be exported to Earth orbit where multiple commercial markets will be served. Low Earth orbit spacecraft, especially government and private space stations, can use them for orbit reboost. Commercial communications and remote sensing satellites can be delivered to low orbit, then be lofted to high orbits via reusable transfer vehicles fueled by lunar propellants. By eliminating the mass of the upper stages now employed to reach geosynchronous and other high orbits, these satellites can become heavier and more productive, or they can be launched on smaller and less expensive boosters. Small excavation robotics have commercialization opportunities in earthworking equipment. In terrestrial construction, small excavation machines are specialized for work in tight spaces, but even the smallest are still on-board human operated. Further minimization of machines can be achieved via teleoperation and autonomy, with the added benefit of enabling work in dangerous confined environments without risking the operator's life.

TECHNOLOGY TAXONOMY MAPPING
Mobility
Manipulation
Teleoperation
In-situ Resource Utilization
Composites


PROPOSAL NUMBER: 09-2 X6.01-9794
PHASE-1 CONTRACT NUMBER: NNX10CE59P
SUBTOPIC TITLE: Robotic Systems for Human Exploration
PROPOSAL TITLE: Parametric Optimization and Prediction Tool for Excavation and Prospecting Tasks

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W. 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kris Zacny
zacny@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(510) 207-4555

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Honeybee Robotics therefore proposed to develop a software tool for facilitating prospecting and excavation system trades in support of selecting an optimal architecture for the Moon. The tool could serve as a starting platform for excavation software for Mars or asteroids. The tool will provide engineers with the ability to quickly examine "What if?" scenarios within a trade space by specifying a surface system architecture (e.g. lander or rover based, digging for ice or building burms) and receiving reliable data and graphs evaluating that architecture's performance in terms relevant metrics, such as total energy used or total duration. The proposed software aims to be (a) user friendly, (b) relevant to NASA excavation priorities (xPRP: digging icy regolith for ISRU or LSS: outpost preparation), and (c) accurate for lunar excavation (equations verified by testing in relevant environment and scaled for gravity).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The software developed under this SBIR effort is specifically intended to facilitate system and architecture trades related to excavation activities on the lunar surface (either dry compacted regolith or icy-soil). At transportation costs of $50K-$100K per kilogram to the surface of the Moon, it is economically imperative that lunar excavation and ISRU tasks be accomplished as efficiently as possible. Doing so requires not just minimizing the mass of individual systems, such as an ISRU reactor or a rover, but maximizing the efficiency of the overall architecture. This is no mean feat, and will require many trade studies as different architectures are devised to make use of the landed resources available. This software will speed the process, enabling quicker turnaround on trade studies and providing the best information available for decision making.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Honeybee has witnessed the interest of major international mining concerns in introducing robotics to industrial surface mines. The issues of maintaining trained and trusted personnel in increasingly remote and sometimes conflict-prone locations makes autonomous, semi-autonomous, and teleoperated mining equipment very attractive. In some cases, applying robotics to the mine is as simple as automating a formerly manual procedure. In other cases, the issues are more complex and require careful consideration of multiple alternative architectures. It is actually rather similar to the challenge of selecting appropriate excavation architecture for the Moon, with the added wrinkle of interfacing with legacy logistics and processing architecture. With appropriate modifications, this software could provide a means to facilitate trade studies for commercial mining concerns increasing the use of robotics in the mine. This software will be especially well-suited to high-investment, high-payoff automation projects that introduce a completely new architecture as opposed to simply automating the existing equipment.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Operations Concepts and Requirements
Software Tools for Distributed Analysis and Simulation
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 X6.02-8148
PHASE-1 CONTRACT NUMBER: NNX10CF34P
SUBTOPIC TITLE: Surface System Dust Mitigation
PROPOSAL TITLE: Industrial Scale Production of Celestial Body Simulants

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Zybek Advanced Products, Inc.
2845 29th Street
Boulder, CO 80301-1229
(303) 530-2727

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Weinstein
mike@zybekap.com
2845 29th Street
Boulder,  CO 80301-1229
(303) 530-2727

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 6
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The technical objectives of this program are to develop a cost-effective process to deliver Celestial body simulants for the foreseeable future. Specifically, the technical objectives of this project are: ? Deliver 3 metric tons of a lunar Mare simulant. A portion of the simulant will be bulk, excavation-grade that is compatible to the now depleted JSC-1a. Another portion of the simulant will be a technical grade simulant that has the proper amounts of glass and agglutinates included. Finally, a titanium-rich Mare will be produced. The correct concentrations of titanium are critical for mechanical and chemical process development and testing. ? After the 3 metric tons of Mare simulant; be able to produce bulk simulant at $10,000 per ton. This will be 30% better than the NASA cost target specified in the original solicitation. ? ZAP will deliver 1 metric ton of research grade Highlands type lunar simulant. ? ZAP will deliver a documented process for producing low-cost, bulk mare simulants. After phase 2 project, estimated cost is: $5,000 per ton. ? ZAP will test and demonstrate the applicability of the manufacturing process to produce other Celestial body materials. Examples include: Asteroid, Mars, probe reference samples, and dark glass.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ZAP has firsthand knowledge of an increasing number of groups trying to purchase simulant from ZAP or requesting that ZAP process their specialty feedstock. Specialty requests are increasing because ZAP has become known in the community but more importantly because researchers and engineers are unable to obtain lunar simulant in quantity or within their schedule or budget. Supplies are depleted. Unfortunately, many requests go unfilled. This proposal will have direct benefit to NASA centers and Directorates as well as to research institutions and private companies. ZAP has provided samples at no charge to four different NASA centers. In addition NASA contractors ranging from the Laboratory for Atmospheric and Space Research (LASP), National Lunar Science Institute to SBIR research contracts have requested lunar simulants in various quantities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
As detailed in the phase 2 proposal, ZAP has identified 6 significant commercial applications for the technologies used to manufacture lunar simulant components. These include: precious metal recovery from ore (using agglutinate plasma reactor), synthetic mineral production for catalysts, high surface area milling for improved platinum extraction, mineral liberation with AIR mill, improved abrasive materials for optic polishing, and environmentally-friendly glass melting. ZAP is working with industrial customers for all of these applications. In addition to the current active commercial interest, future applications for the process include: Zero valent iron in agglutinate for groundwater remediation, synthetic minerals for research accelerators, nano-scale MoOx for Li-Ion batteries, and thermal metal beneficiation. There is always favorable tax payer sentiment for space technologies that are transferred to practical commercial applications. The extensive media coverage ZAP has recently received for this program is aiding in finding these commercial opportunities.

TECHNOLOGY TAXONOMY MAPPING
Ablatives
Testing Facilities
Earth-Supplied Resource Utilization
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 X6.02-8804
PHASE-1 CONTRACT NUMBER: NNX10CD29P
SUBTOPIC TITLE: Surface System Dust Mitigation
PROPOSAL TITLE: Nanotube Electrodes for Dust Mitigation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Eikos, Inc.
2 Master Drive
Franklin, MA 02038-3034
(508) 528-0300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Glatkowski
pglatkowski@eikos.com
2 Master Drive
Franlkin,  MA 02038-3034
(508) 528-0300

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Dust mitigation is critical to the survivability of vehicle and infrastructure components and systems and to the safety of astronauts during EVAs and planetary surface operations. By coupling Eikos Invisicon<SUP>REG</SUP> nanocomposite conductors with existing dust mitigation Dust Shield technology developed at NASA-KSC, the Phase I program demonstrated an enabling approach to producing electrodynamic dust mitigation devices on a wide variety of surfaces not possible with traditional metal based electrode materials. Eikos reproduced proven NASA spiral electrodes using Invisicon<SUP>REG</SUP> patterned onto transparent plastics, Tyvek<SUP>REG</SUP> fabric, and silicone rubber sheets; employing inkjet and spray deposition methods, two CNT ink formulations, and four dielectric binders to create working devices. These Invisicon<SUP>REG</SUP>-based devices are far more flexible then traditional devices and exhibit superior durability to abrasion, elongation, and thermal cycling. A dust mitigation system utilizing this technology has broad value to many NASA mission directorates and terrestrial commercial applications. The Phase II project will build on these successes and integrate the electrode into larger surfaces, and more complex components. Further, extensive dust mitigation, and both environmental and mechanical testing, will be conducted to position this electrode technology for insertion into windows, fabrics, and elastomeric components in space and terrestrial applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ESC mitigation is critical to the survivability of vehicle and infrastructure components and systems and to the safety of astronauts during EVAs and planetary surface operations. This technology will provide significant improvement in robustness, reliability, and safety. Once fully matured, this technology will be implemented to sustain affordable exploration in remote environments where surface contamination, like dust, is persistently reducing the effectiveness, safety, and sustainability of key systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Eikos is currently marketing these conductive coatings under its registered trademark, Invisicon<SUP>REG</SUP>, as a replacement for ITO in existing applications, and a core part of our second thrust is to use Invisicon<SUP>REG</SUP> coatings for rapid prototyping of new electronic devices and enabling entirely new device structures. Based on superior performance and lower costs Invisicon<SUP>REG</SUP> can be a transparent electrode that is easily printed and patterned allowing manufacturers to produce more efficient and cost effective PV's, displays, and electronic devices. One key terrestrial application is the use of Invisicon<SUP>REG</SUP> electrodes in electrodynamic dust mitigation cleaners for solar PV arrays for utility electricity generation in arid regions.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Manned-Maneuvering Units
Portable Life Support
Suits
Photovoltaic Conversion


PROPOSAL NUMBER: 09-2 X7.01-8216
PHASE-1 CONTRACT NUMBER: NNX10CD30P
SUBTOPIC TITLE: Advanced Space Rated Batteries
PROPOSAL TITLE: High Energy Density Li-Ion Batteries Designed for Low Temperature Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NEI Corporation
201 Circle Drive N., Suite 102/103
Piscataway, NJ 08854-3723
(732) 868-3141

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nader Hagh
nmhagh@neicorporation.com
400 Apgar Drive, Suite E
Somerset,  NJ 08873-1154
(732) 868-3141

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The state-of-the-art Li-ion batteries do not fully meet the energy density, power density and safety requirements specified by NASA for future exploration missions. Building upon our Phase I feasibility study, we propose to implement an advanced cathode material in practical Li-ion batteries. The cathode material offers superior electrochemical performance over its commercially used counterpart, particularly in terms of discharge capacity and energy density. In Phase I, working in collaboration with a leading university-based researcher, we demonstrated that intrinsic modifications in the crystal structure, and extrinsic modifications on the surface of cathode particles, can lead to energy densities greater than 1150 Wh/kg at room temperature and 800 Wh/kg at zero degrees C for the cathode powder. In the Phase II program, we intend to combine the intrinsic and extrinsic effects in the cathode material, which will deliver the needed energy density at low temperatures, along with other desirable attributes. This will represent a significant advancement of the state-of-the-art in cathode materials. The structural and morphological modifications introduced in the material will allow us to (i) maintain high energy and power density at low temperature (ii) lower the irreversible capacity loss and improve the efficiency, and (iii) further stabilize and enhance the safety of the cell. In Phase II, our university-based collaborator will fabricate and test small Li-ion pouch cells, which will help optimize the cathode material. In addition, prototype Li-ion cells with a capacity of ~ 5Ah will be fabricated and tested by a large Li-ion battery manufacturer and supplier to the aerospace industry. Further, a NASA prime contractor has offered to guide the Phase II program. The outcome of a successful Phase II program will be the demonstration of an advanced and robust energy storage system that can be used for future NASA applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced Li-ion battery systems with high energy and power densities are required for NASA's exploration missions that will operate at low temperatures. These batteries are required to power components and systems, such as the James Webb Space Telescope (JWST), Mars Atmospheric and Volatile Evolution (MAVEN), deep drilling equipment and Astrobiology Field Laboratory on Mars, International X-ray Observatory (IXO), and extravehicular activities. The Phase II program will demonstrate an advanced Li-ion battery that is expected to meet NASA's high energy density requirement (cell level specific energy > 300 Wh/kg at C/2) at an operating temperature of T=0&#8304;C.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications for the proposed innovation include (i) automotive applications such as Li-ion battery packs in Hybrid Electric Vehicles (HEVs), (ii) consumer electronics such as laptops, mobile phones, cameras, camcorders, electric razors, toothbrush, portable TVs and radios, and power tools, (iii) medical devices, (iv) electric bikes/scooters, (v) military applications such as underwater batteries, air, ground, emergency and pulse power applications.

TECHNOLOGY TAXONOMY MAPPING
Ceramics
Composites
Energy Storage


PROPOSAL NUMBER: 09-2 X7.01-8568
PHASE-1 CONTRACT NUMBER: NNX10CD31P
SUBTOPIC TITLE: Advanced Space Rated Batteries
PROPOSAL TITLE: Mesoporous Silicon-Based Anodes for High Capacity, High Performance Li-ion Batteries

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
EIC Laboratories, Inc.
111 Downey Street
Norwood, MA 02062-2612
(781) 769-9450

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dharmasena Peramunage
pera@eiclabs.com
EIC Laboratories, Inc.,111 Downey Street
Norwood,  MA 02062-2612
(781) 769-9450

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new high capacity anode composite based on mesoporous silicon is proposed. By virtue of a structure that resembles a pseudo one-dimensional phase, the active anode material will be able to accommodate significant volume changes expected upon alloying and de-alloying with lithium. The mesoporosity will be created without the aid of a surfactant template using a novel high volume synthetic process. The anode composite based on this material is designed to have a reversible Li-ion capacity exceeding 600 mAh/g or nearly twice that obtainable with graphite anodes; indeed much higher capacities could be practically attainable. Phase I successfully demonstrated the synthesis of this new meso-Si material as well as its high electrochemical activity and rechargeability. An expanded investigation on the development of mesoporous Si-based Li-ion anode is the principal objective in Phase II. The optimum anode will be evaluated in Li-ion cells containing 4V oxide cathodes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Principal NASA applications will include power for landers, rovers and extravehicular activities (EVA). Coupled with a suitable electrolyte Li-Ion cells based on this anode will be suitable for space-related applications, in moon and other planetary habitats etc, requiring high specific energy rechargeable batteries with unique attributes such as non-flammability and sub-ambient temperature operation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The new anodes will result in high performance Li-ion batteries suitable for electric vehicle propulsion and for use in portable consumer products such as cellular phones, portable power tools, cameras and laptop computers.

TECHNOLOGY TAXONOMY MAPPING
Mobility
Portable Life Support
Semi-Conductors/Solid State Device Materials
Energy Storage
Power Management and Distribution


PROPOSAL NUMBER: 09-2 X7.02-8908
PHASE-1 CONTRACT NUMBER: NNX10CD36P
SUBTOPIC TITLE: Surface Nuclear Power Systems
PROPOSAL TITLE: Autonomus I&C Maintenance and Health Monitoring System for Fission Surface Power

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Analysis and Measurement Services Corporation
9111 Cross Park Drive, Building A-100
Knoxville, TN 37923-4510
(865) 691-1756

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brent Shumaker
bshumaker@ams-corp.com
9119 Cross Park Drive
Knoxville,  TN 37923-4505
(865) 691-1756

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary goal of this project is to design and develop an autonomous instrumentation and control (I&C) health monitoring system for space nuclear power applications. The system, once fully developed, will be able to detect system anomalies based on analytical modeling technique using data from existing sensors in the power generator. The primary application for the proposed technology will be with space nuclear reactors and the non-nuclear test systems that are being used for component and system level validation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application for the proposed technology will be with space nuclear reactors and the non-nuclear test systems that are being used for component and system level validation. However, the basic autonomous instrumentation and control (I&C) and health monitoring technology developed could be applied to a wide range of applications including aircraft structural and system health monitoring, chemical propulsion systems and ground test facilities for liquid fuel rocket motor testing and development.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Another commercial application will be the development of a system health monitoring product for nuclear power utilities. AMS will work to develop a product that can first be used for health monitoring on reactor power plant components and subsystems, with continued development focused on higher-level systems and, potentially, overall plant health monitoring. There is a demonstrated need for such systems in the existing commercial nuclear power fleet as well as the next generation designs that are now being considered. In addition, a potential commercial opportunity exists in the development of autonomous health monitoring systems for Small Modular Reactors (SMRs), which are now in the design phases.

TECHNOLOGY TAXONOMY MAPPING
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 X7.02-9116
PHASE-1 CONTRACT NUMBER: NNX10RA56P
SUBTOPIC TITLE: Surface Nuclear Power Systems
PROPOSAL TITLE: High-Speed Neutron and Gamma Flux Sensor for Monitoring Surface Nuclear Reactors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luna Innovations Incorporated
1 Riverside Circle, Suite 400
Roanoke, VA 24016-4692
(540) 769-8400

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Clark Boyd
boydc@lunainnovations.com
3157 State Street
Blacksburg,  VA 24060-6604
(540) 961-6731

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA needs compact nuclear reactors to power future bases on the moon and/or Mars. These reactors require robust automatic control systems using low mass, rapid response, in-core reactor power monitoring sensors and radiation tolerant sensor interrogation systems that do not yet exist. Luna proposes to develop a new type of fiber optic miniature neutron flux and gamma flux sensor, which will have significantly faster response than recently developed fiber optic radiation sensors. The new sensors will maintain the advantages of current fiber optic reactor sensor technology, including small size for in-core sensor distributions, high temperature performance (above 600<SUP>o</SUP>C), and immunity to electrical noise in the presence of ionizing radiation. During Phase II Luna will optimize the sensor design and the interrogation system for high temperature in-core monitoring of both gamma flux and neutron flux with internal thermal compensation and in-situ thermal calibration. At the end of Phase II, Luna will deliver a lightweight sensor interrogation system, utilizing experimentally verified radiation hardened components wherever possible, and including an analog output signal for interfacing with standard reactor control electronics.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
While the sensor development will be focused on nuclear space power needs, the sensors can also be directly utilized for monitoring nuclear terrestrial power reactors as well. Potential NASA applications include: Lunar surface power reactors, Mars surface power reactors, and Nuclear Thermal Propulsion (NTP) for Mars manned missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The sensors developed on this project will also contribute to the safe and economically competitive operation of commercial nuclear power plants. The high temperature and high speed performance of these sensors will be needed in future advanced reactor designs, where elevated temperature operation is being designed for higher electrical generation efficiency. Under these more severe conditions, reliable sensor operation becomes even more critical for continued safe operation. Arrays of Luna's fiber optic radiation flux sensors can also be used to monitor spent fuel and nuclear waste storage facilities.

TECHNOLOGY TAXONOMY MAPPING
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Control Instrumentation
Particle and Fields
High-Energy
Radiation-Hard/Resistant Electronics
Nuclear Conversion


PROPOSAL NUMBER: 09-2 X7.03-8742
PHASE-1 CONTRACT NUMBER: NNX10CD38P
SUBTOPIC TITLE: Fuel Cells for Surface Systems
PROPOSAL TITLE: Novel Conductive Water Removal Membrane (CWRM) for PEM Passive Fuel Cell Operation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ElectroChem, Inc.
400 West Cummings Park
Woburn, MA 01801-6519
(781) 938-5300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Pien
mpien@fuelcell.com
400 West Cummings Park
Woburn,  MA 01801-6519
(781) 938-5300

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ElectroChem proposes a Phase II program to advance its Phase I effort, to develop a conductive water removal membrane to enable passive, high current density PEMFC operation. Very good progress was demonstrated by the two approaches investigated: 1) Construct a carbon-based composite, higher bubble point membrane; 2) convert a polymer-based water removal membrane to a conductive membrane (both approaches to meet the CWRM primary requirements of conductivity, water permeation, and "no gas leakage"). In Phase I, coating the carbon with conductive/hydrophilic materials was very effective, resulting in CWRM's that met the conductivity and water permeation requirements and reduced gas permeation by 99.8%. A multilayer variation achieved "no gas permeation" at 40 psig. In the polymer approach, conductive material treatments were successful in increasing conductivity. In Phase II, we will 1) use quantitative control of the carbon coatings to advance the promising carbon composite approach; 2) utilize individual layers with different properties to construct a multilayer CWRM; 3) investigate the use of a conducting polymer to increase bubble pressure. To produce a polymer-based CWRM, an advanced pore modification technique will be used to enhance polymer acceptability of the conductive particles. The program will culminate with fuel cell testing of the CWRM's.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The development of a conductive water removal membrane (CWRM) will enable PEM Fuel Cells to operate passively and at high current densities, which eliminates the need for product water removal via complex rotating machinery. This minimizes the weight and volume, improves the efficiency, life, safety, system simplicity and reliability. In the near term, this will enable NASA to meet its critical need for Lunar-type-Rovers (approximately 50-500W) over the next ten years. When the time comes, the IFF PEM Fuel containing the CWRM will be ready to meet NASA's need for a replacement fuel cell power plant (approximately 15 kW) for the successor to the Shuttle. And after NASA returns to the Moon and establishes a permanent presence there, it will have a need for a power system (approximately 25kW) that can reliably meet the Moon's 14+ day-long and 14+ night-long unique requirements. The PEM Fuel Cell containing the CWRM has the potential of meeting this future critical NASA need via a Regenerative Fuel Cell.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The fact that the IFF fuel containing the conductive water removal membrane/separator (CWRM) will significantly simplify PEMFC operation (and result in both higher and safer performance) makes it very attractive for a wide variety of non-NASA Commercial applications. In the near-term, its unique passive operation and exceptional stability makes it ideal for powering remote applications like monitors and sensors, which require very high reliability. Following scale-up and optimization, the IFF concept, applied to the regenerative fuel cell, will be able to meet the growing needs for reliable, non-polluting Uninterruptible Power Systems (in the range of 4-8 kW). And, following further development, the IFF will be able to replace conventional PEMFC systems in satisfying the special requirements of transportation applications, including passenger cars (50 kW and up).

TECHNOLOGY TAXONOMY MAPPING
Energy Storage
Renewable Energy


PROPOSAL NUMBER: 09-2 X7.03-9598
PHASE-1 CONTRACT NUMBER: NNX10CD39P
SUBTOPIC TITLE: Fuel Cells for Surface Systems
PROPOSAL TITLE: Advanced Oxygen Evolution Catalysts for PEM Electrolyzers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Lynntech, Inc.
7610 Eastmark Drive
College Station, TX 77840-4023
(979) 693-0017

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alan Cisar
alan.cisar@lynntech.com
7610 Eastmark Drive
College Station,  TX 77840-4023
(979) 693-0017

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future NASA missions require high efficiency, lightweight, long life, and maintenance-free water electrolyzer technologies to generate oxygen and/or hydrogen for energy storage, propulsion, life-support systems, cabin-oxygen replenishment, and zero-g science activities. International Space Station, future Lunar and Martian Outposts, and future exploration vehicles require high efficiency electrolyzers to improve their operational capabilities for long and complex missions. The oxygen evolution reaction is the limiting step due to non-optimal electrocatalyst structure. State-of-the-art electrocatalysts do not meet MEA efficiency and lifetime requirements for NASA applications. Advanced electrocatalysts are needed. In the Phase I, Lynntech manufactured a binary nanoparticle surface decorated mixed oxide electrocatalyst with the optimal microstructure and demonstrated an MEA efficiency of >90% (i.e., an electrolysis potential of 1.358 V/cell) at 200 mA/cm2. In the Phase II program, Lynntech will investigate different catalyst morphologies to improve the lifetime. In addition, ternary transition metal oxides will be incorporated into the mixed oxide to further increase the efficiency and lifetime. The applicability of this advanced catalyst to different membranes will be investigated. Nanocomposite membranes with low hydrogen gas cross-over will be manufactured and tested. A short electrolyzer stack will be assembled with the optimized components, tested and delivered to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Some of the potential NASA applications for the advanced OER catalyst are listed below. The advanced OER catalyst developed in this project can replace the current state-of-the-art anode catalysts in the following applications: 1. Electrolyzers in regenerative fuel cell systems for storing energy in the form of hydrogen and oxygen via water electrolysis (lunar and planetary fixed base energy storage, recharge of lunar rovers, portable power fuel cells, etc.). 2. PEM electrolyzers systems for oxygen generation (for environmental control, crew life support, replenishing the oxygen for cabin, pre-breath oxygen delivery unit prior to space walking, propulsion for in-space maneuvering, in-space science activities, etc.). 3. Electrochemical oxygen concentrators (oxygen concentration from cabin air for medical emergencies, portable back-up oxygen storage, etc.).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA applications for this OER catalyst are energy storage for use with intermittent renewable sources such as solar, tidal, and wind power, hydrogen and oxygen generation for residential and stationary applications, efficient generation of hydrogen fuel using off-peak electricity, O2 generation for medical applications such as hospitals, deployed field hospitals and portable O2 concentrators. In addition, mixed metal oxide catalyst can have immediate use for gas sensing applications to detect numerous toxic, poisonous and otherwise harmful gases.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Pilot Support Systems
Air Revitalization and Conditioning
Biomedical and Life Support
Manned-Maneuvering Units
Portable Life Support
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Energy Storage
Renewable Energy


PROPOSAL NUMBER: 09-2 X7.03-9874
PHASE-1 CONTRACT NUMBER: NNX10CD40P
SUBTOPIC TITLE: Fuel Cells for Surface Systems
PROPOSAL TITLE: Water Management Membrane for Fuel Cells and Electrolyzers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Giner Electrochemical Systems, LLC
89 Rumford Avenue
Newton, MA 02466-1311
(781) 529-0500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Corkney Mittelsteadt
cmittelsteadt@ginerinc.com
89 Rumford Avenue
Newton,  MA 02466-1311
(781) 781-0529

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of an improved water management membrane for a static vapor feed electrolyzer that produces sub-saturated H2 and O2 is proposed. This improved membrane can increase the performance and especially the durability of static vapor feed electrolyzers. Static vapor feed electrolyzers greatly simplify electrolyzer systems as they eliminate the need for water/gas phase separation, which is particularly challenging in a zero gravity environment. Maintaining water in the vapor phase greatly reduces membrane swelling which should increase durability. Finally, by keeping water in the vapor phase the MEA is not exposed to ion and other contaminants that are carried by a liquid water stream, further increasing durability and simplifying the system by reducing the need for ultra-pure water. The primary goal of this Phase II program then is to demonstrate the enhanced performance and durability of a static vapor feed electrolyzer utilizing an improved water management membrane.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lunar and space stations, satellites, high altitude aircraft. Terrestrial water electrolyzers typically utilize an abundance of recirculated water to the electrolyzer, usually on the anode (oxygen) side, where it serves reactant, coolant, and as the "carrier" phase wherein the product oxygen is carried from the anode by the pumped water. Subsequent to leaving the electrolyzer the phases are separated by gravity in a receiving tank. In near-zero or low-gravity environments, this separation is difficult to achieve. Doing so results in additional system complexity and compromised process efficiency. As part of a regenerative fuel cell system, NASA has a need for highly-efficiency, but robust technologies capable of storing energy in the form of stored hydrogen and oxygen. The Static Water Vapor Feed (SWVF) Electrolyzer is an elegant solution to overcome and simplify the above problems. Thus NASA will be the first to utilize electrolyzers with this technology, possibly in the Constellation mission in the lunar-based and Martian energy storage systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Utilizing a water vapor feed is highly attractive for laboratory and small industrial scale electrolyzers. Giner Electrochemical Systems, LLC. is the world's largest supplier of laboratory electrolyzer stack and stack parts. These electrolyzers have excellent proven durability, greatly exceeding five years. However, they require an extremely pure deionized water feed. The ability of a vapor-fed electrolyzer to operate on tap water would make this technology even more attractive for these applications. In a similar fashion to water permeation through an ionomeric membrane, alcohols such as methanol and ethanol can permeate membranes. Thus the static vapor feed technology may be useful in alcohol-air batteries such as those used for portable power. In all these applications, the management of the gases and liquids involved generates significant complexity that inevitably increases the cost and reduces reliability of such devices. As such, they will all benefit from static water vapor feed technologies.

TECHNOLOGY TAXONOMY MAPPING
Portable Life Support
Composites
Energy Storage
Renewable Energy


PROPOSAL NUMBER: 09-2 X8.01-8258
PHASE-1 CONTRACT NUMBER: NNX10RA57P
SUBTOPIC TITLE: Cryogenic Fluid Transfer and Handling
PROPOSAL TITLE: Wrapped-MLI: Thermal Insulation for Cryogenic Piping

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Quest Product Development Corporation
6833 Joyce Street
Arvada, CO 80007-7570
(303) 670-5088

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Dye
sdye@quest-corp.com
6833 Joyce Street
Arvada,  CO 80007-7570
(303) 670-5088

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
New NASA vehicles (EDS, Orion, landers & orbiting fuel depots) need improved cryogenic propellant transfer & storage for long duration missions. Current cryogen feed line Multi-Layer Insulation (MLI) performance is 10X worse per area than tank MLI insulation. Cryogenic piping heat leak is 50 ? 80% of cryotank heat leak, and 40 ? 50% of LH2 is lost - about 150,000 gallons ($300,000) - during transfer, chill down & ground hold during each STS launch. Quest Product Development, teaming with Ball Aerospace, proposes to continue development of an innovative advanced insulation system, Wrapped MLI, which could provide improved thermal insulation for cryogenic feed lines. Wrapped MLI (wMLI) is high performance multilayer insulation designed for cryogenic piping that uses Quest's innovative discrete spacer technology to control layer spacing/density and reduce heat leak. The Phase I program successfully proved wMLI feasibility by designing, building and testing a wMLI prototype with a measured heat leak 3.6X lower than spiral-wrapped conventional MLI widely used for piping insulation. A wMLI prototype had a heat leak of 7.3 W/m2, or 27% of the heat leak of conventional MLI (26.7 W/m2). Modeling estimates the thermal performance of wMLI could be further improved by 3-fold, leading to a heat leak of 0.7 W/m2 (20 layers, 77K to 295K), and even larger advantages over conventional MLI piping insulation. In a Phase II program we would further develop wMLI technology with custom, molded polymer spacers, and advance the product toward commercialization via a rigorous testing program including developing advanced vacuum insulated pipe for GSE application. wMLI could provide advanced cryogen transfer line insulation and be the basis of a superior Vacuum Insulated Pipe technology.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Improved passive thermal insulation for cryogenic propellant lines is a critical need for new NASA vehicles and orbiting fuel depots, where the heat leak into cryo-feed lines can be 10 to 20% of the overall system heat leak. Wrapped MLI, with a heat leak 3.6X less than conventional MLI, can provide improved piping insulation. Lower heat leak, easier assembly, fewer layers, lower cost and less mass are all desirable features for cryogenic feed line insulation that wMLI might provide. wMLI technology could create superior vacuum insulated pipe used to transfer cryogens. NASA's launch pads use some 1500' of vacuum jacketed pipe to transfer LH2 and LOX to launch vehicle tanks, losing 40 ? 50% of the LH2. Boil off losses from line and tank chill down and heat leak are 150,000 gallons ($300,000) per shuttle launch. wMLI could be beneficial for: ? Cryogenic propellant piping insulation for NASA vehicles, including EDS, Orion, cryo landers, cryo upper stage launch vehicles, orbiting fuel depots ? Cryogenic piping insulation for Ground Support Equipment for launch facilities, launch vehicles, cryogenic upper stages and LH2 powered aircraft

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High performance thermal insulation specially designed for pipes and tubing has utility in numerous industrial and commercial cryogenic applications. Insulated cryogenic piping is used for transfers of cryogenic liquid into and from cryogenic dewars for LN2, LHe, LOX, which are widely used in food, research, medical and industrial applications. There are numerous industrial uses for cryogenic lines and handling equipment. Cryogenic pipes, lines and tubing uses include liquid nitrogen (LN2), liquid oxygen and liquified natural gas (LNG) handling products such as piping, automatic filling equipment, dewar manifolds and gas panels. High performance insulated cryogenic transfer piping is critical to the LNG industry, where heat gain into pipes causes LNG losses from vaporization during liquid transfer. LN2 equipment is used for industrial or food applications including semiconductor, electronics and aerospace environmental temperature testing, special effects (fogging), biological freezing applications, inerting of food and beverage containers, container pressurization and food freezing. wMLI could provide superior vacuum insulated pipe insulation for these applications: ? Ground Support Equipment for commercial launch facilities and cryogenic upper stage launch vehicles such as Atlas Centaur and Delta IV upper stage ? Cryogenic fluid handling piping such as Vacuum Insulated Pipe

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Thermal Insulating Materials
Feed System Components
Fluid Storage and Handling


PROPOSAL NUMBER: 09-2 X8.01-8579
PHASE-1 CONTRACT NUMBER: NNX10CE61P
SUBTOPIC TITLE: Cryogenic Fluid Transfer and Handling
PROPOSAL TITLE: Hybrid Aerogel-MLI Insulation System for Cryogenic Storage in Space Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aspen Aerogels, Inc.
30 Forbes Road, Bldg. B
Northborough, MA 01532-2501
(508) 691-1161

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Redouane Begag
rbegag@aerogel.com
30 Forbes Road
Northborough,  MA 01532-2501
(508) 466-3124

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The future of the NASA space program includes longer and more invasive missions into space. Long duration storage of large quantities of cryogenic fluids for propulsion, power, and life-support is an essential requirement for these missions. Efficient and reliable insulation of the cryogenic fluids is key to the success of long missions into space. Aspen Aerogels successfully developed a novel low-density hybrid insulation system composed of multiple layers of low density, low dust superhydrophobic aerogels and multilayer insulation (MLI) for cryogenic fluid management. The hybrid aerogel/MLI insulation system outperformed MLI system at cryogenic temperatures and across a range of vacuum conditions, including high vacuum. This exceptional performance is considered a new breakthrough in high vacuum cryogenic thermal insulation materials. During the Phase II Program, further refinement and qualification testing of the low-density aerogel material will be performed in order to be used in real world applications. Liquid oxygen (LOX) compatibility of the aerogel material and a cost assessment will also be investigated. For qualification of this novel insulation system for future NASA in-space programs, extensive work will be dedicated to large-scale testing and performance evaluation of the refined hybrid aerogel/MLI insulation system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The material developed in the Phase II effort could have a variety of applications in the aerospace industry and within NASA. Aerogels are the most efficient thermal insulation known, and NASA has several applications that would benefit from the low density and low thermal conductivity of aerogels. Aspen has been in discussions with United Launch Alliance and NASA Kennedy Space Center to test the hybrid aerogel/MLI insulation system on the CRYogenics Orbital TEstbed (CRYOTE). This testbed will be used to advance the TRL level of the insulation system from 5 (at the end of Phase II) to 7. Low density aerogels will greatly assist NASA to improve its insulation for cryogenic fuel tanks, cryogenic fuel transfer lines, and internal insulation on re-usable launch vehicles. The aerogels developed could also find applications in hypersonic vehicles, and crew exploration vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting insulation system from this program will also have far reaching benefits for both military and commercial applications. The materials would also be of interest to DoD and DoT. The potential for the use of this material exists for cryogenic fuel storage tanks and transfer lines for liquefied natural gas. There are also numerous applications for durable and reliable insulation systems that would improve the energy efficiency of cryogenic industrial processes. The product will have a commercial impact in areas such as: magnetic resonance imaging, power transmission in big cities (superconducting cable), food freezing and blood banking.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Launch and Flight Vehicle
Thermal Insulating Materials
Fluid Storage and Handling
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X8.01-8628
PHASE-1 CONTRACT NUMBER: NNX10CE62P
SUBTOPIC TITLE: Cryogenic Fluid Transfer and Handling
PROPOSAL TITLE: Aerogel-Filled Foam Core Insulation for Cryogenic Propellant Storage, Phase II

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ultramet
12173 Montague Street
Pacoima, CA 91331-2210
(818) 899-0236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Victor Arrieta
victor.arrieta@ultramet.com
Ultramet
Pacoima,  CA 91331-2210
(818) 899-0236

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Current cryogenic insulation materials suffer from various drawbacks including high cost and weight, lack of structural or load-bearing capability, fabrication complexity, and property anisotropy. A need clearly exists for lightweight thermal insulation that is isotropic and structurally capable with high thermal performance, while also offering reduced fabrication and installation complexity and lower cost. In previous work for NASA and DoD involving lightweight structural insulation for high temperature engine and airframe applications, Ultramet developed and demonstrated lightweight open-cell foam insulators composed of a carbon or ceramic structural foam skeleton filled with a low-cost, nanoscale aerogel insulator. The potential exists to adapt and optimize aerogel-filled structural foam for the cryogenic insulation application, taking advantage of the thermal and mechanical benefits of each component while offering low cost and manufacturability in complex shapes. In Phase I, the feasibility of fabricating aerogel-filled open-cell foam for cryogenic application was demonstrated, initial thermal performance was established, and a path for continued material and structural optimization was developed through design and modeling. In Phase II, Ultramet will again team with Ocellus, a leader in low-cost aerogel fabrication, and Materials Research and Design for design and analysis support. Thermal performance will be characterized at the Cryogenics Test Laboratory at Kennedy Space Center.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The potential application of this technology as a lightweight structural insulator for cryogenic propellant tanks and lines both at ambient pressure and under high vacuum may prove an enabling technology for future NASA space and planetary missions and ground operations. Passive thermal control is required for zero-boiloff storage of cryogens for both long term (>200 days for liquid oxygen and hydrogen) on the lunar surface and short term (14 days) on orbit. Future launch sites on Earth and in space will need a new approach for supplying propellants, gases, and electrical power. Insulation advances must be built around system-integrated concepts for both energy conservation and cryogenic production. Piping networks to deliver the cryogenic fluids across long distances will be a key element, and cost-efficient production and storage of cryogens is an important area of future NASA technology development. The proposed aerogel-filled structural foam cryogenic insulation will offer improved thermal performance over current materials, with the added benefits of reduced weight and fabrication and installation costs relative to conventional multilayer insulation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Advanced cryogenic insulation will find extensive commercial application as cryogenic liquids (nitrogen, oxygen, argon, carbon dioxide, and liquefied natural gas) must be stored, handled, and transferred in support of the food, transportation, energy, and medical industries. To minimize heat leaks into storage tanks and transfer lines, high-performance, economical materials are needed to provide high levels of thermal isolation and minimize evaporation losses. Specific applications for these industries include energy (electricity, power transmission, and fuel cells), food (preservation and packaging), medicine (biological storage), electronics (imaging and semiconductors), and scientific research instrumentation.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Propellant Storage
Thermal Insulating Materials
Tankage
Fluid Storage and Handling
Ceramics
Composites
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 X8.01-8727
PHASE-1 CONTRACT NUMBER: NNX10CE63P
SUBTOPIC TITLE: Cryogenic Fluid Transfer and Handling
PROPOSAL TITLE: High Reliability Cryogenic Piezoelectric Valve Actuator

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Dynamic Structures and Materials, LLC
205 Williamson Square
Franklin, TN 37064-1315
(615) 595-6665

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Paine
jpaine@dynamic-structures.com
205 Williamson Square
Franklin,  TN 37064-1315
(615) 615-6665

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cryogenic fluid valves are subject to harsh exposure and actuators to drive these valves require robust performance and high reliability. DSM's piezoelectric actuators offer advantages over traditional alternative actuator technology. However, in order to use piezoceramic actuators in cryogenic fluid handling applications, proof of operational reliability and improvements in thermal neutral response are required. During the Phase I, DSM experienced great successes and found multiple compelling reasons to continue into Phase II. Particular successes include: gaining access to a new piezoceramic material with superior cryogenic performance, demonstrating a flight-like vibration test survivability level for a small actuator sample set, and, development of a novel composite actuator with excellent neutral thermal response. The outcome of the Phase I yields multiple compelling reasons to continue into Phase 2. The potential for application of this actuator technology to cryogenic fluid valves is substantial with interested NASA advisors at NASA JSC, MSFC, and GRC.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
DSM has received interest from NASA regarding piezoelectric actuators for cryogenic applications and for others that do not require low temperature capability. Many non-cryogenic uses require a wider temperature range than laboratory environment, so some of the proposed work related to CTE characterization and improved protective coating would be useful for these purposes, as well. Many inquiries are related to the regulation of fluid flow or pressure. Thruster valves used in highly miniaturized satellites have received significant attention. Flow and pressure control of cryogenic propellants such as LOX for propulsion is also an area of interest. A scientist at GRC has begun investigating whether this technology will be suitable for regulation of flow for a fuel cell application. As the technology is more fully developed, it will be practical to pursue applications requiring more force. Interest has been expressed in an actuator for a 2 inch cryo-isolation valve that will require over 150 pounds of output force. There are many cryo and non-cryo valve applications that can potentially be addressed by this technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The most direct applications outside NASA are other aerospace projects that require actuators to operate valves for cryogenic fluid handling. ESA and major US defense contractors have previously tested systems that used piezoelectric actuators from DSM. It is reasonable to assume that once the technology reaches a readiness level that is acceptable for NASA, other aerospace entities will have similar interest in using it for their programs. The US Air Force has expressed interest in very low temperature, high force piezoelectric actuators for use in their low Earth orbit simulation chambers at Arnold Engineering Development Center. More broadly, some commercial applications related to materials evaluation and inspection need positioning at very low temperature and could benefit from this research.

TECHNOLOGY TAXONOMY MAPPING
Micro Thrusters
Propellant Storage
Kinematic-Deployable
Feed System Components
Biomedical and Life Support
Laser
Fluid Storage and Handling
Instrumentation
Photonics
Composites


PROPOSAL NUMBER: 09-2 X8.01-9482
PHASE-1 CONTRACT NUMBER: NNX10CE64P
SUBTOPIC TITLE: Cryogenic Fluid Transfer and Handling
PROPOSAL TITLE: Manufacture of Novel Cryogenic Thermal Protection Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Materials Technology, Inc.
9324 Mandrake Court
Tampa, FL 33647-3289
(813) 994-6360

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Akbar Ghaneh-Fard
advancedmaterialstech@gmail.com
9324 Mandrake Court
Tampa,  FL 33647-3289
(813) 994-6360

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Materials Technology, Inc (AMTI) responds to the NASA SBIR solicitation X8 "Space Cryogenic Systems" under subtopic X8.01, "Cryogenic Fluid Transfer and Handling". The proposed Phase II SBIR program is aimed at developing new cryogenic insulations for passive thermal control, resulting in zero boil-off storage of cryogens. The passive thermal control will serve to limit the heat leak into the cryogenic storage system. The proposed technology is expected to increase reliability, increase cryogenic system performance, and is capable of being made flight qualified for the flight systems and to meet Exploration Systems mission requirements. We will continue to use the technical approaches that have shown tremendous potential during the successful Phase I effort. Our key approach will be based on the development, fabrication, and characterization of organic-inorganic hybrid nanocomposite microfoams. In the Phase I program, we successfully demonstrated the feasibility of fabrication of these new foams with significantly improved morphology and thermo-mechanical properties. The proposed approach will utilize environmentally friendly blowing agents. The closed cell structure of these novel foams will prevent the occurrence of cryopumping. The proposed effort will further enhance and optimize the novel microfoams, scale up the optimized materials, and culminate in the fabrication of prototype materials to demonstrate the readiness and maturity of our techniques.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The ability of the proposed hybrid microfoams to remain flexible and resilient at cryogenic temperatures makes them an ideal choice for lightweight insulation in space applications. Some examples of NASA applications include cryogenic insulation of storage tanks, vessels, pumps, and transfer lines on major rocket propulsion systems. Our materials will provide NASA with robust cryogenic solutions and, therefore, will significantly decrease space mission failures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The innovative technology proposed in this program will provide excellent thermal and electrical insulation capabilities. The technology is ideal for numerous applications. For instance, it can be used in military or commercial aircraft, and in the hulls of ships. In addition, these novel microfoams can be used as laminates for circuit boards or in other electronics. In automobiles, the foam can be used for the firewall behind the engine or in brake pads, trim, molded plastic parts, and other care elements. They also can be used in a variety of construction applications or in recreational equipment. Other attributes of these materials are their excellent chemical resistance, low outgassing, superior radiation resistance, and excellent wear performance. In addition, the novel cellular material is an ideal core material for composite structures in aircraft industry such as luggage bins, galleys and lower wall panels. We anticipate that parts made from these materials will be excellent replacements for metals, ceramics, and other engineering polymers.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Thermal Insulating Materials
Fluid Storage and Handling
Composites
Organics/Bio-Materials


PROPOSAL NUMBER: 09-2 X9.01-8952
PHASE-1 CONTRACT NUMBER: NNX10CC52P
SUBTOPIC TITLE: Ablative Thermal Protection Systems
PROPOSAL TITLE: Phenolic Impregnated Carbon Ablator (PICA) Gap Filler for Heat Shield Assemblies

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Fiber Materials, Inc.
5 Morin Street
Biddeford, ME 04005-4497
(207) 282-5911

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Violette
sviolette@fibermaterialsinc.com
5 Morin Street
Biddeford,  ME 04005-4414
(207) 282-5911

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
During this program, Fiber Materials, Inc. (FMI) will develop practical methods for preparing Phenolic Impregnated Carbon Ablator (PICA) materials for joining thermal protection system segments and penetrations of the heat shield assembly. Current and future mission flight environments and designs, such as those for Mars Science Laboratory Aeroshell (MSLA) and anticipated for New Frontiers and Mars EDL missions, will be assessed. Capability of the developed solution(s) will address mechanical and thermal robustness, and performance under representative mission heating environment. The Phase 1 program evaluated candidate joining and gap-fill materials, and assessed joining design approaches for cost effective manufacturability and assembly. Material joining design, assembly methodology and material test performance was documented. The Phase 2 program will utilize materials developed during the Phase 1 program to test performance under representative environment(s). A down-selected material-joining approach will result in the design and fabrication of a mission-specific PICA sub-assembly. The prototype sub-assembly will demonstrate assembly methods and the prototype materials will be utilized for characterization and performance testing. The proposed materials, designs and methods are TRL <=3. It is anticipated that TRL=>6 will be achieved at the conclusion of a successful phase 2 program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Stardust Sample Return Capsule completed its objective with earth reentry in January 2006. Mars Science Laboratory Aeroshell heat shield has been completed and delivery of the Curiosity rover to Mars is scheduled for 2015. With the successful fabrication of PICA TPS heat shields in support of NASA flight missions, FMI has quoted and is prepared to continue supporting PICA heat shields for NASA missions. FMI is actively involved in the study of PICA application for two New Frontiers sample return missions, and Mars EDL mission. The program proposed will assist FMI in support of these missions and extend PICA utility to additional mission application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
PICA coupled with joining and gap-fill solutions developed under this program would support commercial space operations including Commercial Orbital Transportation Services (COTS) and space study missions. During 2008, NASA entered into contracts with Orbital Sciences and SpaceX to utilize their COTS cargo vehicles, Cygnus and Dragon respectively, for cargo delivery to the International Space Station (ISS). PICA is an enabling technology for this effort. FMI has recently quoted PICA TPS for the Reentry Breakup Recorder application. It is reasoned that similar application opportunities will result from continued space commercialization efforts.

TECHNOLOGY TAXONOMY MAPPING
Ablatives


PROPOSAL NUMBER: 09-2 X9.01-9440
PHASE-1 CONTRACT NUMBER: NNX10CC53P
SUBTOPIC TITLE: Ablative Thermal Protection Systems
PROPOSAL TITLE: Computational Tool for Coupled Simulation of Nonequilibrium Hypersonic Flows with Ablation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corp.
215 Wynn Drive, 5th Floor
Huntsville, AL 35805-1944
(256) 726-4858

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sarma Rani
sxh@cfdrc.com
215 Wynn Dr.
Huntsville,  AL 35805-1944
(256) 726-4850

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this SBIR project is to develop a predictive computational tool for the aerothermal environment around ablation-cooled hypersonic atmospheric entry vehicles. This tool is based on coupling the relevant physics models to the LeMANS code for hypersonic flows and to the MOPAR code for material response, both developed by the University of Michigan. In Phase I of this project, we developed an efficient, high-fidelity 3-D radiation transfer equation (RTE) solver based on the Modified Differential Approximation (MDA). The MDA method was shown to be accurate over at least three orders of magnitude variation in medium optical thickness, typical in entry hypersonic flows. The coupled LeMANS-radiation code was demonstrated for Stardust and IRV2 configurations, while the coupled LeMANS-MOPAR code was validated for the Passive Nosetip Technology (PANT) experiment [1], successfully establishing feasibility. In Phase II, the primary focus is to advance the flow and ablation modeling capabilities of the LeMANS/MOPAR codes by including innovative models for: (1) Non-equilibrium surface thermochemistry; (2) Non-equilibrium pyrolysis chemistry; and (3) Non-gray, non-equilibrium radiation. All models will be implemented in a modular manner with particular attention paid to their coupling interfaces to facilitate easy coupling to a computational aerothermodynamics code of interest to NASA such as DPLR. The tool will be validated and applied to ablation-cooled re-entry flow problems relevant to NASA such as the Stardust capsule.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future NASA missions will be more demanding and will require better performing ablative TPS than currently available. The proposed SBIR project will result in a computational tool with unique, comprehensive, and accurate predictive capabilities for ablative TPS performance in hypersonic, non-equilibrium atmospheric entry flows. The tool will find direct application in NASA technology development programs such as the In-Space Propulsion Technology Program, and also in NASA's Fundamental Aeronautics Hypersonics (FAH) Project that aims to develop methods, tools and data that enable emergence of highly reliable and efficient hypersonic systems. The tool can also be used to aid in the design and development of next-generation planetary vehicles (such as the Crew Exploration Vehicle, Mars Aerocapture and Mars Sample Return spacecraft) and components of future hypersonic vehicles. The various models comprising the tool will be implemented in an extensible and modular framework that can be ported to other NASA codes (e.g. DPLR) with relative ease.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Technology applications beyond NASA include the Theater and National Missile Defense vehicles performing exo-atmospheric missile intercepts, and missile warhead re-entry applications. The computational tool will also be relevant to the joint DOD/NASA effort called the National Aerospace Initiative (NAI) that involves, among other things, the development of air-breathing hypersonic vehicles. OEMs will also find the tool useful in exploring and designing newer and more robust ablative TPS materials and heat shield systems. The models developed in this SBIR project can also be ported to commercial CFD software such as ATAC, Fluent, CFD-ACE+ and CFD-FASTRAN.

TECHNOLOGY TAXONOMY MAPPING
Ablatives
Thermal Insulating Materials


PROPOSAL NUMBER: 09-2 X9.02-8827
PHASE-1 CONTRACT NUMBER: NNX10CC54P
SUBTOPIC TITLE: Advanced Integrated Hypersonic Entry Systems
PROPOSAL TITLE: Multi-Layered Integrated Airframe System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Fiber Materials, Inc.
5 Morin Street
Biddeford, ME 04005-4497
(207) 282-5911

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Benjamin Dwyer
bdwyer@fibermaterialsinc.com
5 Morin Street
Biddeford,  ME 04005-4414
(207) 282-5911

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposed Phase II program builds on the Phase I effort addressing NASA's future mission requirements by: 1) developing higher performing TPS materials capable of meeting the demands of multiple severe mission trajectories; and 2) integrating TPS materials with the sub-structure to improve overall robustness and decrease mass. The program's goal is to extend Phenolic Impregnated Carbon Ablator (PICA) and Fiber Materials, Inc. (FMI<SUP>REG</SUP>) Integrated Composite Structure (ICS) TPS materials to a broader range of flight heat fluxes and mission performance requirements to address future heatshield design needs. Specific mission enabling improvements sought by NASA that will be developed and/or demonstrated under this Phase II program include: preform/component size, ablation performance, thermal insulation performance, efficient and extendable assembly process, and net-shape preform casting.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Stardust Sample Return Capsule completed its objective with earth reentry in January 2006. Mars Science Laboratory Aeroshell heat shield has been completed and delivery of the Curiosity rover to Mars is scheduled for 2015. With the successful fabrication of PICA TPS heat shields in support of NASA flight missions, FMI has quoted and is prepared to continue supporting PICA heat shields for NASA missions. FMI is actively involved in the study of PICA application for two New Frontiers sample return missions, and Mars EDL mission. The program proposed will assist FMI in support of these missions and extend PICA utility to additional mission application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed multi-layered integrated airframe concept will be applicable to commercial space vechiles, as well as NASA vehicles. Advances in the individual PICA and integrated composite structure technologies will be advantageous for DoD applications, including Missile Defense interceptor airframes, and aeroshell/insulation systems for Air Force and AMRDEC extended-flight vehicles.

TECHNOLOGY TAXONOMY MAPPING
Ablatives


PROPOSAL NUMBER: 09-2 X9.02-9443
PHASE-1 CONTRACT NUMBER: NNX10CC55P
SUBTOPIC TITLE: Advanced Integrated Hypersonic Entry Systems
PROPOSAL TITLE: Integrated Inflatable Ballute for Planetary Entry

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corp.
215 Wynn Drive, 5th Floor
Huntsville, AL 35805-1944
(256) 726-4858

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Essam Sheta
sxh@cfdrc.com
215 Wynn Dr.
Huntsville,  AL 35805-1944
(256) 726-4869

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
CFDRC and TRLA are proposing to develop, design and test a highly scalable, mass-optimized inflatable structure that makes maximum utilization of materials in providing tailored stiffness and rigidity for hypersonic entry vehicles. The proposed inflatable structure is a hybrid pressure restraint vessel employing an impervious cloth-reinforced barrier structure enveloped by an integrated array of high-tenacity tendons. The external grid of cordage tendons provides mass- and load pathway-optimized containment of the structure's global pressure loads. In Phase I, the conceptual model was designed and the materials were evaluated for their stiffness. The feasibility of the model was demonstrated for typical Mars trajectory point. Phase II efforts will focus on fabricating and testing a prototype of the proposed inflatable structure to validate the design robustness and capability for larger payload masses. Pre and post testing multidisciplinary integrated fluid-structure-thermal simulations will be conducted to provide insight into the aerodynamic, material stress and dynamic characteristics of the model and to verify/optimize the developed design. Wind tunnel testing as well as dynamic aerostructural simulations will be conducted to verify the stability of the model. The developed inflatable concept will be fabricated complete with flexible TPS, multiple protection layers and sensors and will be tested to demonstrate the prototype folding, packaging, and deployment.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed integrated hypersonic inflatable entry system will have an immediate application in delivering large payload masses to the surface of Mars. This will reduce the number of launches required for the mission completion and total mission costs. The proposed technology will find direct applications with present and future NASA and industry inflatable structures programs, such as those seeking to provide deceleration and precision landing capability for large scale mass return from Earth orbit to Earth surface, or for missions to many of the potential atmosphere-endowed solar system destinations. Other NASA applications include large aperture antenna reflectors, solar collectors, cryogenic propellant tanks, lander air bags, and rover vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Additional application areas include analysis of space-based inflatable structures such as telescopes and mirrors, satellite solar panels and military reentry vehicles (inflatable decoys, etc) exposed to the atmosphere. The aeroelastic analysis of parachutes and parafoils and the analysis of high-altitude endurance airplanes with flexible wings will be improved. Further military applications include stabilization and deceleration of ordnance with attached inflatable decelerators. Other non-NASA applications include satellite de-orbit device, compressed air energy storage, high altitude airships, oil storage containers, helicopter and motor vehicles crash air bags and launch vehicle payload fairings.

TECHNOLOGY TAXONOMY MAPPING
Inflatable
Simulation Modeling Environment
Testing Requirements and Architectures
Structural Modeling and Tools
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 X10.01-8636
PHASE-1 CONTRACT NUMBER: NNX10CD15P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: Low-Cost, High-Performance Combustion Chamber for LOX/CH4 Propulsion, Phase II

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ultramet
12173 Montague Street
Pacoima, CA 91331-2210
(818) 899-0236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Arthur Fortini
art.fortini@ultramet.com
Ultramet
Pacoima,  CA 91331-2210
(818) 899-0236

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this project, Ultramet is designing and fabricating a lightweight, high temperature combustion chamber for use with cryogenic liquid oxygen/methane (LOX/CH4) propellant that will deliver a specific impulse of ~355 seconds, an increase over the current 320-sec baseline that will result in a propellant mass decrease of 55 lbm. The material system is based on Ultramet's proven oxide-iridium/rhenium architecture, which has been successfully hot-fire tested with stoichiometric oxygen/hydrogen for hours. Instead of rhenium, however, the structural material will be a niobium or tantalum alloy that has excellent yield strength at both ambient and elevated temperature. Phase I demonstrated alloys with yield strength-to-weight ratios more than three times that of rhenium, which will significantly reduce chamber weight. The starting materials are also two orders of magnitude less expensive than rhenium and are less expensive than the C103 niobium alloy commonly used in low-performance engines. Phase II will focus on the design, fabrication, and hot-fire testing of a small (5-25 lbf thrust class) chamber with LOX/CH4, and will culminate in the design and fabrication of a 100-lbf chamber that can be mated and tested with an existing LOX/CH4 injector. Throughout the project, Ultramet will work closely with Aerojet, which will perform the hot-fire testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
For cryogenic LOX/CH4 engines in the 5- to 100-lbf thrust class, potential NASA applications include reaction control systems for lunar or Martian ascent/descent vehicles, lunar or Martian sample return vehicles, and main engines for interplanetary spacecraft and spacecraft being placed into geostationary orbit. The material technology can also be used with Earth-storable propellants such as nitrogen tetroxide/monomethyl hydrazine (NTO/MMH), where the primary application would be apogee topping engines and attitude control systems for Earth-orbiting satellites. The technology can be applied to launch vehicles for attitude control as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial applications include apogee topping engines for commercial satellites as well as attitude control thrusters for launch vehicles. Military applications include both primary propulsion and divert and attitude control system functions for ballistic missile defense and tactical missiles. Because the proposed combustion chambers can be used with storable propellants such as NTO/MMH, they could be used as drop-in replacements for iridium/rhenium engines currently being manufactured and flown.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Metallics


PROPOSAL NUMBER: 09-2 X10.01-8831
PHASE-1 CONTRACT NUMBER: NNX10CD16P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: Carbon-Carbon High Melt Coating for Nozzle Extensions

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Carbon-Carbon Advanced Technologies, Inc.
4704 Eden Road
Kennedale, TX 76060-6800
(817) 985-2500

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Thompson
jthompson@c-cat.net
4704 Eden Road
Kennedale,  TX 76060-6800
(817) 985-2500

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The High Melt Coating system is applied to a carbon-carbon structure and embeds HfC, ZrB2 in the outer layers. ACC High Melt builds on the time tested base material system of T-300 fibers, impregnated with phenolic resin, pyrolyzed, densified, and SiC Conversion coated For Phase 2, C-CAT proposes to team with Pratt and Whitney Rocketdyne to fully develop High Melt into a material system that when combined with the appropriate design will produce nozzle extensions for future NASA spacecraft. PWR will supply the designs for a notional nozzle extension for a 2000 lbf LOX/LCH4 lunar descent engine and a nozzle extension for a notional lunar ascent engine sized at 5500 lbf LOX/LCH4. Objectives: C-CAT engineering will work with PWR designers to insure that the nozzle extension design for each prototype is both manufacturable and will meet the technical requirements. C-CAT engineering will design and C-CAT will fabricate lay-up tools that will take into account ply shrinkage distortion and still maintain dimensional tolerances during processing. Lay-up the nozzle extensions without defects Process each nozzle extension through pyrolysis, heat treatment and coating without defects. Apply SiC Conversion Coating to the ACC High Melt material without spalling.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are a variety of NASA programmatic needs for advanced combustion devices, notably nozzle extensions for upper and exo-atmospheric operation that benefit from the unique materials properties offered by the ACC High Melt material system. A partial list of NASA programs that would derive benefit are robotic lunar or Mars missions like Project M, human lunar ascent, and J-2X. Additionally, ACC High Melt is a material system that can be used as a structural, re-usable TPS system for future spacecraft. The continued development of this material for nozzle extensions will lead to a more in depth understanding of the manufacturability and structural properties that can be applied to the TPS designs of future spacecraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Pratt & Whitney Rocketdyne is currently developing an 800 lbf LOX/LCH4 upper stage engine for commercial nanosatellite launch capability. The nozzle extension has an inlet plane diameter of 8", an exit plane diameter of 10.5", and an axial length of 11",. The propulsion system is optimized for cost and weight, with the carbon-carbon nozzle extension offering a significant weight and schedule savings versus traditional, thin-wall metallic designs. The fabrication of the design is rather simple and was focused on lightweight attachment mechanisms that were readily producible, in this case, direct bolting into a single-use ablative thrust chamber. As with other upper stage or exoatmospheric engines, the nozzle extension was designed to run in a radiation-cooled mode only, thereby benefiting directly from the superb operating temperatures offered by carbon-carbon. Additional benefits of a successful Phase 2 SBIR will be to demonstrate scale-up of ACC High Melt for non-engine applications. These applications include structural TPS for aircraft that require multiple uses at temperatures in excess of 2800<SUP>o</SUP>F. This need exists at both NASA and the Department of Defense for hypersonic space plane applications

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Reuseable
Ceramics
Composites


PROPOSAL NUMBER: 09-2 X10.01-9015
PHASE-1 CONTRACT NUMBER: NNX10CD18P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: Regeneratively-Cooled, Turbopump-Fed, Small-Scale Cryogenic Rocket Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ventions, LLC
1142 Howard Street
San Francisco, CA 94103-3914
(415) 543-2800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Adam London
adam.london@ventions.com
1142 Howard Street
San Francisco,  CA 94103-3914
(415) 543-2800

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To-date, the realization of small-scale, high-performance liquid bipropellant rocket engines has largely been limited by the inability to operate at high chamber pressures in a regeneratively-cooled environment using on-board pumps for propellant pressurization. Ventions seeks to fulfill this critical need by using a novel fabrication scheme to realize small-scale thrust chambers and turbopumps, and proposes to extend its previously-demonstrated technologies (under DARPA and NASA sponsored efforts) to develop a 3,000lbf, regeneratively-cooled, cryogenic propulsion system with a T/W ratio of approx. 100 and a vacuum Isp up to 355sec.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed pump concept overcomes a key challenge of providing on-board pressurization for high-performance rocket engines in the small size-class. Hence, upon integration with other propulsion system components (thrust chamber, valves, tanks, etc.), it serves as critically-enabling technology for a new generation of liquid bipropellant rocket engines in the 50-5,000lbf thrust class. Additionally, these turbopump and thrust chamber assemblies may be batch fabricated in a cost-effective manner and modularly stacked, thereby covering a wide range of NASA exploration applications, including nano-sat launch, lunar ascent / descent(precursors, rovers, cargo, man-rated vehicles, etc.), planetary missions (payload ascent vehicles for payload and orbiting sample placement into orbit, sample return, etc.), and Near-Earth-Object (NEO) missions (sample return).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications for high-performance micro-rocket engines enabled by the proposed pump technology are likely to include commercial / military launch vehicles for low-cost and on-demand access to space for a variety of micro / small satellite payloads, upper stage propulsion for orbit insertion of commercial satellites, apogee kick motors for orbit circularization of commercial satellites, etc. Additionally, the pump itself is expected to have non-aerospace applications in industrial cryogenic pumping applications, and as a replacement for small-scale, high-pressure liquid pumps.

TECHNOLOGY TAXONOMY MAPPING
Micro Thrusters
Feed System Components
Fluid Storage and Handling


PROPOSAL NUMBER: 09-2 X10.01-9134
PHASE-1 CONTRACT NUMBER: NNX10CD19P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: Propellant Flow Actuated Piezoelectric Rocket Engine Igniter

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Innovative Engineering Solutions
26200 Adams Avenue
Murrieta, CA 92562-7060
(951) 304-7600

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Wollen
mwollen@iesnet.com
26200 Adams Ave
Murrieta,  CA 92562-7060
(619) 593-7750

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Under a Phase 1 effort, IES successfully developed and demonstrated a spark ignition concept where propellant flow drives a very simple fluid mechanical oscillator to excite a piezoelectric crystal. The Phase 1 effort exceeded expectations, with the device demonstrating reliable ignition of both hydrogen and propane fuels, and achieving in excess of 1 million impact cycles (40,000 start cycles) during fatigue testing without measureable degradation. Several spin-off concepts were also identified that provide additional options for improving spark ignition system design. For Phase 2, IES proposes an accelerated, 18 month effort to refine design concepts and analysis tools, and then develop specific ignition system designs for two customer applications, with the intention of having these ignition systems demonstrated in engine ground testing during Phase 2 and ready to start flight qualification immediately following the Phase 2 effort. Both customers (United Launch Alliance and Pratt Whitney Rocketdyne) have expressed interest and commitment in participating in the Phase 2 activity, making engines and facilities available for development testing, and integrating any resulting viable products into their flight engines. The ULA application is a new gaseous bipropellant H2/O2 attitude control thruster, for which the piezoelectric igniter is ideal as a simple, direct ignition source. The PWR application is for an evolved RL-10 study currently underway, for which the piezoelectric system might be scaled up or used as a pilot igniter for a torch, or make use of another spin-off concept that was identified during the Phase 1 effort. The timing of this Phase 2 effort coincides perfectly with near term needs of both these customers, as well as for other small engine applications in work to replace catalytic hydrazine engines with bi-propellant engines that will require a simple and reliable ignition source.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Two specific commercial customers that regularly provide services for NASA have identified strong interest in this technology, with intent to implement the technology if Phase II development is successful. One application is a new gaseous H2/O2 attitude control and settling thruster currently under development by United Launch Alliance (ULA) for Atlas upper stage. The second application is a new ignition system for the Pratt and Whitney Rocketdyne (PWR) evolved RL-10 engine. Both ULA and PWR have stated their interest and intention to provide facility access and test opportunities concurrent with any Phase II effort. A third potential application is for ignition of any bi-propellant thrusters to be installed on the CRYOTE (Cryogenic Orbital Testbed) currently of interest to NASA and ULA. This testbed might use either the ULA thrusters mentioned above, or another engine identified by NASA. Numerous other NASA applications for very simple spark igniters are inevitable as small catalytic monopropellant (hydrazine) thrusters are replaced by cleaner bipropellant thrusters for satellite and upper stage attitude control purposes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aside from the ULA and PWR applications mentioned above (both of which also provide non-NASA services to commercial satellite operations and military customers such as Air Force), other potential commercial aerospace and industrial applications include gas turbine igniters for aircraft or ground power applications, furnace combustor ignition, flare stack ignition systems for hydrogen or methane, etc.

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
Micro Thrusters
Fluid Storage and Handling
Manned-Maneuvering Units
Ceramics
Combustion


PROPOSAL NUMBER: 09-2 X10.01-9473
PHASE-1 CONTRACT NUMBER: NNX10CD20P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: Non-Toxic Ionic Liquid Fuels for Exploration Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Orbital Technologies Corporation
Space Center, 1212 Fourier Drive
Madison, WI 53717-1961
(608) 827-5000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Millicent Coil
coilm@orbitec.com
1212 Fourier Drive
Madison,  WI 53717-1961
(608) 229-2812

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ORBITEC proposes to develop and test new, non-toxic ionic liquid fuels for propulsion applications. Vintage propulsion systems frequently use highly toxic propellants such as MMH. The toxicity of these propellants increases not only the risk of the missions but also the expense, due to special handling required during the entire lifetime of the propellant. Replacing toxic propellants with strong-performing, non-toxic formulations will significantly reduce the cost of propulsion systems. The Phase I project demonstrated the feasibility of developing several ionic liquid formulations that essentially equaled MMH in performance while offering low volatility and low toxicity. The Phase II work will continue the synthesis strategy to refine the formulations, conduct more extensive material property testing, conduct ignition delay tests, and demonstrate the fuels in a small-scale thruster. The collective result of these tasks will be the development and demonstration of new, safer fuels for propulsion applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Because of their good performance and low toxicity, these storable fuels will be suitable for a number of NASA propulsion applications. These new fuels could be used in reaction control systems for NASA's in-space science missions, lunar missions, satellites, or any future manned flights.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The applications for these ionic liquid fuels in the military and civilian sectors exceed even the abundant NASA applications. These storable non-toxic fuels are suitable for many kinds of tactical systems including missiles, ballistic defense systems, and satellites. Many opportunities exist in all branches of the military.

TECHNOLOGY TAXONOMY MAPPING
Chemical
High Energy Propellants (Recombinant Energy & Metallic Hydrogen)


PROPOSAL NUMBER: 09-2 X10.01-9575
PHASE-1 CONTRACT NUMBER: NNX10CD21P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: Magnetically Actuated Seal

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Florida Turbine Technologies, Inc.
1701 Military Trail, Suite 110
Jupiter, FL 33458-7887
(561) 427-6400

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alex Pinera
APinera@fttinc.com
1701 Military Trail, Suite 110
Jupiter,  FL 33458-7887
(561) 427-6277

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
FTT proposes development of a magnetically actuated dynamic seal. Dynamic seals are used throughout the turbopump in high-performance, pump-fed, liquid rocket engines for a variety of purposes. The most common applications are in the lift-off seal (LOS), inter-propellant seal (IPS), and balance piston seals ? high-pressure orifice (HPO), low-pressure orifice (LPO), and inner diameter impeller shroud seal (eye seal). The system solution for conventional seals represents a compromise between the turbopump mechanical design, primarily flowpath, and secondary flowpath design that results in increased leakage, increased seal wear, and reduced balance piston load capacity that reduces performance, throttle-ability, thrust-to-weight, reliability, and operability. The magnetically actuated seal eliminates this compromise and provides significant improvement in performance, throttle-ability, thrust-to-weight, reliability, and operability. Phase 1 resulted in a significant advancement of the technology by demonstrating a magnetically actuated face seal in both ambient and cryogenic conditions, characterizing the seal and actuator performance, and quantifying the performance improvements for the turbopump and engine. Phase 2 will advance the technology from TRL 3 to 5. The technology is applicable to booster engines, in-space engines, and ascent/descent engines.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The anticipated benefits from this technology include reduced seal leakage (for improved efficiency, and reduced turbine inlet temperature, which improves reliability), reduced seal wear (which increases life and reliability), reduced or eliminated purge (which improves operability and reduces weight), eliminates primary and secondary seal drains and associated plumbing and valves (which improves reliability and reduces weight), and improves design point and off-design balance piston performance (which increases the throttle range). This technology is directly applicable to booster engines, in-space engines, and ascent/descent engine for NASA applications including booster and upper stage engines planned for HLLV.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting technology is directly applicable to address the seal wear issue in the commercial pump industry, dynamic seals in FTT's family of small UAV turbofan engines as well as for active clearance control systems in large aero engines and industrial gas turbine engines. These product lines have the potential demand for more than 10,000 units annually.

TECHNOLOGY TAXONOMY MAPPING
Feed System Components


PROPOSAL NUMBER: 09-2 X10.01-9928
PHASE-1 CONTRACT NUMBER: NNX10CD22P
SUBTOPIC TITLE: Cryogenic and Non-Toxic Storable Propellant Space Engines
PROPOSAL TITLE: UCDS Based Stable Injector Design

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Gloyer-Taylor Laboratories, LLC
2212 Harton Blvd.
Tullahoma, TN 37388-5583
(931) 393-5108

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Gloyer
paul.gloyer@gtlcompany.com
2212 Harton Blvd.
Tullahoma,  TN 37388-5583
(931) 393-5108

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
History has repeatedly shown that combustion instability is the greatest technical risk faced in any chemical propulsion development program. The UCDS Process addresses this issue by using a rigorous physics-based analytical framework to decompose the complex flow field inside a chemical propulsion device, such as a liquid or solid rocket, in a way that allows rapid simulation of the dynamic behavior. Using UCDS it is possible to generate high fidelity predictions of the time evolution, amplitude and waveform of a pressure oscillation, along with any changes to the mean properties due to non-linear effects. Furthermore, it has been shown that the modal Alpha (linear growth rate) is a key physical parameter that defines the dynamic behavior of a rocket and provides a reliable measure of combustion stability margin. By monitoring how the array of modal Alphas change with design or operational features, the effects on engine combustion stability can be predicted. This insight provides the means to eliminate instability without resorting to expensive cut-and-try iterative developmental testing. GTL proposes to use this design guideline and the UCDS<SUP>TM</SUP> Process to create a clean-sheet design for a new liquid rocket that is inherently stable and compare it to an existing engine.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
As a physics-based tool, the UCDS Process is applicable to practically any chemical propulsion systems, including liquid rocket engines, solid rocket motors, turbojets and scramjets. With UCDS, it is possible to either fix an existing engine that has oscillations or design new engines that are inherently stable. This will greatly reduce development costs by eliminating the need to rely on expensive cut-and-try testing. Additionally, UCDS provides the means to explain the dynamic behavior of engine. This added insight and reduced development risk may lead to great advances in engine performance and capability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The UCDS Process is equally applicable to NASA and non-NASA chemical propulsion systems, since UCDS is not restricted by propellant type or engine size. Therefore UCDS can support DoD propulsion development efforts from small storable propellant thrusters to large cryogenic engines to complex tactical interceptor solid rocket motors and many others. Additionally, UCDS could play a critical role in the commercialization of space by reducing the cost and risk of commercial rocket development.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Fundamental Propulsion Physics
Monopropellants
Simulation Modeling Environment


PROPOSAL NUMBER: 09-2 X11.02-9753
PHASE-1 CONTRACT NUMBER: NNX10CD23P
SUBTOPIC TITLE: EVA Suit Simulator
PROPOSAL TITLE: Space Suit Simulator (S3) for Partial Gravity EVA Experimentation and Training

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aurora Flight Sciences Corporation
9950 Wakeman Drive
Manassas, VA 20110-2702
(703) 369-3633

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jessica Duda
jduda@aurora.aero
1 Broadway, 12th Floor
Cambridge,  MA 02142-1189
(617) 500-0552

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Pressurized space suits impose high joint torques on the wearer, reducing mobility for upper and lower body motions. Using actual space suits in training or experimentation is problematic due to the expense, bulk, weight, and difficulty in donning/doffing. The goal of this project was to demonstrate a novel method for simulating space suit joint torques, which are non-linear and vary with angular position. We designed a knee joint simulator using McKibben actuators with active control (also known as artificial muscles), which are cylindrical pneumatic actuators constructed of flexible rubber with an inextensible weave that causes the cylinder to contract longitudinally when pressurized. A commercial knee brace was used as an exoskeleton to mount the actuators. One actuator was mounted anterior to the knee to provide resistance to flexion, and a second actuator was mounted posterior to the knee to provide resistance to extension. The active controller read angle input from a potentiometer mounted to the brace and output the appropriate pressures for each actuator to provide the needed torque. The knee joint was installed on MIT's Robotic Space Suit Tester (RSST), a full-sized anthropometric robot equipped with torque and angle sensors on each of the joints. Results from testing indicated that the torque vs. angle relationship achieved using the actively controlled spacesuit joint simulator was qualitatively similar to the non-linear trend observed in prior testing of the EMU on the RSST. We conclude that the use of these actuators potentially results in higher fidelity than passive actuation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary customer for this device will be NASA. The timing of this Phase 2 effort is important to facilitate planned microgravity and lunar and martian surface EVA research and training in support of NASA's current vision for future exploration missions. Development of surface operations activities on the moon or Mars will benefit from the support of human testing and training; e.g. what is the metabolic cost of performing specific tasks in partial gravity while wearing a space suit? Additionally, experimentation in support of development of the future moon/Mars EVA space suit will require human testing; our adjustable space suit simulator joint torques will allow for characterization of various suit configurations in order to optimize the future suit design. We anticipate that EVA S3 systems will be used to support training and simulation activities at multiple centers including JSC, GRC, and ARC, and that this market will require initial production of 10 to 15 systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Joint torque devices such as those developed during this program are useful in medical technologies as orthopedic devices: either restricting motion in order to prevent injury, or providing resistance to motion in order to improve muscle function or promote bone growth. For example, a controlled resistance suit could be used as an exercise device (e.g. performing squats with a controlled resistance suit rather than with weights) or individual components of the EVA S3 design could be used separately for rehabilitation of specific joints. Alternately the control scheme can be changed to provide performance augmentation to the wearer. To support these various markets, the EVA S3 technology is adjustable to accommodate individuals of different heights and weights, is rugged, portable, has low power requirements and is compatible with under water operations.

TECHNOLOGY TAXONOMY MAPPING
Suits


PROPOSAL NUMBER: 09-2 X12.02-9125
PHASE-1 CONTRACT NUMBER: NNX10CE37P
SUBTOPIC TITLE: Behavioral Health Monitoring Tools
PROPOSAL TITLE: Individualized Behavioral Health Monitoring Tool

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pulsar Informatics, Inc.
3624 Market Street, Suite 5E
Philadelphia, PA 19104-2685
(215) 520-2630

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Daniel Mollicone
daniel@pulsarinformatics.com
3624 Market Street, Suite 5E
Philadelphia,  PA 19104-2685
(215) 520-2630

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Given the extended duration of future missions and the isolated, extreme and confined environments, there is the possibility that behavioral conditions and mental disorders (DSM-IV-TR) will develop. The overarching goal of this project is to deliver an Individualized Behavioral Health Monitoring Tool that unobtrusively integrates all available behavioral measures collected during a mission to provide a dashboard of behavioral health indicators. These indicators will be placed within the context of quantitatively-tracked mission stressors to provide meaningful feedback allowing behavioral issues to be detected and mitigated at an early stage. The result of this project will be a system prototype that can be deployed in space analog environments (e.g., Mars 520 study, Antarctica) for validation testing and ultimately deployed in long-duration space exploration missions. The critical need for an Individualized Behavioral Health Monitoring Tool has been identified as a priority outlined in the BHP Integrated Research Plan (July 2009) gap BMED3. Phase II will achieve: (1) an Individualized Behavioral Health Monitor software interface; (2) a data integration system; (3) a trend and change detection algorithm; and (4) a countermeasure selection aid. The Technology Readiness Level at the end of Phase II will be TRL 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Individualized Behavioral Health Monitoring Tool will meet the specific requirements of long duration exploration missions and provide feedback to astronauts, Op Psy Personnel and Flight Surgeons about behavioral health status as well as aid in the selection of countermeasures. It will be designed to be unobtrusive and require minimal crew time or effort to train and utilize. The resulting product will be primarily relevant to NASA's Behavioral Health and Performance (BHP) research gaps (as of July 2009): BMED 3 (What are the optimal methods to detect and assess decrements in behavioral health during exploration missions?) but will also be relevant to gaps BMED1, BMED2, BMED6, BMED7, and BMED8. When validated, the Individualized Behavioral Health Monitoring Tool will be deployed in long-duration space exploration missions to support crew behavioral health efforts during training, mission and return to Earth.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Individualized Behavioral Health Monitoring Tool can be adapted to meet an articulated need to track behavioral health in occupations associated with high stress, high workload and high danger factor such as military applications and law enforcement. A tool that enables the systematic and efficient tracking of individual behavioral health status in these occupational settings can provide a means to detect and address behavioral disorders and mental conditions at an early stage. Taking military operations as an example, there is evidence that behavioral disorders and mental conditions such as depression, post-traumatic stress disorder, and traumatic brain injury have a high prevalence among soldiers. There is a present market opportunity to deliver an Individualized Behavioral Health Monitoring Tool to track changes in behavioral health status in soldiers during training, deployment, and post-deployment. The Army currently has 238,000 soldiers deployed overseas in 120 countries (source: US Army, 2006).

TECHNOLOGY TAXONOMY MAPPING
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Database Development and Interfacing
Expert Systems
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 X13.01-9342
PHASE-1 CONTRACT NUMBER: NNX10CE39P
SUBTOPIC TITLE: An Automated Tool for Human Factors Evaluations
PROPOSAL TITLE: Human Factors Analysis Support Tool (H-FAST)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TiER1 Performance Solutions
6 E. 5th Street, Suite 400
Covington, CO 41011-1512
(859) 663-2114

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Terence Andre
t.andre@tier1performance.com
6 E. 5th Street, Suite 400
Covington,  KY 41011-1512
(719) 213-4205

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Designing complex systems, such as those used by NASA, requires a coordinated effort among a variety of engineering teams. In order to be successful, the human-computer interactions in these systems need to follow a principle-based design process. In Phase II, TiER1 and Alion propose to continue development on HFE-AT, renaming it and creating a Human Factors Analysis Support Tool (H-FAST), which will provide human factors guidance and support to engineering design teams. This tool will be used throughout the design lifecycle, and will provide inputs to engineers and program managers to help them identify and avoid potential human factors problems early in the design process. It also will provide detailed guidance regarding human factors evaluations, and it will store data and provide feedback on the results of these evaluations. H-FAST will improve the engineering design process by providing engineers with easy access to detailed human factors methods, relevant research, and subject matter expert contact information. This will empower engineers to create more usable systems, thus reducing the number of design iterations and resulting in higher-quality products.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
H-FAST will provide a tool to support the engineering design process at NASA JSC. As such, it will be populated with human factors requirements and guidelines related to the design of systems for space exploration. The design patterns and methods will be chosen to support particular design issues related to NASA JSC missions. H-FAST will also provide a modular framework that can be customized to a variety of NASA engineering projects. By including relevant requirements, guidelines, methods, and design patterns, NASA project managers will be able to customize H-FAST for their particular application. We expect that H-FAST can be used to support space vehicle design projects; ground systems, such as mission control center designs; and flight deck design projects at NASA Ames and Langley. Human-in?the-loop research conducted at any NASA facility will provide relevant input to H-FAST. The technical reports and white papers will populate the library of H-FAST, and provide all NASA engineering H-FAST users with access to relevant human factors research results. H-FAST will provide a customizable tool to support a diverse range of engineering design projects with human performance implications. Examples include ergonomic design of large complex systems, human-computer interface design, control design, display layout.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Department of Defense Applications: We anticipate that H-FAST will provide a useful, nearly directly-usable tool for other agencies involved in large scale system acquisition. A key example is the Department of Defense (DoD). They, like NASA, are concerned with identifying and verifying human performance requirements in complex systems. They too would benefit from a tool that improves the design process by giving engineers tools and guidance to perform preliminary human factors assessments. For DoD customers, it would be necessary to include more Military Standard (MIL-STD) guidelines, project-specific requirements, and verification methods, to identify relevant design patterns for military applications, and to link to military-relevant research sources (e.g., Army Research Laboratory, Office of Naval Research). However, the basic framework provided by H-FAST would be readily usable by DoD customers. Entrepreneur Center Application: Another possible non-NASA commercial application of H-FAST would be as a market validation tool for an Entrepreneur/Business Incubation Center. In this application the primary user would be the new business founder, seeking to validate the market for their product or service.

TECHNOLOGY TAXONOMY MAPPING
Expert Systems
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 X13.03-9519
PHASE-1 CONTRACT NUMBER: NNX10CE41P
SUBTOPIC TITLE: Advanced Food Technologies
PROPOSAL TITLE: Advanced Cookware and Techniques for Food Preparation at Reduced Pressure and Gravity

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Makel Engineering, Inc.
1585 Marauder Street
Chico, CA 95973-9064
(530) 895-2770

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Susana Carranza
scarranza@makelengineering.com
1585 Marauder Street
Chico,  CA 95973-9064
(512) 512-0718

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Makel Engineering and Cornell University propose to develop a galley architecture taking into account the design constraints of the space habitat, such as reduced pressure and gravity, minimize size, mass, power and crew time, while producing food with high nutritional value and enough variety, acceptable taste and texture qualities for long term crew consumption. The current design of the space habitat will have a reduced atmospheric pressure of 8 psia which is equivalent to a 16,000 foot mountain top, with oxygen enrichment to prevent hypoxia effects on the crew. The combination of reduced pressure and gravity will affect the heat and mass transfer during food processing and food preparation of the food. Whether the food system is based chiefly on bulk packaged ingredients or crops grown on site, it must minimize mass, volume, power and waste, make effective use of the limited resource of crew time, produce nutritious, highly acceptable and varied food, and integrate into the closed habitat's atmospheric control system by containing and controlling airborne particulates, water vapor and odors generated during food preparation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed in Phase 2 will find near term applications in ground-based analog missions, where many of the subsystems will be tested. Portions of the technology (such as individual cookware items, or environmental control system) may be incorporated in flight demonstration missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Recent research indicates that the fumes generated in the kitchen, if not properly exhausted and treated, are rather detrimental to human health. While exhaust systems are common practice in residential kitchen, they are usually ill-equipped to treat noxious fumes, but rater focus on drawing air and trapping oil mist. Many kitchens, in particular in small urban spaces, use recirculation exhaust, which simple traps oil mist, but end up recirculating odor causing volatiles and any noxious chemicals (e.g., overheated oil, small food spills on hot surfaces, etc.). A derivation of a hood system with built-in treatment may be the development of convection ovens and microwave ovens with built-in odor control systems. These items are usually outside of the range of kitchen exhaust, but also are key sources of odors and indoor pollution.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Biomedical and Life Support


PROPOSAL NUMBER: 09-2 X14.01-9159
PHASE-1 CONTRACT NUMBER: NNX10CC44P
SUBTOPIC TITLE: Active Charged Particle and Neutron Radiation Measurement Technologies
PROPOSAL TITLE: Fast Neutron Dosimeter for the Space Environment

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Radiation Monitoring Devices, Inc.
44 Hunt Street
Watertown, MA 02472-4699
(617) 668-6801

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Christian
jchristian@rmdinc.com
44 Hunt St.
Watertown,  MA 02472-4699
(616) 668-6897

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Model calculations and risk assessment estimates indicate that secondary neutrons, with energies ranging between 0.5 to >150 MeV, make a significant contribution to the total absorbed dose received by space crews during long duration space missions [1-3]. Advanced scintillation materials, which exhibit radiation type and mass dependent emission times, coupled to SSPM detectors, provide the optimum volume to payload performance and the ability to easily discriminate between the fraction of dose, which results from secondary neutrons, and that which results from exposure to energetic charged particles and background gamma-rays. The Phase-1 effort successfully characterized the critical components of the proposed dosimeter, specifically, the response of the scintillation material to irradiation by gamma-rays, protons, and neutrons, as well as the performance of the SSPM detector. The Phase-1 modeling studies provide a critical foundation for assessing the anticipated signals in the space radiation environment. The proposed dosimeter would overcome many of the limitations in the current generation of neutron dosimeters, and would provide baseline information on the physics, needed with the information from biological studies, to assess risk in future human-space-exploration missions to the moon and Mars.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary target market for the fast-neutron dosimeter is NASA missions. Key missions are NASA missions that involve extended space-time, such as possible Moon and Mars missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
. Governmental and private sector space agencies across the globe will have similar needs for dosimeter devices. . International airlines, especially those investigating space tourism, such as Space X. . The commercial satellite market is a large and growing market that will be interested in monitoring space radiation. . Earth bound or terrestrial markets, including hospitals, national laboratories and industrial research, is the largest potential segment. This market does require some changes in the product design.

TECHNOLOGY TAXONOMY MAPPING
Particle and Fields
Ultra-High Density/Low Power
Highly-Reconfigurable
Photonics
Radiation-Hard/Resistant Electronics
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 X15.01-9505
PHASE-1 CONTRACT NUMBER: NNX10CE42P
SUBTOPIC TITLE: Alternative Methods for Ambient Preservation of Human Biological Samples during Spaceflight and Lunar Operations
PROPOSAL TITLE: Novel Fluid Preservation System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ChromoLogic, LLC
133 N. Altadena Drive, Suite 307
Pasadena, CA 91107-7328
(626) 381-9974

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nicholas Booth
nmenon@chromologic.com
133 N. Altadena Drive, Ste 307
Pasadena,  CA 91107-7340
(626) 381-9974

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To address NASA's need for a method to preserve human biological samples, mostly blood and urine, from astronauts collected during flight under ambient conditions, ChromoLogic (CL) has developed a novel Fluid Preservation System (FPS). FPS is based on collecting and sealing fluids in a sterile, hermetically sealed volume, with automatic separation of supernatant fluid where necessary. The unique microfluidic and medical expertise of CL scientists has resulted in an innovative and lightweight fluid storage system that utilizes compact and rugged microfluidic chips and novel valve technology that are capable of processing ~10ml of samples in a few minutes using on-board processing equipment. In Phase I CL has demonstrated the feasibility of the FPS technology by building prototype chips and demonstrating the proof of concept of pumping, separation, storage and preservation. The FPS has been demonstrated to be able to store blood plasma at room temperature for 54+ days. In Phase II CL will develop a fully functional system that will be FDA approved and space qualified.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The FPS will be used by NASA to collect and store bodily fluids such as blood, urine and saliva from astronauts with the aim of gaining a fuller understanding of the physiological effects of travel to and from and existence within a microgravity environment. Fluid samples will be able to be stored at ambient temperature over extended periods of time. Further applications of the FPS may present themselves in the field of extra terrestrial soil and bio-sample recovery and processing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA commercial applications exist in fields such as blood sample collection and storage by medical personnel operating in locations far from traditional preservation infrastructure. From third world counties to rural America medical practitioners that serve outlying areas are often constrained by the lack of a method of blood preservation, reducing the need to carry methods of refrigeration will increase the total amount of samples that can be collected and will increase the efficiency of man power used for such work. Other fields that will be targeted by the FPS are research and development environments. Civilian research applications include large epidemiological studies and remote field research, such as environmental research. There also exists many opportunities for use of the FPS by the military for bio-sample collection and management under challenging field conditions.

TECHNOLOGY TAXONOMY MAPPING
Biomass Production and Storage
Biomedical and Life Support
Sterilization/Pathogen and Microbial Control



PROPOSAL NUMBER: 09-2 S1.01-8384
PHASE-1 CONTRACT NUMBER: NNX10CD50P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Monolithic Rare Earth Doped PTR Glass Laser

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
OptiGrate Corporation
3267 Progress Drive
Orlando, FL 32826-3230
(407) 381-4115

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christine Spiegelberg
cspiegelberg@optigrate.com
3267 Progress Drive
Orlando ,  FL 32826-3230
(407) 381-4115

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The main goal of the project is to demonstrate the feasibility of a monolithic solid state laser on the basis of PTR glass co-doped with luminescent rare earth ions. The main feature of this new complex material is its ability to be simultaneously an active laser medium and a phase photosensitive medium. That way the same piece of material can be used as laser gain element and a monolithic laser resonator produced by the recorded in that volume Bragg gratings (VBGs). A series of PTR glasses co-doped with rare-earth ions (Nd, Yb and Er) was fabricated. It was shown that those glasses possess both high efficiency of luminescence and photosensitivity (photo-thermo-induced change of refractive index). A technology of the recording of volume Bragg gratings in each of these new PTR glasses was developed and controllable diffraction efficiency between 10 and 99% was demonstrated. A laser was demonstrated in Nd-doped PTR glass plate using an external Fabry-Perot resonator based on two plane dielectric mirrors with longitudinal pumping by laser diodes at 808 nm. Lasing and narrowing of spectrum down to ~20 pm is demonstrated when one of the mirrors was replaced by a high efficiency VBG.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Monolithic solid state laser created by recording volume Bragg gratings in PTR glass co-doped with luminescent ions enables a number of important applications resulted from its unique features V this laser will possess the best parameters as DFB and DBR semiconductor and fiber lasers (single frequency emission, compactness and extreme tolerance to vibrations and shocks) combined with best parameters of solid state lasers (high power and low cost). We will develop lasers working in both most usable region of 1064 nm and in eye safe regions of 1550 nm. The absence of elements in a resonator that could be misaligned makes this laser beneficial for spaceborne and airborne applications. This combination of features will make this new laser very beneficial for different NASA applications, which require extreme narrow spectral width combined with extreme compactness and robustness: spectral sensing, LIDARs, LADARs, spectroscopy, range finding, targeting, remote sensing, precise altimetry, etc.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Solid state lasers are in strong demand for different industrial and military applications because of high power, high quality of laser radiation and an opportunity of extremely narrow and stable emission lines. However, high sensitivity of those lasers to vibrations and shocks restrict their applications outside of academic environment. Creation of a monolithic solid sate lasers in most important spectral regions of 1 and 1.5 ?m will solve a lot of problems which restrain laser applications. The first obvious application is defectoscopy, laser marking, and different aspects of spectral analysis including Raman spectroscopy in industrial environment. The second obvious application is remote sensing, optical communication, target recognition, and spectral analysis of potential threats installed at different movable platforms in Air Force, Army, and navy. It is important that OptiGrate has positive experience in fabrication and delivery of narrow band lasers to both military and civilian organizations.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
Photonics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 S1.01-8403
PHASE-1 CONTRACT NUMBER: NNX10CE91P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: High Power Narrow Linewidth 1.26 Micron Ho-Doped Fiber Amplifier

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NP Photonics, Inc.
9030 S. Rita Road
Tucson, AZ 85747-9102
(520) 799-7424

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jianfeng Wu
jfwu@npphotonics.com
9030 S. Rita Road, Ste 120
Tucson,  AZ 85747-9102
(520) 799-7498

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal is for the development of an innovative, high power, and extremely reliable 1.26-micron Ho-doped fluoride fiber amplifier. The proposed fiber amplifier consists of a Ho-doped fluoride fiber pre-amplifier and power amplifier. Laser at 1187 nm will be used as a resonant pump laser source for Ho3+-doped fiber laser. High gain per unit length at 1.2 micron can be achieved in Ho-doped fluoride glass fiber due to the strong pump absorption at 1187 nm and strong emission at 1.2 micron transition. The proposed Ho-doped fiber amplifier will be implemented into a MOPA system with a 1.26 micron single frequency Ho-doped fiber laser. This type of fiber based seed laser is needed for remote sensing of O and O -N for measuring atmospheric pressure. Concurrent on-board O2 measurements using lines at 1.26 m to allow for the best relative compensation for aerosol scattering along the line-of-sight of the CO2 and O2 measurements. The particular O2 band was chosen so that the surface and atmospheric scattering characteristics from aerosols and thin clouds would be nearly the same as for the measurement of CO2 at 1.57 m. It's part of program to provide space-based active measurements of CO2 for Active Sensing of CO2 Emissions over Nights, Days, and Seasons (ASCENDS) Mission.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's investigation of large-scale environmental processes requires highly accurate measurements of atmospheric parameters from ground-based, airborne, and spaceborne platforms. Coherent Doppler Lidars and Differential Absorption Lidars (DIALs), working with 1.26-micron lasers, enable the measurement of oxygen in the atmosphere. The proposed compact all-fiber based single frequency 1.26-micron fiber laser offers a commercial solution to such applications. Its anti-vibration package and all-fiber cavity design allow a compact, reliable and efficient package for the LIDAR application in ground, airborne and space-borne platform. Most components in the fiber laser and the seed laser have been used for space applications, which means both the fiber laser and seed laser can be qualified for space application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are a number of non-NASA commercial applications for the proposed 1.26-micron single frequency fiber laser. Its narrow linewidth, stable laser output at oxygen absorption wavelength makes it a favorable source for lots of other practical applications, which needs to monitor the gas, especially oxygen.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.01-8410
PHASE-1 CONTRACT NUMBER: NNX10CD51P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Electro-Optic Laser Scanners for Space-Based Lidar

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vescent Photonics, Inc.
4865 E. 41st Avenue
Denver, CO 80216-4401
(303) 296-6766

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Davis
davis@Vescentphotonics.com
4865 E. 41st Ave.
Denver,  CO 80216-4401
(303) 296-6766

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of this phase II SBIR is to design and build new non-mechanical, electro-optic (EO) laser scanners that will be suitable for space based laser ranging, with a specific focus on the upcoming Lidar Surface Topography (LIST) mission. Even though the applications for EO laser scanning are extensive and pervasive, replacing opto-mechanics has been a historically intractable problem. Vescent Photonics has developed a proprietary electro-optic architecture that enables, for the first time, very wide field-of-regard (270 degrees of scanning demonstrated) and simple EO laser scanners. In our phase I work we demonstrated that these new EO scanners can be designed/adapted to meet the unique performance requirements for satellite based laser sensors. In phase II we will design, build and deliver a full EO scanner system, including a mated optical amplifier that will meet the LIST performance requirements. This phase II program will advance the TRL from 4 to 5-6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Rugged, low cost, wide-angle EO laser scanners, which have been an elusive goal for many years, have a large variety of applications. These include: free space optical (FSO) communications, micro-ladar for security and robotic vision, laser profilometers, environmental monitors (when combined with tunable lasers), and many more. Our technology will provide an increase of several orders of magnitude in the angular range of traditional electro-optic beamsteerers leading to wider spread electro-optic replacement of mechanical beamsteerers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low cost, rugged, wide-angle EO laser scanning is a basic component that will find utility across a wide variety of NASA missions. When combined with laser ranging (ladar) this will enable autonomous rover navigation, auto-docking devices, space based laser altimeters for terrain mapping, and many more. EO scanners can also be used for very high bandwidth free-space-optical communications between vehicles, satellites, planes, and/or remote platforms. Finally, the unprecedented small size, weight, and power will enable deployment on previously inaccessible platforms such as miniature UAVs, balloons, buoys, and more.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Airport Infrastructure and Safety
Attitude Determination and Control
Guidance, Navigation, and Control
Architectures and Networks
Autonomous Control and Monitoring
Laser
Optical
Sensor Webs/Distributed Sensors
Photonics


PROPOSAL NUMBER: 09-2 S1.01-8433
PHASE-1 CONTRACT NUMBER: NNX10CE92P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Tunable Narrow Linewidth, Low Noise 2.05 Micron Single Frequency Seeder Laser

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NP Photonics, Inc.
9030 S. Rita Road
Tucson, AZ 85747-9102
(520) 799-7424

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jianfeng Wu
jfwu@npphotonics.com
9030 S. Rita Road, Ste 120
Tucson,  AZ 85747-9102
(520) 799-7498

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose an all-fiber based 2.05-micron single frequency, narrow linewidth seeder laser with 10 nm tuning range and 5GHz frequency modulation for next generation LIDAR system. Highly Tm-doped fiber laser is used as a resonant pump source in order to reduce the phase noise and laser linewidth. An environment insensitive package will be used to minimize the laser phase noise and linewidth. Ho3+-doped fiber is used for seed laser generation, due to its strong emission at 2.05 micron. A Piezo attached to the laser cavity is used to modulate the frequency to 5 GHz with speed up to 10KHz. The laser can be continuously tuned over 10 nm range. The single frequency 2.05-micron fiber laser can be used to build coherent laser radars and Differential Absorption Lidars (DIALs) to perform instant measurement of velocity and concentration of CO2 and other gases , aerosols, clouds. The high-speed frequency modulation (5 GHz) of single frequency fiber laser used as local oscillator covers tuning over a selected CO2 absorption line. The large wavelength tuning range (10 nm) also enable scientists and engineers to explore the feasibility of using such laser for other remote sensing applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's investigation of large-scale environmental processes requires highly accurate measurements of atmospheric parameters from ground-based, airborne, and spaceborne platforms. Coherent Doppler Lidars and Differential Absorption Lidars (DIALs), working with 2-micron pulsed lasers, enable the measurement of CO2. The proposed low noise, narrow linewidth, single frequency 2.05 micron seeder laser with fast frequency modulation and wide tuning range offers a commercial solution to such applications. Its anti-vibration package and all-fiber cavity design allow a compact, reliable and efficient package for the LIDAR application in ground, airborne and space-borne platform. Most components in the fiber laser and the seed laser have been used for space applications, which means both the fiber laser and seed laser can be qualified for space application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The narrow linewindth and fast frequency modulation capability make it an ideal laser source used for commercial LIDAR for wind measurement. It also can be used to monitoring the green house gases. It can be a very important part for NOAA to build the CO2 gas monitor network. This type of all-fiber laser can be used for in situ measuring the 13C/12C and 18O/16O isotope ratios in atmospheric CO2 by laser absorption spectrometry. In ecosystem research, isotope ratios of molecules such as CO2 are of interest as they may improve our understanding of the sources and sinks of this important greenhouse gas. Long-term, real time, continuous in situ measurement at ambient concentrations would provide valuable information for atmospheric and environmental research. Laser absorption spectroscopy is one of the most promising tools due to its high sensitivity, species selectivity and spectral resolution. Based on the molecule's spectral fingerprint, laser absorption spectroscopy measurement can be performed on a gaseous sample, without need for pre-sampling and pre-treatment.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.01-8552
PHASE-1 CONTRACT NUMBER: NNX10CE93P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: HIgh Efficiency Laser for Aircraft/UAV and Space Lidar Missions

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Fibertek, Inc.
510 Herndon Parkway
Herndon, VA 20170-5225
(703) 471-7671

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Floyd Hovis
fhovis@fibertek.com
Fibertek, Inc. 510 Herndon Parkway
Herndon,  VA 20170-5225
(703) 471-7671

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR is developing high-efficiency, high beam-quality Nd lasers and non-linear wavelength conversion technologies suitable for ozone, aerosol, oxygen, CO2, water vapor and wind lidar. The advanced solid-state laser technology proposed directly supports NASA Earth Science Decadal Study programs for aerosols and clouds (ACE), global wind (3D-Winds) and advanced multi-beam altimetry and vegetation canopy missions (DESDynI, LIST). We propose to increase the wall-plug efficiency of fieldable 1um lasers from 4-6% into the 12-16% range, drastically reducing the electrical power needed for satellite missions. For the same satellite bus this means that power will be available to support another lidar system, radar or other instruments - greatly increasing the science mission value. The closely related non-linear wavelength conversion technology can also enable direct range-resolved CO2 measurement and/or oxygen lidars that support CO2 pressure and density determinations. The technology developed will also support sub-orbital flight missions for ozone, water vapor, and High Spectral Resolution Lidar (HRSL) systems for advanced aerosol measurements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
1. High-efficiency, single-frequency transmitter for the LaRC High Spectral Resolution Lidar (HSRL) system that is a strong candidate for the NRC Decadal Survey recommended Aerosol, Cloud and Environment (ACE) mission. 2. High efficiency 1064 nm transmitter for the NRC Decadal Survey recommended DESDynI mission. 3. High efficiency 1064 nm transmitter for the NRC Decadal Survey recommended LIST mission. 4. High efficiency 1064 nm transmitter for the Laser Vegetation Imaging System ? Global Hawk (LVIS-GH) being built by GSFC. Fibertek was recently awarded a contract to build the laser for this system based on our successful Phase 1 results. 5. High efficiency pump laser and nonlinear conversion module for use in Ozone Differential Absorption Lidar (DIAL) system development at LaRC. 6. High efficiency 355 nm source for the Direct Detection Wind Lidar system being built at GSFC for the recently awarded Hurricane and Severe Storm Sentinel (HS3) Venture Class Mission. 7. Upgrade to 1064/532/355 nm lasers being used in High Spectral Resolution Lidar (HSRL) research at Langley Research Center (LaRC).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
1. The NOAA Environmental Technology Laboratory (ETL)- We have been recently approached by researchers at ETL about the possibility of providing a laser transmitter for a water vapor DIAL. The results of our Phase 2 work would directly support our developments for this type of laser. 2. Ball Aerospace & Technologies Corp. (BATC) - BATC is developing next generation aerosol lidars, vegetation canopy lidars, and Doppler wind lidars for both airborne and space-based remote sensing systems. The high efficiency 1 m transmitter technology we will develop in Phase 2 would improve our ability to respond to opportunities to support these systems. 3. Short- pulse (< 6 ns), high-efficiency laser transmitters for use in DOD rangefinder/designator and imaging lidar systems. Fibertek has received multiple RFIs and RFPs from DOD prime contractors for laser transmitters whose requirements could be met by the laser designs we will be developing in the proposed Phase 2 work.

TECHNOLOGY TAXONOMY MAPPING
Optical


PROPOSAL NUMBER: 09-2 S1.01-9175
PHASE-1 CONTRACT NUMBER: NNX10CD52P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Fiber Coupled Pulse Shaper for Sub-Nanosecond Pulse Lidar

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ADVR, Inc.
2310 University Way, Building 1-1
Bozeman, MT 59715-6504
(406) 522-0388

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tony Roberts
roberts@advr-inc.com
2310 University Way, Building #1-1
Bozeman,  MT 59715-6504
(406) 522-0388

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovation Research Phase II effort will develop an all-diode laser and fiber optic based, single frequency, sub-nanosecond pulsed laser source for high resolution lidar applications benefiting SLR, LIST and DESDynI missions. This laser will have a user adjustable pulse width from 2ns to 400ps and will be ideal for seeding high power fiber amplifiers for short pulse, high resolution lidar transmitters. The highest utility of the proposed sub-nanosecond pulsed laser is simultaneously achieving narrow linewidth AND narrow pulse widths that can be set by the user for lidar instruments with <10cm vertical resolution.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
AdvR will discuss with NASA personnel the applications in high resolution lidar imaging with sub-ns pulses and long range optical telecommunications. Several future NASA applications identified as part of the Decadal Survey Missions that are likely to benefit from utilizing AdvR's pulse shaper including LISA (NASA/GSFC EUD: Code 661 Gravitational Astrophysics Lab), LIST (Lidar for Surface Topography, NASA/GSFC, and ICESat (GSFC Laser Remote Sensing Branch, Code 924). It will also supply a necessary component for planned upgrades to the international laser ranging service network (ILRS) as part of NASA's satellite laser ranging (SLR) program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The competitive advantage of the proposed approach is programmable, sub-nanosecond pulse generation with narrow, single frequency linewidth. Applications include: (1 )laser communication systems, the narrow linewidth provides improved signal-to-noise ratio, (2) free space laser communication for secure transmission of sensitive information, and (3) time resolved lasers for induced fluorescent spectroscopy, the short pulse and high power are key. Adding wavelength converters such as AdvR's KTP waveguides offers a value added benefit of tailoring the wavelength to specific fluorophores of study. This technology can also be applied to high power fiber modulators as could lead to a new approach to Q-switches in solid state lasers.

TECHNOLOGY TAXONOMY MAPPING
Optical
Photonics
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.01-9210
PHASE-1 CONTRACT NUMBER: NNX10CE95P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Pulsed, Single-Frequency, 2-um Seed Source for Coherent LIDAR Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Q-Peak, Inc.
135 South Road
Bedford, MA 01730-2307
(781) 275-9535

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alex Dergachev
dergachev@qpeak.com
135 South Road
Bedford,  MA 01730-2307
(781) 781-9535

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary objective of the proposed Phase II effort is to develop and deliver a ruggedized, single-frequency, mJ-level, 2050-nm master oscillator ? power amplifier system suitable for coherent LIDAR applications. The laser system is based on a low-average power, pulsed, single-frequency, 2-um Ho-laser source. Pulsed operation of the Ho-oscillator is achieved via passive Q-switching using robust Cr2+-doped saturable absorbers. Development of such pulsed seed sources enables the design of compact, rugged, reliable and efficient LIDAR transmitters based on all-amplifier architecture. Direct diode-pumping using the latest 1.9-um diode laser technology provides improved oscillator reliability and compactness. Efficient, Tm:fiber laser pumped, bulk Ho:YLF single-stage amplifier provides energy scaling to mJ level. The choice of a 2-um Ho-laser material (as opposed to 1.5-um Er-lasers) enables efficient power/energy scaling of the pulsed seed oscillator output in high-gain Ho-amplifiers. This approach decreases the number of amplifying stages, simplifies the overall design and packaging, and improves the electrical efficiency of the complete laser system as compared to the current technology.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work has direct application to NASA coherent, wind-sensing LIDAR programs based on the use of eyesafe, 2-um region lasers, as well as CO2 DIAL applications. The developed seed oscillator enables compact design, enhanced ruggedness and aids the overall all-amplifier system efficiency. Other use is as a front end of an all-amplifier-system to pump mid-IR parametric oscillators for application to DIAL sensors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial uses are for ground- and aircraft-based wind sensors in commercial aviation for wind shear and turbulence detection , as well as monitoring of CO2 levels in the atmosphere . Low-power, pulsed oscillator can be offered as a stand-alone component.

TECHNOLOGY TAXONOMY MAPPING
Optical


PROPOSAL NUMBER: 09-2 S1.01-9431
PHASE-1 CONTRACT NUMBER: NNX10RA75P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Narrow Wavelength, Frequency Modulated Source at 1.5 Wavelength

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Princeton Optronics, Inc.
1 Electronics Drive
Mercerville, NJ 08619-2054
(609) 584-9696

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Laurence Watkins
lwatkins@princetonoptronics.com
1 Electronics Drive
Mercerville,  NJ 08619-2054
(609) 584-9696

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Ultrastable, narrow linewidth, tunable, high reliability sources at 1.5 or 2mm are needed for high performance LIDARs for several NASA applications, including wind speed measurement, surface topography, earth and planetary atmosphere composition measurements. Princeton Optronics proposes to develop a low noise, narrow linewidth, 10W output MOPA source at 1500nm using a tunable, low noise, narrow linewidth, FM modulated seed laser as a master oscillator coupled to a fiber amplifier. The technology developed in this SBIR could be applied to develop a Thulium MOPA at 2mm. The proposed program will develop a MOPA laser system assembled in a small robust package for field applications. The optical design of the system comprises the FM solid-state microchip seed laser in which a FM source drives the piezo tuning actuator in the microchip laser to provide >5GHz frequency modulation at 1kHz rates. The microchip laser is designed for output power of >20mW in single frequency, linear polarized, single transverse mode. This is coupled into the fiber amplifier to produce 10W output with the same narrow linewidth and FM modulation as the seed laser. Isolators are used between the seed and fiber amplifier to prevent ASE and reflections causing noise and lasing of the amplifier.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The NASA applications include (the NASA applications are from Dr Farzin Amzajerdian 1) Coherent Doppler LIDAR systems: Global measurements of atmospheric winds for weather forecasting and climate research, windshear and wake vortex detection for aircraft, and ground velocity and range for landing vehicles. Once the product is developed, a significant number of the products would be required by NASA. 2) Differential Absorption LIDAR: Measuring CO2 concentration for climate research and pollution control Once the product is space qualified, we could expect a need from NASA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Princeton Optronics has been selling products into the commercial market for the last 10 years. PRO products include low noise tunable laser products as well as VCSEL devices and arrays. There is a large market for narrow linewidth, stable lasers for commercial applications which include atomic spectroscopy, interferometry for oil exploration, LIDARs, magnetometers for military application, analog and coherent communications, etc. PRO will commercialize this product once it is developed from this SBIR. Low noise and stable lasers have a market of $50M. Princeton Optronics is in a very good position to commercialize the products through their manufacturing and sales organization. Princeton Optronics has raised funds from venture capital sources and is in a position to manufacture and sell this product very efficiently. PRO has a strong manufacturing operation and a strong sales team as well as a national and international distribution network to take advantage of the market demand.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
Photonics


PROPOSAL NUMBER: 09-2 S1.01-9529
PHASE-1 CONTRACT NUMBER: NNX10CE96P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Integrated Planar Lightwave Circuits for UV Generation and Phase Modulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ADVR, Inc.
2310 University Way, Building 1
Bozeman, MT 59715-6504
(406) 522-0388

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shirley McNeil
mcneil@advr-inc.com
2310 University Way, Building #1-1
Bozeman,  MT 59715-6504
(406) 522-0388

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary goal of this SBIR effort is delivery of a compact, robust, highly efficient, fiber-coupled UV module to provide the required 355nm light for integration into HSRL's UV interferometric-based measurement system. An additional goal of this effort is to prototype a compact, robust, fiber-coupled UV PLC module which produces the required spectrally formatted 355nm light for stabilization of the HSRL's UV interferometric filter, a component required for the accurate measurement of critical aerosol microphysical properties. This approach is enabled by AdvR's patented submount poling technique together with AdvR's integrated Planar Lightwave Circuit (PLC) technology. The UV PLC concept advances NASA's state-of-the-art lidar systems due to its compact, efficient, and reliable design, thus enabling use on small aircraft and future space-based platforms.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary customer is NASA Langley's High Spectral Resolution Lidar (HSRL) program for aerosol and cloud characterization. HSRL is targeted for the ACE Mission by NASA's ACE Science Working Group because of the higher information content it provides over backscatter lidar on key aerosol optical and microphysical properties. The proposed UV technology will find uses in other NASA lidar remote sensing programs, such as UV DIAL lidar and Doppler lidar for 3D Winds where compact, low cost, UV stabilized sources are required. This technology also has potential application as a calibration source for visible to UV spectrometers (such as MODIS), as well as for multi-wavelength imaging for atmospheric correction.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to NASA's use in various lidar systems, the PLC technology in general will find use in fiber and free-space communications where rapid, moderate power phase modulation is required. This technology can also be applied for systems used for environmental and pollution monitoring, precision spectroscopy, high power pulse shaping, visible display applications, and for stabilizing laser sources and interferometric filters.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Laser
RF
Optical
Photonics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials
Thermoelectric Conversion


PROPOSAL NUMBER: 09-2 S1.01-9879
PHASE-1 CONTRACT NUMBER: NNX10CE97P
SUBTOPIC TITLE: Lidar and Laser System Components
PROPOSAL TITLE: Frequency Up-Conversion Detection System with Single Photon Sensitivity within 1-1.8 m and 3-4 m for ASCENDS Mission: A Novel Approach to Lidar

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ArkLight
3210 N. Bay Hill Drive
Center Valley, PA 18034-8452
(484) 547-5375

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yuliya Zotova
yzotova@hotmail.com
3210 N. Bay Hill Drive
Center Valley,  PA 18034-8452
(484) 547-5375

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
PI at ArkLight proposes to implement photon counting detectors at near-IR (1-1.8 microns) and mid-IR (3-4 microns) with single photon sensitivity based on frequency up-conversion during Phase 2, representing an innovative Lidar technology for ASCENDS mission. By working with Prof. Ding at Lehigh University, PI will explore fundamental limits to quantum efficiencies for up-conversion detection at 1.57 microns. She will implement, characterize, and optimize single up-conversion device capable of detecting 1.57 microns and 1.27 microns. She plans to achieve detections of CO2 and O2 using implemented up-conversion device. She will investigate fundamental limits to noises for up-conversion detections. She will compare among PPLN, PPKTP, and PPLT as up-conversion media. She will expand detection wavelengths to cover ranges of 1-1.8 microns and 3-4 microns. She plans to introduce novel techniques for improving performances of up-conversion devices. She will investigate versatility of up-conversion devices under harsh environments. To achieve all these objectives, she has laid out a detailed work plan describing all the specific tasks necessary. Through optimizations, she will achieve the quantum efficiency of 50%, dark count rate of 50 Hz, bandwidth of GHz, electrical consumption of < 1 W, weight of < 1 lb, and dimension of 7x4x4 (all in inches).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The photon counting detectors implemented by PI during Phase 2 will meet the requirement of NASA as being defined by the NASA SBIR solicitation of TOPIC: S1 Sensors, Detectors, and Instruments. Specifically, these detectors will be used to achieve single photon sensitivity in the wavelength ranges of near-IR (1-1.8 microns ) and mid-IR (3-4 microns ). In comparison, InGaAs/InP avalanche photodiodes are incapable of reaching single photon sensitivity within the two spectral ranges. 3-D imaging systems by combining the photon counting detectors and a laser can be used to realize coherent imaging LIDAR for the ASCENDS, DESDynI, LISA, Doppler Wind Lidar, and LIST mission programs. Such 3-D imaging can be achieved by both a staring single-element photon counting detector and an array of these detectors. The energy sources of nine infrared luminous galaxies can be diagnosed by a ground-based 3-4 m spectrometer to be developed by PI based on the photon-counting detectors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The photon counting detectors can be used in Missile countermeasure with significantly improved sensitivity and reliability. A spectrometer based on these detectors can be used for making spectroscopic studies of molecules in the range of 1-11 microns. It can be also used to detect trace amounts of the molecular species for the applications in chemical sensing and detections of biological and chemical agents. It can be used as a tool for biomedical diagnostics for important applications such as glucose detection. The new LIDAR system to be developed by PI by combining the photon counting detectors and a laser has important applications in archaeology, meteorology and atmospheric environment, wind power, geology, physics and astronomy, biology and conservation, military and law enforcement, vehicles, imaging, and 3-D mapping. Since it can reach single photon sensitivity around 1550 nm, it is not only eye-safe but also important for military applications in night vision goggles.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Large Antennas and Telescopes
Airport Infrastructure and Safety
Attitude Determination and Control
Biomolecular Sensors
Laser
Biochemical
Optical
Photonics
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.02-8927
PHASE-1 CONTRACT NUMBER: NNX10RA60P
SUBTOPIC TITLE: Active Microwave Technologies
PROPOSAL TITLE: 3D High Density Wave Interconnects

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nuvotronics, LLC
7586 Old Peppers Ferry Loop
Radford, VA 24141-8846
(800) 341-2333

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jean Marc Rollin
jmrollin@nuvotronics.com
7586 Old Peppers Ferry Loop
Radford,  VA 24141-8846
(800) 341-2333

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Nuvotronics has developed and optimized the PolyStrata<SUP>TM</SUP> process for the fabrication of intricate microwave and millimeter-wave devices. These devices have primarily been rectangular coaxial transmission lines, although rectangular waveguide and other structures have also been demonstrated. Intricate devices have been demonstrated with insertion loss 5 to 10 times lower than traditional planar circuits; isolation better than 60dB for lines that share separating walls; multiple levels of densely-packed coaxial circuits; and low-parasitic attachment to active devices and traditional circuit boards. In this Phase II project, Nuvotronics will optimize and fabricate high density low-loss millimeter backplane circuits to package and interconnect components of future NASA millimeter wave (MMW) radars. The significance of the innovation primarily lies in three areas: reduction of system size, weight and loss in MMW radars. The PolyStrata technology is a batch manufacturing process, providing economies of scale and cost reduction for higher volumes, in addition to flexibility in design for various frequencies of interest.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our primary goal in this project is to provide NASA with robust space-capable MMW interconnection technology that is lower cost, lower weight, and has improved performance over current technology. The initial application is MMW radars for advanced cloud and precipitation measurements and for Mars landing sensors. Candidate NASA missions are future landers for the Mars Exploration Program and the Aerosol/Cloud/Ecosystems (ACE) Mission. Reducing size and weight of radar instruments will allow more mission capability on each platform, increasing NASA return on investment in these missions. Instrument constraints on size and weight in NASA unmanned aerial vehicles could also benefit from the PolyStrata RF backplane technology as well as future NASA communication systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We anticipate high volume product opportunities within the DOD and non-Government commercial markets. Within DOD, applications in communications and radar systems exist for advanced microwave components. For military communications, the benefits are higher bandwidth, multipoint links, and low payload weight for planes, missiles, and tanks. Programs within the DOD such as the Army's WIN-T (Warfighter Information Network - Tactical) require advanced microwave components in order to meet the demanding applications of satellite communications while on-the-move. Other key market opportunities driving future growth exist in the mobile backhaul, wireless enterprise bridge, wireless fiber lateral emulation, government and public safety networks, WirelessHD, and WiMax.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
RF
Microwave/Submillimeter


PROPOSAL NUMBER: 09-2 S1.02-9911
PHASE-1 CONTRACT NUMBER: NNX10CD96P
SUBTOPIC TITLE: Active Microwave Technologies
PROPOSAL TITLE: High-Speed, Low-Power ADC for Digital Beam Forming (DBF) Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ridgetop Group, Inc.
6595 North Oracle Road
Tucson, AZ 85704-5645
(520) 742-3300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Justin Judkins
justin.judkins@ridgetopgroup.com
6595 North Oracle Road
Tucson,  AZ 85704-5645
(520) 742-3300

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In Phase 1, Ridgetop Group designed a high-speed, yet low-power silicon germanium (SiGe)-based, analog-to-digital converter (ADC) to be a key element for digital beam forming (DBF) systems that will be used in NASA's future radar applications. The ADC will employ a novel combination of time interleaving, high-speed silicon-germanium BiCMOS technology and low-power techniques, such as the double-sampling technique, providing exceptional sampling speed of 500 MSPS, 1.5 GHz analog bandwidth,12 bits of resolution, and below 500 mW power dissipation, exceeding NASA's requirements. Ordinarily, ADC design requires large trade-offs in speed, resolution, and power consumption. The significance of this innovation is that it simultaneously provides a high-speed, high-resolution, and low-power ADC that is well ahead of the state of the art. These three characteristics are needed for DBF systems that contain large ADC arrays. The power consumption of existing ADC chips prohibits implementation of large DBF arrays in space. Ridgetop's innovative design leverages newer semiconductor process technologies that combine silicon and germanium into a compound semiconductor. Ridgetop has identified two Phase 2 objectives, which are: 1. Design, fabricate and characterize Test Chip 1 that contains critical ADC subcircuits. 2. Design, fabricate and characterize Test Chip 2 that contains the complete radiation tolerant, digitally calibrated, time-interleaved ADC design. During Phase 1 Ridgetop identified the topologies for all of the circuit blocks that will be included on Test Chip 1 and Test Chip 2. Ridgetop has also completed transistor-level designs for the key components on these chips. Estimated TRL at beginning and end of Phase 2 contract: Begin 4; End 8.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications include radar, imaging, detectors, space radio astronomy, and communication circuits. Space radar systems stand to benefit from the combination of high resolution and low power of the proposed ADC. The technology is ideal for NASA Jet Propulsion Laboratory's radar research program, UAVSAR program, and many other critical communication circuits.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications include: ? Phased arrays for ballistic missile defense (BMD) (the DBF technology is commonly cited as a "huge leap" for radar-based missile defense systems) ? Space-based radar for military/intelligence targets or earthquake detection ? Measurement applications, including pin test electronics on ATE systems ? Space navigation systems ? Conformal arrays for UAVs ? Telecommunications applications, such as software-defined radio ? Medical imaging device manufacturers ? Computer networks, hard disk readout circuits, digital oscilloscopes, etc. ; these applications require 500 MSPS sampling speeds, and the "effective number of bits" (ENOB) used in contemporary converters is <10 bits, and the power dissipation is >2 W ? Power-limited applications, such as laptops, wireless devices and PDAs.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Guidance, Navigation, and Control
Microwave/Submillimeter
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 S1.03-9002
PHASE-1 CONTRACT NUMBER: NNX10CD97P
SUBTOPIC TITLE: Passive Microwave Technologies
PROPOSAL TITLE: Low Power 2-Bit ADC Array with Serial Output

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pacific Microchip Corp.
3916 Sepulveda Blvd. #108
Culver City, CA 90230-4650
(310) 683-2628

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dalius Baranauskas
dalius@pacificmicrochip.com
3916 Sepulveda Blvd. #108
Culver City,  CA 90230-4650
(310) 940-3083

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Microwave interferometers for NASA missions such as PATH employ the GeoSTAR instrument, consisting of 600 receivers. Each receiver requires I and Q ADCs (analog-to-digital converters) for signal digitizing at 1GHz before further processing in the cross-correlators. Power consumption as well as instrument volume and weight are critical in space born instruments. During Phase I, Pacific Microchip Corp. designed the block diagrams and circuits of a monolithic array consisting of sixteen 2-bit ADCs. A serializer is integrated to reduce the number of outputs from 32 to 1. This reduces the power consumption per ADC and resolves the problem of wiring congestion in the interface with cross-correlators. For further power reduction, a novel metastability programming feature is integrated into the ADC latches. The clock distribution is fundamentally simplified as well. The 2-wire serial I2C (Inter-Integrated Circuit) interface allows all 1200 ADCs of the GeoSTAR instrument to be calibrated and optimized. Phase I work provided a complete definition and in silico validation of the monolithic ADC array with serial output. Phase II of the project will produce a fieldable product. In order to facilitate the commercialization efforts in Phase III, a Complementary Metal-Oxide-Semiconductor (CMOS) Silicon-on-Isolator (SOI) technology will be used for fabrication.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The extra-low power ADC arrays with serial outputs featuring power optimization capability depending on the required BER, high quantization frequencies, and convenient control through a two wire interface can be used in radiometer and interferometer instruments such as GeoSTAR. These instruments apply passive and active microwave technologies that are under development by NASA in its mission to provide inexpensive data for many different fields including science, agriculture, geology, weather forecast, climatology, and civil aviation. The potential application of the ADC arrays in space-based wireless communication systems promises to lower the cost of exploration data delivery to users.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The unique characteristics of the proposed ADC array make it ideal for parallel digitizing applications that require power efficiency at high quantization rate. Oversampling can be used when more than 2-bit resolution is required. Such ADCs are critical components in multichannel wireless communication systems. Advanced ADC arrays are also required for neural implants, image sensors and sensor networks. The ADC array will be implemented using commercial 45nm SOI CMOS technology offering low device cost and extremely power efficient operation. The proposed Pacific Microchip Corp. Serializers and Deserializers (SerDes) capable of operating at a line rate of up to 32Gb/s are the essential blocks required for the next generation 100Gb/s (4x25Gb/s) Ethernet. We also plan to offer the ADC array as an IP block for integration in Systems On Chip (SoC).

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Ultra-High Density/Low Power
Architectures and Networks
RF
Data Input/Output Devices
Microwave/Submillimeter
Highly-Reconfigurable
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 S1.04-8479
PHASE-1 CONTRACT NUMBER: NNX10CD98P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: High Power Room Temperature Terahertz Local Oscillator

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Desert Beam Technologies, LLC
3542 N. Geronimo Ave.
Tucson, AZ 85705-3614
(520) 888-5900

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Yarborough
j.yarborough@desert-beam.com
3542 N Geronimo Ave.
Tucson,  AZ 85705-3614
(520) 307-5361

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The motivation of the proposed SBIR is to develop, demonstrate and commercialize a compact, low-mass, high output power (1-10 milliwatt), tunable source of CW THz radiation operating at room temperature. The source will be useful both as a narrow band frequency stable sources for driving heterodyne receivers at key frequencies between 1 and 5 THz (1.4, 1.9, 2.7, 4.7 etc..) or for laboratory sources to characterize THz components, including MMIC's, or possibly for active spectrometers in an in-situ environment The proposed source would enable the development of THz array receivers for use in space and suborbital missions, or for atmospheric sounders and planetary landers. In Phase 1 our VECSEL THz source, based on intra-cavity difference frequency generation, demonstrated 2mW at 1.9THz running on a finite number of cavity modes with a linewidth per mode of around 1MHz. Desert Beam Technologies will team up TeraVision (Tucson) and with researchers at the Steward Observatory Radio Astronomy Laboratory (SORAL), University of Arizona in Phase 2 to further characterize a breadboard VECSEL 1.9THz system, measure Y-factor and I-V curves, redesign the VECSEL cavity to reduce it to single mode operation and test it as a local oscillator for SORAL's 1.9THz receiver.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In response to the upcoming Explorer Announcement of Opportunity, the University of Arizona team at SORAL and collaborators plan to propose to build and fly a new, higher performance THz balloon-borne observatory with array receivers at 1.9, 2.06, 2.46, 2.7, and 4.7 THz. The VECSEL THz source has the potential of providing the LO powers required for such systems. They are also planning to propose to develop THz array receivers for the Stratospheric Observatory for Far-Infrared Astronomy (SOFIA). JPL has expressed an interest in our VECSEL THz technology to test heterodyne components at 2.5, 3 and 4.7 THz that they have been prototyping for several upcoming NASA opportunities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Current commercially available CW sources are low power (typically between 500 nW and a few micro-Watta) at frequencies within the THz gap that offers unique spectroscopic fingerprints of explosives and chem./bio agents. Desert Beam Technologies VECSEL THz source is capable of delivering mW's of power at any targeted frequency with narrow linewidth < 1 MHz. The company has received NSF SBIR funding to develop a stand-off detection, 3D imaging and spectral fingerprinting system at 820Ghz in an atmospheric transmission window. The Department of Defense has a critical need in Iraq and Afghanistan, for a THz stand-off detection system that would identify explosives hidden under the clothing of a suicide bomber and detect biological contaminants on surfaces.

TECHNOLOGY TAXONOMY MAPPING
Biomolecular Sensors
Microwave/Submillimeter


PROPOSAL NUMBER: 09-2 S1.04-8553
PHASE-1 CONTRACT NUMBER: NNX10CD99P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: Metal-Mesh Optical Filter Technology for Mid IR, Far IR, and Submillimeter

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Lake Shore Cryotronics, Inc.
575 McCorkle Blvd.
Westerville, OH 43082-8699
(614) 891-2243

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William McGovern
bill.mcgovern@lakeshore.com
575 McCorkle Blvd.
Westerville,  OH 43082-8699
(614) 891-2243

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovative, high transmission band-pass filter technology proposed here is an improvement in multilayer metal-mesh filter design and manufacture for the far IR to submillimeter ranges. The proposed metal-mesh filters can tolerate cryogenic temperatures (down to 4K and below) and a wide vibration/shock spectrum, making them launch-capable and durable for long periods in space. In addition, the proposed band-pass filters are light weight, as they employ no heavy substrates. The proposed 2 ? 5 mm thickness (mostly the mounting frame) allows insertion into tight spaces and standard filter wheels. The thin, light weight, vacuum compatible design can be incorporated into almost any detector setup. Large sizes can be manufactured for newer instruments with larger diameter beams.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Improvements in the detector sensitivity and format have enabled significant development of the capabilities in the far-IR and submillimeter spectral regime, in the last few years. Detector arrays have improved from hundreds to thousands or millions of pixels, which has led to rapid dispersive (i.e. diffraction-grating) spectroscopy of multiple sources in multiple far IR wavebands simultaneously. In astrophysics, sensitive far IR spectroscopy from actively-cooled space telescopes can reveal the history of galaxies, heavy-element production, and black-hole growth since the very first stars. There are a number of astronomy programs such as, SOFIA, SPICA/BLISS, SAFIR, SPIRIT that will use far IR spectrometers for optimal science discovery. Other projects such as CLARREO are designed to provide a measure of the earth's radiation budget, reveal distribution of key greenhouse gases, and probing the role of high altitude clouds could use sensitive far IR spectroscopy to improve its capabilities by orders of magnitude.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Lake Shore's proven track record in commercializing advanced technologies along with being an established supplier to NASA makes us confident we can further commercialize our metal-mesh filter technology upon developing standard multi-layer designs. Earth-based astronomy programs have a need and will continue to have a need for improved IR band pass filters, dichroic filters among other optical components. University astrophysics research, missle defense applications, and infrared, submillimeter, and Thz spectrometer manufacturing (improve broadband detector performance with filtering) are all markets that are actively growing and show a need for band-pass filters.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Microwave/Submillimeter
Optical
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.04-9317
PHASE-1 CONTRACT NUMBER: NNX10CE02P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: An Implant-Passivated Blocked Impurity Band Germanium Detector for the Far Infrared

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TechnoScience Corporation
P.O. Box 60658
Palo Alto, CA 94306-0658
(650) 838-9833

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jam Farhoomand
jam.farhoomand@nasa.gov
P.O. Box 60658
Palo Alto,  CA 94306-0658
(650) 650-9833

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to fabricate a germanium blocked-impurity-band (BIB) detector using a novel process which will enable us to: 1- fabricate a suitably-doped active layer using the well-established bulk crystal-growth process, which guarantees excellent dopant control and extremely low compensating impurities, and 2- grow the blocking layer using an implant-passivation technique which will produce the required high purity and a very sharp transition from the active to blocking layer. These features are key in design and optimization of the multi-layered structure of BIBs, and their implementation and quality are crucial in optimum operation of these detectors. The proposed process is a drastic departure from conventional epitaxial methods, such as chemical vapor deposition and liquid phase epitaxy, which have yet to produce far IR BIBs suitable for astronomical instruments. Germanium BIBs will offer extended wavelength response up to at least 200m, high quantum efficiency, high immunity to ionizing radiation, and elimination of long-term transient and memory effects. Coupled with their compatibility with Si cryo-CMOS readout multiplexers and the planar, bump-bond hybridization process, these detectors will make possible the construction of large format, high sensitivity FPAs for far IR astronomy and will replace the current unstressed and stressed germanium detectors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Far-infrared astronomical instruments on board SOFIA, balloon experiments, and any follow-on missions to Spitzer and Herschel such as SAFIR/CALISTO.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Far-infrared astronomical instruments on board SPICA, a japanese-led, JAXA-ESA joint mission scheduled to launch in 2017.

TECHNOLOGY TAXONOMY MAPPING
Microwave/Submillimeter
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 S1.05-9730
PHASE-1 CONTRACT NUMBER: NNX10CD59P
SUBTOPIC TITLE: Detector Technologies for UV, X-Ray, Gamma-Ray and Cosmic-Ray Instruments
PROPOSAL TITLE: Functionalized Nano-Film Microchannel Plate: A Single High Aspect Ratio Device for High Resolution, Low Noise Astronomical Imaging

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Arradiance, Inc.
142 North Road
Sudbury, MA 01776-1122
(978) 369-8291

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Neal Sullivan
nsullivan@arradiance.com
142 North Road
Sudbury,  MA 01776-1142
(888) 949-4441

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Atomic layer deposited functional nano-film technology is used to manufacture Microchannel plate (MCP) devices capable of high gain / low ion feedback operation, on glass capillary array substrates, as a means to replace MCP chevron configuration and enable direct photocathode deposition (e.g. GaN) for NASA applications. Commercial MCP devices rely on 1970's manufacturing technology, constrained by the bulk glass: heavy metal impurities limit the achievable dark noise in low signal detection, the requisite batch processing restricts flexibility to tailor individual device performance and often result in poor yield. Arradiance's proven nano-film technology has been shown in Phase I to improve the component functions of secondary electron emission and conductivity resulting in high performance MCPs. In Phase II performance optimization of these novel devices and, enabled by substrate independence, an opportunity to explore direct deposition of advanced photocathodes. Since the high quality GaN films required for efficient photoelectron transport can only be deposited at elevated temperatures (<900 C), conventional Pb-glass MCPs, with a softening point of ~400C, are not suitable. Arradiance nanofilms allow high temperature MCP substrates (e.g. quartz or anodized alumina - AAO) and the opportunity for significant detection efficiency improvement. TRL 4 at beginning; TRL 6 at end.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA: Substrate independence, large area detectors, single event detection in a single MCP (no chevron required), greatly improved resolution and direct deposition of opaque photocathodes have the potential for enormous impact on NASA missions. These innovations will contribute to improved resolution and optics simplification. By significantly improving functionality & capability of MCPs, a single plate configuration capable of low noise, high resolution counting and imaging that could surpass existing detector performance benchmarks becomes possible. A significant reduction of size, mass, power and cost of detection enabling smaller, more affordable spacecraft while benefitting science measurement capabilities allowing NASA programs can to meet multiple mission needs making the best use of limited resources.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA: Night Vision, Mass spectrometry, Photoionization, Electron microscopy, Surface physics, UV and VUV imaging, Fusion research, Synchrotron Radiation, Nuclear physics, Field ion microscopy, Low temperature physics, Neutron Detectors, Neutron Radiography and Tomography, Scanning Near field Microscopy, Accelerators , Plasma Physics, Cluster research, Fluorescent detection and Trace analysis.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Particle and Fields
Optical
High-Energy
Photonics
Ceramics
Composites
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 S1.05-9827
PHASE-1 CONTRACT NUMBER: NNX10CD60P
SUBTOPIC TITLE: Detector Technologies for UV, X-Ray, Gamma-Ray and Cosmic-Ray Instruments
PROPOSAL TITLE: Low-Noise, UV-to-SWIR Broadband Photodiodes for Large-Format Focal Plane Array Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Discovery Semiconductors, Inc.
119 Silvia Street
Ewing, NJ 08628-3200
(609) 434-1311

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Abhay Joshi
abhay@chipsat.com
119 Silvia Street
Ewing,  NJ 08628-3200
(609) 434-1311

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Broadband focal plane arrays, operating in UV-to-SWIR wavelength range, are required for atmospheric monitoring of greenhouse gases. Currently, separate image sensors are used for different spectral sub-bands: GaN for UV, Si for visible, and InGaAs for SWIR, requiring expensive component-level integration for hyper-spectral imaging. Also, the size of the InGaAs focal plane arrays is currently limited by the InP substrate area. We propose to develop a 640 x 512 UV-to-SWIR focal plane array sensor using GaAs substrate having following photodiode performance: (1) Cut-on Wavelength = 0.25 micron; (2) Cut-off Wavelength = 2.5 micron; (3) RoA > 35 Ohm-cm^2 at 300K; and (4) Quantum Eficiency > 30% in UV (0.25 to 0.4 micron), > 80% in Visible (0.4 to 0.9 micron), and > 70% in IR (0.9 to 2.5 micron) subbands. Based on P.I.'s experience on SCIAMACHY, this project will enable one image sensor for 8 spectroscopic channels currently orbiting on European Space Agency's ENVISAT.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications for large-format UV-to-SWIR focal plane array sensors include: 1. Space-based atmospheric monitoring of ozone and greenhouse gases 2. Weather observation 3. Hyper-spectral sensors for planetary missions

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA commercial applications for large-format UV-to-SWIR focal plane array sensors include: 1. Pollution monitoring for automobiles, refineries, etc. 2. Bio-medical imaging and spectroscopy 3. Jet engine development 4. Industrial process control in pharmaceutical, food-processing, and petrochemical industries 5. Crop monitoring 6. Mineral detection

TECHNOLOGY TAXONOMY MAPPING
Optical
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.06-8420
PHASE-1 CONTRACT NUMBER: NNX10CD61P
SUBTOPIC TITLE: Particles and Field Sensors and Instrument Enabling Technologies
PROPOSAL TITLE: Miniature Laser Magnetometer (MLM)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Polatomic, Inc.
1810 N. Glenville Dr., #116
Richardson, TX 75081-1954
(972) 690-0099

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
RObert Slocum
bob_slocum@polatomic.com
1810 N. Glenville Dr, #116
Richardson,  TX 75081-1954
(972) 690-0099

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This 2009 NASA SBIR Phase 2 proposal for an innovative Miniature Laser Magnetometer (MLM) is a response to subtopic S1.06 Particles and Field Sensors and Instrument Enabling Technologies. The MLM instrument will incorporate a number of technical innovations to achieve high-sensitivity and high-stability performance while significantly reducing the size of the laser-pumped helium magnetometer for use on very small satellites and UAVs. The MLM design approach will trade sensitivity for miniaturization of critical components while still meeting the performance requirements for geomagnetic and space science experiments. Reduction in instrument mass, volume and power will be accomplished through innovations including new non-magnetic components, compact nested triaxial Braunbek coils for vector measurements, and miniaturized packaging designs. The MLM will have a dynamic range up to 75,000 nT. The scalar sensitivity will be 5 pT/rtHz with an accuracy of 0.2 nT. The vector sensitivity will be 5 pT/rtHz with an accuracy of 0.5 nT. The feasibility of fabricating and demonstrating a MLM prototype in Phase 2 was established in the Phase 1 effort. The TRL is expected to be 6 at the end of the Phase 2 contract.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed in this SBIR project will find applications in advanced instruments for airborne, satellite, and surface measurements of near-Earth magnetic fields. Potential flight platforms include small satellites such as the upcoming Cosmic 2 mission and UAVs such as the high-altitude Global Hawk. Laser-pumped space magnetometers are also under development for missions including Earth-field orbiting magnetometer/gradiometer mapping missions and joint US mapping missions with NOAA and USGS. Laser magnetometers are under consideration for volcanic eruption predictions and geo-potential changes in the Earth's crust associated with earthquakes and subduction zones. The outstanding accuracy and sensitivity will allow the measurement of gradients at short and long distances. The MLM can also be configured as a portable instrument for use in magnetic calibration facilities and for ground-based magnetic testing of spacecraft and aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The high-sensitivity laser-pumped helium magnetometer technology is currently being developed for military applications in UAVs and UUVs used for Mine Countermeasures and Anti-Submarine Warfare. Polatomic is pursuing opportunities in magnetic detection of tunnels for border security and monitoring and airborne detection of underground facilities. The MLM is being considered by the Office of Naval Research for use on a Navy Global Hawk for geomagnetic noise reduction for submarine detection magnetometers. The MLM will be used for surface, marine, and airborne magnetic prospecting in small UAVs. Polatomic is jointly pursuing use of the laser magnetometers for mineral and petroleum exploration with Southern Methodist University and the Kansas Geophysical Society. The MLM permits high-resolution magnetometer and gradiometer mapping of mineral deposits that form in ridges, narrow intrusions, geologic up-thrusts, and deep-lying ore deposits. In conventional airborne surveys, the high sampling rate and high resolution may increase the daily productivity per aircraft by as much as a factor of ten. In addition, underwater magnetic surveys will benefit from the order-of-magnitude gradiometer resolution improvement realized by towing the MLM in a magnetically clean underwater vehicle.

TECHNOLOGY TAXONOMY MAPPING
Particle and Fields


PROPOSAL NUMBER: 09-2 S1.06-8554
PHASE-1 CONTRACT NUMBER: NNX10CD62P
SUBTOPIC TITLE: Particles and Field Sensors and Instrument Enabling Technologies
PROPOSAL TITLE: Elastic Deployable Composite Tubular Roll-Out Boom

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Deployable Space Systems
75 Robin Hill, Building B2
Goleta, CA 93117-3108
(805) 693-1319

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Spence
Brian.Spence@DeployableSpaceSystems.com
75 Robin Hill, Building B2
Goleta,  CA 93117-3108
(805) 805-1313

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Deployable Space Systems (DSS) has developed an affordable and ultra-lightweight elastically self-deployable Roll-Out Boom technology that provides affordability and mission-enabling performance features for current and future NASA missions. The Roll-Out Boom technology provides affordability and a significant performance increase in terms of extremely compact stowage volume, ultra-lightweight, broad scalability, high deployed frequency, high deployed strength, reliable/immediate/repeatable controlled deployment, high stiffness during deployment, good thermal/dimensional stability, highly conductive composite materials construction, space environmental survivability, and broad mission applicability. The Roll-Out Boom technology is applicable as an improved direct replacement to competing deployable structures, and is flexible in geometry, length, section, material, and construction to meet the most demanding mission requirements. The Roll-Out Boom is highly applicable as an enabling deployable structure for electric field sensors, antennas, gravity gradient booms, and magnetometer booms, or as a deployable structural platform for solar arrays, sunshades and/or other proprietary payloads. The technology innovation is applicable for practically all NASA and non-NASA missions as a direct replacement for classical state-of-the-practice deployable structure technologies.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed DSS Roll-Out Boom is widely applicable to future NASA missions as a direct replacement for existing technologies, and will provide the end-user with an enabling technology that reliable deploys and is strong, stiff, lightweight, thin, compactly-stowed, and fabricated from ultra-lightweight composite materials. The Roll-Out Boom can be used as a self-deploying antenna, electric field antenna, linear actuator, grapple arm, gravity gradient boom, camera support, inspection aid, or as an actuator/structure for deploying payloads, antennas, solar arrays, instrument benches, solar sails, and sunshades. The technology is ideal for making large antennas and arrays such as dipoles, monopoles, and Yagi antenna shapes. Boom sizes envisioned can be from 0.5-inch to 12-inches in diameter (or greater), with lengths from 1-m to 50-m long (or longer).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed Roll-Out Boom is also widely applicable to non-NASA missions, including DoD and commercial missions, as a direct replacement for current state-of-the-art. The Roll-Out Boom can be used as a self-deploying antenna, electric field antenna, linear actuator, grapple arm, gravity gradient boom, camera support, inspection aid, or as an actuator/structure for deploying payloads, antennas, solar arrays, instrument benches, solar sails, and sunshades. The technology is ideal for making large antennas and arrays such as dipoles, monopoles, and Yagi antenna shapes. Applicable missions include: LEO DoD surveillance, reconnaissance, communications and other critical payload/equipment satellites, LEO commercial mapping and critical payload/equipment satellites, MEO DoD satellites, GEO commercial communications and critical payload/equipment satellites, and GEO DoD communications and payload/equipment satellites. Non-space applications include fixed and mobile ground deployable structures for antennas and other payloads

TECHNOLOGY TAXONOMY MAPPING
Mobility
Manipulation
Kinematic-Deployable
Particle and Fields
RF
Composites


PROPOSAL NUMBER: 09-2 S1.07-8699
PHASE-1 CONTRACT NUMBER: NNX10CD63P
SUBTOPIC TITLE: Cryogenic Systems for Sensors and Detectors
PROPOSAL TITLE: ADR Magnets Operating at 30-40K

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Superconducting Systems, Inc.
5 Fortune Drive
Billerica, MA 01821-3923
(978) 330-3021

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shahin Pourrahimi
pourrahimi@superconductingsystems.com
5 Fortune Drive
Billerica,  MA 01821-3923
(978) 330-3021

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This program is designed to achieve high operational efficiency for superconducting ADR magnets in space, and to meet space launch requirements. The overall technical objective is to manufacture an efficient magnet using YBCO HTS tapes that can generate 3 T at 30-40 K with an operating current of 5-7 A. To meet this goal we will conduct research and development in areas of: 1) Characterization and use of 1.25 mm YBCO tape in ADR coils. 2) Fabrication of narrower YBCO tapes. 3) Development of low resistance tape-to-tape electrical joints. 4) Quench protection of YBCO ADR coils operating at 30-40 K. 5) Design and manufacturing of a 3 T, YBCO ADR magnet. 6) Testing of the 3 T magnet at 30-40 K.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Many next generation satellite detectors and space telescopes require detectors to be cooled to temperatures of below 0.1 K. Adiabatic Demagnetization Refrigerators (ADRs) offer a practical approach to achieving such low temperatures. Present ADRs operate at 4-10 K requiring substantial cryocoolers. If an ADR system could reject its heat at about 30 K or above, the approach of passive radiative cooling can come into serious consideration whereby mechanical cryocoolers can be totally removed from the overall cooling system. This can be a significant breakthrough that opens the door to a wider application of ADRs in space application, as well as other superconducting magnets in space in general.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Currently many commercial superconducting magnets use Nb-Ti or Nb3Sn wires and are cryogen-free. These magnets use commercial cryocoolers that can achieve cooling capacity of 0.5-3 W at 4-10 K. The input power requirement of these expensive cryocoolers range between 3-5 KW, and they can weigh in access of 100 Kg. Magnets fabricated with HTS wires/tapes that operate at 30-40 K can be operated by simple and less expensive single-stage cryocoolers. This breakthrough technology will have a significant impact on efficiency of superconducting magnets used in motors, actuator, imaging devices, high-power electric propulsion, and detectors with potential use in space applications.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Superconductors and Magnetic


PROPOSAL NUMBER: 09-2 S1.07-9643
PHASE-1 CONTRACT NUMBER: NNX10CD65P
SUBTOPIC TITLE: Cryogenic Systems for Sensors and Detectors
PROPOSAL TITLE: Micromachined Active Magnetic Regenerator for Low Temperature Magnetic Coolers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-0071
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Weibo Chen
wbc@creare.com
P.O. Box 71
Hanover,  NH 03755-0071
(603) 603-3800

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's future science missions to investigate the structure and evolution of the universe require highly efficient, very low temperature coolers for low noise detector systems. We propose to develop a highly efficient, lightweight Active Magnetic Regenerative Refrigeration (AMRR) system that can continuously provide remote/distributed cooling at temperatures in the range of 2 K with a heat sink at about 15 K. The AMRR system uses a vibration-free, reversible cryogenic circulator and Micromachined Active Magnetic Regenerators (MAMRs) to achieve a large cooling capacity and very high thermal efficiency. The MAMRs use an innovative flow channel configuration and novel micromachining technologies to achieve very high thermal and flow performance. In Phase I we proved the feasibility of our approach by demonstrating critical fabrication methods for the micromachined regenerator and its thermal and flow performance through detailed analysis. In Phase II we will build and demonstrate a full-scale micromachined regenerator for a prototype AMRR system that can provide 70 mW of cooling near 2 K. In Phase III we will demonstrate the operation of an AMRR system incorporating the MAMRs and Creare's innovative reversible cryogenic circulator.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed AMRR system will enable NASA to carry out future science missions that use cryogenic infrared, gamma ray, and X-ray detectors. Potential missions include the International X-Ray Observatory (IXO) and the Single Aperture Far-Infrared observatory (SAFIR). These detectors need to operate at temperatures in the range of 4 K to below 1 K to reduce the thermal emission of the detectors themselves and to achieve high sensitivity and resolution. The vibration-free, lightweight AMRR can provide efficient cooling for these missions at the required temperature ranges. The fabrication technologies developed for the magnetic regenerator can also be applied to the fabrication of advanced regenerators for mechanical cryocoolers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The military applications for the proposed magnetic cooler include cooling systems on space-based surveillance, missile detection, and missile tracking systems. Scientific applications include cooling systems for material microanalysis using X-ray microcalorimeter spectrometers, cryogenic particle detectors, and biomolecule mass spectrometry using superconducting tunnel junction detectors.

TECHNOLOGY TAXONOMY MAPPING
Cooling


PROPOSAL NUMBER: 09-2 S1.08-8772
PHASE-1 CONTRACT NUMBER: NNX10CD66P
SUBTOPIC TITLE: In Situ Airborne, Surface, and Submersible Instruments for Earth Science
PROPOSAL TITLE: Hyperspectral Image Projector with Polarization Capability

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Boulder Nonlinear Systems, Inc.
450 Courtney Way, Unit 107
Lafayette, CO 80026-8878
(303) 604-0077

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Tanner
mtanner@bnonlinear.com
450 Courtney Way, Unit 107
Lafayette,  CO 80026-8878
(303) 303-0077

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this proposal is improve testing and calibration of imaging sensors used on remote sensing platforms through the development of calibrated scene projector, the Polarization Hyperspectral Image Projector (PHIP). Current calibration methods utilize spatially uniform optical radiation sources to ensure that sensors meet radiometric, polarization and spectral requirements, without the sensor being subjected to complex spatial /spectral / polarization imagery more typical of an operational scenario. As a result, instrumentation is sent into orbit without proper characterization, neglecting the very real effects of stray light, optical cross-talk and earth-shine. The proposed instrument will be capable of projecting realistic scenes to sensors under test, with accurate and high-resolution spectral/spatial /polarization tunability at each pixel.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed PHIP instrument would be of benefit in calibrating imaging sensors in a number of NASA programs, including: Aerosol Polarimetry Sensor Visible Infrared Imager Radiometer Suite (VIIRS) Instrument Incubator Program Sensors ? including the proposed Ocean Color Radiometer (ORCA).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The outcome of Phase II development will be a Polarization Hyperspectral Imaging Projector. Beyond the calibration of remote sensing instruments, applications include; Digital Tissue Phantoms (Simulations of medical imagery), Factory Calibration of CMOS Sensors, Quality Control of Photographic Film Materials, Machine Vision Simulation, Polarization-Spatial-Spectral Illumination Sources.

TECHNOLOGY TAXONOMY MAPPING
Optical


PROPOSAL NUMBER: 09-2 S1.08-9140
PHASE-1 CONTRACT NUMBER: NNX10CC26P
SUBTOPIC TITLE: In Situ Airborne, Surface, and Submersible Instruments for Earth Science
PROPOSAL TITLE: Atmospheric Aerosol Analysis using Lightweight Mini GC

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Seacoast Science, Inc.
2151 Las Palmas Drive, Suite C
Carlsbad, CA 92011-1575
(760) 268-0083

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Marcel Benz
mbenz@seacoastscience.com
2151 Las Palmas Drive, Suite C
Carlsbad,  CA 92011-1575
(760) 268-0083

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The major components of manmade aerosols are created by the burning of coal and oil. Aerosols are recognized to significantly impact the climate through their effects on solar and terrestrial radiation. Accurate speciation and measurement of aerosol composition is an important first step in understanding and managing these pollutants. This Phase II proposal continues development of a small, portable, detection system specifically for the collection, speciation and identification of gas phase and aerosolized organics. This Mini Gas Chromatograph collects samples and operates without the need for compressed-bottled gas by using Seacoast's proprietary chemicapacitive sensor array and commercial sensors with a preconcentration/chromatography system, combining selectivity from a diverse sensor array with a miniature sampling system for amplified sensitivity. Specific components are: 1) sample preconcentrator/collector capable of being heated quickly, 2) capillary column to separate the chemicals released from the preconcentrator and provide selectivity, 3) the chemical sensor array containing Seacoast's chemoselective microcapacitors and metal-oxide-based detectors, 4) integrated user interface. In Phase I Seacoast demonstrated that the system is capable of analyzing gas-phase and aerosolized volatile organics. In Phase II we propose to further develop the system's capabilities with a focus on improving sensitivity and collection efficiency.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This program provides environmental researchers, who study atmospheric pollutants, with a low-cost miniature gas and aerosol analyzer, allowing for direct measurement of chemicals from a variety of polluting industries, clouds, and plumes, by providing a lightweight low-powered system that can be launched in balloons or UAVs. When coupled with GPS, the system could be used to map plumes from many sources. For example, the Mini GC can contribute to the ongoing research on the Gas and Aerosol Monitoring Sensorcraft (GAMS), which is often carried out by applying analytical instrumentations to an airplane or spacecraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential government customers include researchers at the NOAA, USDA, EPA, and DOE. The product will continuously monitor organic aerosols in the environment and automatically log data. This system has broad relevance for regulatory compliance and environmental research. By developing diverse sensor arrays these systems could be used for monitoring of industrial processes for both quality and process control. The resulting benefits are significant when considering the possible use of these "electronic noses" in any number of industries, from food processing, petrochemicals, specialty chemicals, and waste handling and disposal. Consumer and food industries require methods to improve their batch-to-batch processes, reduce contaminants, and reduce off odors that come from packaging. Chemical industries need detectors for leaks of toxic or explosive vapors as well as contamination detection in process streams. Civilian applications include monitoring drinking water for MTBE, pesticides, or fuels, while military applications include detecting toxic or explosive agents in fuels.

TECHNOLOGY TAXONOMY MAPPING
Portable Data Acquisition or Analysis Tools
Biochemical
Sensor Webs/Distributed Sensors


PROPOSAL NUMBER: 09-2 S1.08-9355
PHASE-1 CONTRACT NUMBER: NNX10RA64P
SUBTOPIC TITLE: In Situ Airborne, Surface, and Submersible Instruments for Earth Science
PROPOSAL TITLE: Calibration/Validation Technology for the CO2 Satellite

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Atmospheric Observing Systems, Inc.
1930 Central Avenue, Suite A
Boulder, CO 80301-2895
(303) 443-3389

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. James Smith
jim@aosinc.net
1930 Central Avenue, Suite A
Boulder,  CO 80301-2895
(303) 817-6854

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
AOS has shown that it is feasible to use the combined NASA/SBIR resources from Phases I and II to: (i) Build a turn-key analyzer system that has the dual-band/differential architecture and is small, light and sensitive enough to be deployed in the smallest zone of the Global Hawk (GH); (ii) Demonstrate TRL 9 and flight readiness of the analyzer system for deployment on the GH and (iii) Validate the analyzer system for observations of CO2 DMF by double-blind comparison with the flask sampling technology of NOAA/GMD and by broadband comparison with an AOS analyzer system that have been validated on hundreds of airborne missions. The net result of Phase II will be a TRL 9 CO2 analyzer system that can be deployed on the GH as needed for NASA field studies and validation of CO2 satellites.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
(i) CO2 analyzer payloads appropriate for the platforms of NASA's Airborne Science Program. (ii) Validation/calibration of the atmospheric CO2 column observed by satellite. (iii) Calibration of ground-based line of sight calibrators (TCON) of the CO2 satellite. (iv) Studies of atmospheric CO2 as part of detailed process studies of oceanic and terrestrial environments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
(i) Drop-in CO2 analyzer payload for great range of platforms to include robotics and the cabin of conventional aircraft. (ii) Studies of atmospheric CO2 as part of detailed process studies of oceanic and terrestrial environments. (iii) Improvement of all CO2 analyzer technologies invented and developed by AOS, Inc. for a substantial range of robotic and manned platforms.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Operations Concepts and Requirements
Training Concepts and Architectures
Testing Facilities
Testing Requirements and Architectures
Optical
Photonics


PROPOSAL NUMBER: 09-2 S1.08-9682
PHASE-1 CONTRACT NUMBER: NNX10CE98P
SUBTOPIC TITLE: In Situ Airborne, Surface, and Submersible Instruments for Earth Science
PROPOSAL TITLE: Compact Instrument for Measurement of Atmospheric Carbon Monoxide

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Southwest Sciences, Inc.
1570 Pacheco Street, Suite E-11
Santa Fe, NM 87505-3993
(505) 984-1322

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alan Stanton
astanton@swsciences.com
1570 Pacheco Street, Suite E-11
Santa Fe,  NM 87505-3993
(505) 505-1322

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Southwest Sciences proposes to continue the development of a rugged, compact, and automated instrument for the high sensitivity measurement of tropospheric carbon monoxide (CO) and methane. The application of recently developed room temperature vertical cavity diode lasers (VCSELs)operating near 2300 nm permits the development of sensitive and rugged instrumentation for measurement of both atmospheric CO and methane with high precision. Phase 1 efforts successfully addressed the feasibility of measuring CO to a precision of 10 parts-per-billion or better over a range of tropospheric temperatures, pressures, and humidity. Phase 2 will extend the technology to simultaneous measurement of both carbon monoxide and methane. The principal objective is the development of prototype instrumentation for field testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Successful development of a VCSEL-based instrument for high sensitivity measurement of tropospheric carbon monoxide and methane will allow NASA to adopt a single high-reliability system for measurement of these two important gases using a wide variety of platforms (e.g. aircraft, balloons, ground-based network, etc.). The instrument will be very compact and low-power, designed for long-term operation with minimal attention and maintenance. The instrument is expected to find use in validation of remote sensing data obtained in planned NASA missions (e.g. ASCENDS and GEO-CAPE). Longer term NASA applications could include adaptation of the instrument for measurements in planetary atmospheres, via use of space-qualified electronics and further ruggedization of the mechanical and thermal design. Applications could include measurements of atmospheric gases on Mars (e.g. water vapor, methane), Titan (methane, ethane), or other future planetary missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology will have direct commercial application in new instrumentation for atmospheric research. Other important commercial applications include combustion monitoring and control, and toxic gas sensing. The instrumentation design could also be adapted to measurement of hazardous or toxic gases, or other trace species, by appropriate selection of laser wavelengths. VCSELs operating in the same general wavelength region, for example, could be used for measurement of two other atmospheric species, nitrous oxide (N2O) and water vapor.

TECHNOLOGY TAXONOMY MAPPING
Optical


PROPOSAL NUMBER: 09-2 S1.08-9774
PHASE-1 CONTRACT NUMBER: NNX10CD67P
SUBTOPIC TITLE: In Situ Airborne, Surface, and Submersible Instruments for Earth Science
PROPOSAL TITLE: Small Submersible Robust Microflow Cytometer for Quantitative Detection of Phytoplankton

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Translume, Inc.
655 Phoenix Drive
Ann Arbor, MI 48108-2201
(734) 528-6371

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Haddock
tomhaddock@translume.com
655 Phoenix Drive
Ann Arbor,  MI 48108-2201
(734) 528-6135

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Marine phytoplankton are critical in sustaining life on Earth. They are key drivers of the global biogeochemical cycles of carbon and other nutrients, and account for 50% of global photosynthesis. Phytoplankton growth is the fundamental component of the 'ocean biological pump' ? one of the two primary mechanisms that cause the ocean to be a significant sink of atmospheric carbon dioxide. Since different taxa occupy different ecological niches, identifying the major influences on the spatial and temporal distribution of phytoplankton groups is necessary to understand ecosystem function and the role of the oceans in global climate. Scientists employ various satellite sensors to measure the amount and distribution of chlorophyll a, an indicator of phytoplankton biomass in the ocean, but satellites only detect near-surface properties and therefore cannot adequately resolve the water column biomass and composition of phytoplankton species. Small and robust sea-based instrumentation (the innovation of this work) provides this information, as well as valuable independent verification of the spaced-based data ("sea truth" data). The objective of this program is to develop a small, inexpensive, submersible, robust microflow cytometer (uFC) for quantitative detection of phytoplankton, to be initially deployed on the NSF Center for Coastal Margin Observation & Prediction coastal ocean observatories (Oregon). The device will be designed for long-endurance autonomous operation. The proposed design has low power requirements, reduces or eliminates consumables, prevents of fouling, and reduces sensitivity to the environment. Our Phase 2 technical objectives are to (1) fabricate a complete uFC with all the subsystems necessary for extended autonomous operational deployment; (2) test our uFC on a coastal station operated by CMOP/OHSU. (3) Deploy our mFC on a submarine glider operated by CMOP/OHSU (4) Collect data at-sea, along the coast of Oregon/Washington.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Scientists employ satellite-based sensors to measure the amount and distribution of chlorophyll a, an indicator of phytoplankton biomass in the ocean. For example NASA's Aqua satellite is monitoring red-light fluorescence emitted by phytoplankton. Red-light fluorescence reveals insights about the physiology of marine plants and the efficiency of photosynthesis, as changes in fluorescence emission reflect the amount of light and nutrients available for growth. The instruments onboard these satellites must be calibrated, and the algorithms applied to the collected raw data need to be validated. Therefore it is important to have sea-based instrumentations to provide an independent verification and confirm the validity of the data collected using spaced-based platforms. These validation instruments are typically deployed on buoys in coastal zones and research vessels out in the open ocean. Current sensors for at-sea applications are expensive, physically large, and have considerable consumable needs. Our proposed low-cost sensor will allow for more extensive deployment of units and allow for more extensive verification and calibration of satellite data, thus enhancing NASA's Earth science research capabilities. It will be extremely robust and capable of operating in an autonomous or semi-autonomous basis for extended periods. In addition, should there be a mission to Europa, this technology may be of use on such a mission under that moon's ice field.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The goal of this program is to fabricate a small, submersible, robust, microflow cytometer uFC for quantitative detection of phytoplankton. In situ detection of phytoplankton is a niche market directed at climate and environmental research. This market is growing. There are more than 200 underwater gliders currently deployed for scientific research. Our uFC will ultimately be a common option on these underwater platforms. In order to achieve significant penetration of this market, the equipment price needs to be reasonable and its operation/deployment simple. We are well positioned to meet these requirements. There are significantly larger research markets for our uFC. For example NOAA has deployed ARGO, a global array of 3,000 free-drifting profiling floats that measure the temperature and salinity of the upper 2000 m of the ocean. These buoys could be equipped with our uFC. Additional units could be deployed onboard seagoing cargo ships to monitor the open ocean. The Navy has interest in better methods of detecting phytoplankton blooms, as they can interfere with submarine navigation or detection, and they are also interested in water quality issues associated with coastal assets. There are major commercial developments to pursue the use algae as a biofuel source. This emerging industry will need a means to monitor algae growth, which could be served by a variant of our uFC. There are also proposed water standards that call for algae monitoring.

TECHNOLOGY TAXONOMY MAPPING
Biomass Production and Storage
Optical
Photonics


PROPOSAL NUMBER: 09-2 S1.08-9836
PHASE-1 CONTRACT NUMBER: NNX10RA80P
SUBTOPIC TITLE: In Situ Airborne, Surface, and Submersible Instruments for Earth Science
PROPOSAL TITLE: Water Properties Sensor

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Kaitech, Inc.
22 Mariners Drive
Marshfield, MA 02050-3158
(781) 837-8465

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Cox
tooque@earthlink.net
22 Mariners Drive
Marshfield,  MA 02050-3158
(781) 781-8465

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this Phase II project, Kaitech proposes to develop and demonstrate a Water Properties Sensor (WPS) sensing system to synchronously measure the spectral inherent and apparent optical properties and the physical properties of oceanic, coastal, and fresh water. This single instrument will provide oceanographers with a small, easy to deploy, affordable, and adaptable integrated sensing system to collect and measure geospatial information of the in situ water's fundamental marine processes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The WPS's applications have capabilities to support NASA's earth science programs to gather the in situ measurements of environmental conditions impacting the marine processes. Basic programs this instrument can support include: NASA's Ocean Biology and Biogeochemistry and Applied Sciences programs, its Integrated Ocean Observing System (IOOS) program, its regional coastal research, and NASA's satellite measurement calibration and validation programs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include supporting marine field studies for coastal research by Federal, state, and local resource managers.

TECHNOLOGY TAXONOMY MAPPING
Portable Data Acquisition or Analysis Tools
Optical
Sensor Webs/Distributed Sensors
Photonics
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S1.09-8528
PHASE-1 CONTRACT NUMBER: NNX10CE04P
SUBTOPIC TITLE: In Situ Sensors and Sensor Systems for Planetary Science
PROPOSAL TITLE: Thermopile Detector Radiation Hardened Readout

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Black Forest Engineering, LLC
P.O. Box 8059
Colorado Springs, CO 80933-8059
(719) 593-9501

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Stephen Gaalema
sgaalema@bfe.com
P.O. Box 8059
Colorado Springs,  CO 80933-8059
(719) 593-9501

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA Jupiter Europa Orbiter (JEO) conceptual payload contains a thermal instrument with six different spectral bands ranging from 8m to 100m. The thermal instrument is based on multiple linear arrays of thermopile detectors that are intrinsically radiation hard; however, the thermopile CMOS readout needs to be hardened to tolerate the radiation sources of the JEO mission. Black Forest Engineering (BFE) is developing a thermopile readout to tolerate the JEO mission radiation sources. On Phase II, BFE will test new circuitry for radiation hardness, complete the design of a 1x128 thermopile readout integrated circuit (ROIC) and fabricate the ROIC using 180 nm CMOS technology. The Phase II ROIC also includes on-chip 16-bit analog-to-digital conversion and serial digital output for system noise immunity. The Phase II ROIC will be characterized to meet the JEO thermal instrument requirement.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The potential NASA application is a thermopile detector readout to support the Europa Jupiter System Mission (EJSM) and specifically the Thermal Instrument proposed for inclusion in the Jupiter Europa Orbiter (JEO). The JEO is the NASA element of the EJSM and is due to launch in February 2020 and arrive at Jupiter in December 2025. The thermopile detector readout is also suitable for spectrometers operating in push-broom mode imaging and remote sensing from a wide variety of platforms.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ROIC for thermopiles has applicability to commercial spectrometers used to check the condition of fluids for degradation and the presence of contaminants. The ROIC capability represents opportunity to reduce size, weight and power of commercial spectrometers and also increase performance. The thermopile ROIC also has applicability in thermopile based spectrometers for low concentration detection and identification of airborne chemicals.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Control Instrumentation
Ultra-High Density/Low Power
Optical
Photonics
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 S1.09-9459
PHASE-1 CONTRACT NUMBER: NNX10CF13P
SUBTOPIC TITLE: In Situ Sensors and Sensor Systems for Planetary Science
PROPOSAL TITLE: Compact Vacuum Pump for Titan Lander Missions

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-0071
(603) 643-3800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Sorensen
phs@creare.com
P.O. Box 71
Hanover,  NH 03755-0071
(603) 603-3800

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For a number of years Creare has developed, fabricated, and tested highly miniaturized, high vacuum pumps specifically designed for mass spectrometers used on NASA Mars missions. These pumps would also be useful on other missions to planets and satellites with atmosphere, such as Titan, as well as terrestrial applications on Earth. In order to allow these high vacuum pumps to operate in high-pressure environments such as exist on Titan and Earth, the vacuum pump needs to be supplemented with a rough pump that can take its exhaust and compress it to 1?1.5 atm. This project aims to design, fabricate, test, and deliver such a compact vacuum pump system that can generate a high vacuum, on the order of 1e-8 torr, and exhaust directly to an Earth or Titan atmosphere. The pump will be assembled in a very compact, robust, and low-power package. Our Phase I project clearly demonstrated the feasibility of our innovative design by demonstrating the performance of a rough pump and designing a compact vacuum system for use on Earth or other planetary bodies with atmospheric pressure greater than 1 atm. During Phase II of this project, we will build a complete benchtop pumping system that meets the requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The pumping system developed during this project is tailored to provide the vacuum necessary for a number of instruments, notably miniature mass spectrometers, leak detectors, miniature electron microscopes, etc. Such instruments are of scientific interest on future missions (e.g., to Titan), for Earth atmospheric sampling, for volcano emission monitoring, for ISS environmental monitoring, and for numerous other missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Numerous commercial applications exist for the proposed compact vacuum pump, primarily to support portable analytical instruments such as mass spectrometers and leak detectors. Current-generation devices are limited by the size and mass of their high vacuum and rough pumps, or else use less capable absorption pumps. Building a small, low mass, low-cost, and low-power high vacuum pump whose performance is tuned to the needs of miniature detectors and can exhaust to greater than 1 atmosphere is expected to greatly expand the market for such devices. The pump technology to be developed under this proposal will be used in instruments being developed by some of our partners in portable mass spectrometers for use by the Department of Homeland Security and the Defense Threat Reduction Agency.

TECHNOLOGY TAXONOMY MAPPING
Biochemical


PROPOSAL NUMBER: 09-2 S1.09-9778
PHASE-1 CONTRACT NUMBER: NNX10CC27P
SUBTOPIC TITLE: In Situ Sensors and Sensor Systems for Planetary Science
PROPOSAL TITLE: An Infrared Fiber-Optic Raman Sensor for Field Detecting of Organic Biomarkers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Crystal Research, Inc.
48501 Warm Springs Blvd., Suite 103
Fremont, CA 94539-7750
(510) 445-0833

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Suning Tang
suningtang@eocrystal.com
48501 Warm Springs Blvd., Suite 103
Fremont,  CA 94539-7750
(510) 445-0833

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The search for organics on Mars remains a key objective for future missions. However current instruments for detailed organic analysis require complex sample handling and can process only a limited number of samples. To allow for rapid sample characterization, the in situ non-destructive Raman detection technique is a highly desirable sensing tool for both qualitative and quantitative analysis. However, current Raman systems deployed in the field are inadequate due to deleterious fluorescence interference. Fluorescence is often several orders of magnitude more intense than Raman scattering signals and its broad structures spectrum could be difficult to remove from Raman spectra. We propose to develop a rover-mounted infrared fiber-optic Raman sensor that can eliminate fluorescence with significantly improved Raman sensitivity for fast field detections. The infrared fiber-optic Raman sensor is based on recent technology advances in fiber lasers, fiber optic Raman probes and infrared detector arrays. Innovative infrared fiber-optic Raman sensor enables highly sensitive fluorescence-free Raman analysis and offers flexible remote detection, so that the field spectral sensor's overall performance would be intact and extremely flexible for planetary missions. We will deliver a rover-mounted infrared fiber-optic Raman sensor to NASA at the end of Phase II program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed rover-mounted infrared fiber-optic Raman sensor will provide NASA a light weight, low-power consumption, versatile, compact, rugged sensing instrument for rapid in-situ field detection of geological materials. It is a new field detection instrument capable of analyzing solid, liquid, and gaseous samples without firmware changes. The instrument proposed here is relevant to the NASA solicitation topic, "Instrument technologies for detecting inorganic and organic biomarkers on future Mars missions." It will directly support NASA for improving existing NASA flight instrument.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Raman spectroscopy provides information about molecular vibrations that can be used for material identification and quantization. The proposed infrared fiber-optic Raman sensor has wide applications to include environmental monitoring, homeland security, life science, matter physics, chemistry and bio-fuel production. It offers a non-destructive, non-contact method of qualitative and quantitative analysis suitable for both laboratories based and plant based applications. Currently, Raman spectrometer serves as an important instrument for Homeland Defense. It can be used for the bulk identification of explosives, chemical warfare agents, and other hazardous chemicals.

TECHNOLOGY TAXONOMY MAPPING
Biomolecular Sensors
Waste Processing and Reclamation
Optical
Sensor Webs/Distributed Sensors
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 S1.11-8154
PHASE-1 CONTRACT NUMBER: NNX10CF14P
SUBTOPIC TITLE: Lunar Science Instruments and Technology
PROPOSAL TITLE: Remote UV Fluorescence Lifetime Spectrometer

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Redondo Optics, Inc.
811 N. Catalina Avenue, Suite 1100
Redondo Beach, CA 90277-2187
(310) 406-1295

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Edgar Mendoza
emendoza@redondooptics.com
811 N. Catalina Avenue, Suite 1100
Redondo Beach,  CA 90277-2187
(310) 310-7673

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this project is to develop, demonstrate, and deliver to NASA an innovative, portable, and power efficient Remote UV Fluorescence Lifetime Spectrometer (RUVPhase<SUP>TM</SUP>) for the in-situ robotic or manned crew planetary scientific exploration and investigation of surface and subsurface geophysical terrain. The RUVPhase<SUP>TM</SUP> system is based on the integration of ROI's leading technologies: 1) frequency domain fluorescence lifetime-resolved imaging spectroscopy using time gated "phase-locked" detection, 2) steady-state fluorescence miniature spectrometer, and 3) remote fiber optic laser induced UV fluorescence detection. The RUVPhase<SUP>TM</SUP> technology addresses the problem of developing a compact, energy efficient, fast detection, and highly sensitive UV Fluorescence Lifetime Spectrometer to remotely detect and measure fluorescence signals from geophysical lunar materials such as minerals and organic species that exhibit characteristic fluorescence signatures in the UV-Visible spectrum with relatively low fluorescence quantum efficiencies. The innovativeness of the miniature RUVPhase<SUP>TM</SUP> system will support a large variety of NASA terrestrial and space scientific discovery applications for chemical and biological materials identification and characterization as well as in the commercial market for medical and biological applications, chemicals and pharmaceuticals, environmental science, and defense and homeland security applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The RUVPhase<SUP>TM</SUP> system will support a large variety of NASA terrestrial and space scientific applications for inorganic, organic, and biological materials identification and characterization. NASA has a need for advanced, lightweight, and power efficient scientific instrumentation that enable the remote or manned operated planetary scientific exploration of subsurface and surface geophysical measurements. The Lunar surface and subsurface is composed of a variety of mineral species that absorb light of certain wavelengths and emits light of other wavelengths. These emissions and absorptions create a "spectral signature" that can be use to identify and classify the mineral composition and its genealogical history.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The RUVPhase<SUP>TM</SUP> technology products are expected to find wide applications for NASA and in military, government, and civilian remote fluorescence sensing applications. The specific commercial market for such innovative spectrometers with fast growing emerging markets include the biomedical, pharmaceutical, chemical and petro-chemical, environmental, and geophysical fluorescence instrumentation market. Explosive markets ROI currently addresses with the RUVPhase<SUP>TM</SUP> technology include fluorescence DNA sequencing, remote fluorescence monitoring of chemical and biological agents in military and homeland security applications, fluorescence monitoring of vegetation and marine life stress affected by the oil spill in the Gulf of Mexico, and fluorescence cryogenic gas leak sensing. Technology innovation is the driving force that has opens spectroscopic applications to new markets. These new markets and applications ins turn are driven by new instrument designs that are compact, lower cost, more functionality, and better performance.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Perception/Sensing
Biomedical and Life Support
Biomolecular Sensors
Instrumentation
Portable Data Acquisition or Analysis Tools
Biochemical
Optical
Sensor Webs/Distributed Sensors
Manned-Maneuvering Units
Photonics
Optical & Photonic Materials
Organics/Bio-Materials
Biophysical Utilization


PROPOSAL NUMBER: 09-2 S1.11-8566
PHASE-1 CONTRACT NUMBER: NNX10CF16P
SUBTOPIC TITLE: Lunar Science Instruments and Technology
PROPOSAL TITLE: A Compact, Dual Excitation Raman Probe and Instrument for the Identification of Lunar Samples

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
EIC Laboratories, Inc.
111 Downey Street
Norwood, MA 02062-2612
(781) 769-9450

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Job Bello
bello@eiclabs.com
EIC Laboratories, 111 Downey Street
Norwood,  MA 02062-2612
(781) 769-9450

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's Vision for Space Exploration advocates a return to the moon and involves a pl an of using the moon as a base of for missions to other planets. Early return missions to the moon will involve lunar exploration with robotic spacecrafts with instrumental payloads for scientific measurements of lunar surface features such as rocks, soil, and minerals. These instrument payloads will be helpful in identifying lunar resources that can be used in establishing extended human presence. Raman spectroscopy has been actively investigated as a lunar as well as a Mars surface robotic investigative tool for minerals. Current Raman instruments for space exploration utilize a single excitation wavelength, with a laser in the near-infrared (IR) to minimize fluorescence background. The goal of this project is to employ a dual excitation (visible and near-IR lasers) Raman instrument to minimize background emission. To achieve this goal, a dual excitation wavelength fiber optically coupled Raman probe head and a compact wide spectral range echelle spectrograph were demonstreated in Phase I. Phase II will integrate the probe into a compact instrument for mineralogical analysis capable of deployment on a rover-type of vehicle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The NASA application for the dual excitation wavelength Raman instrument is for remote lunar and planetary analysis of mineralogical and soil samples. Specific NASA programs include In Situ Resource Utilization (ISRU), The Exploration Robotic Precursor Program (xPRP), astrobiology missions such as the Max-C Mars rover and international programs such as the Exo-Mars.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial market for the instrument will be in manufacturing and pharmaceutical industries, where the Raman instrument can be used as a quality control instrument for raw materials and end products. In addition, the instrument can also be beneficial for first responders for interrogating unknown samples.

TECHNOLOGY TAXONOMY MAPPING
Optical
Photonics
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 S1.11-9088
PHASE-1 CONTRACT NUMBER: NNX10CF17P
SUBTOPIC TITLE: Lunar Science Instruments and Technology
PROPOSAL TITLE: DIHeDRAL: Downhole Regolith Interrogation with Helium-Assisted Drill and LIBS

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W. 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paolo Moreschini
moreschini@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(646) 459-7823

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future landed robotic missions to the lunar poles will seek to characterize the properties of subsurface regolith. Current instruments for such in-situ analysis, however, require that geological samples be brought to the surface by a sample acquisition tool and subsequently processed and presented to the analyzer. This model has significant limitations with regard to science yield: evaporation of volatile molecules before reaching the instrument, loss of stratigraphic information, sample bias, and cross-contamination. Furthermore, sophisticated sample acquisition, processing and handling mechanisms required to operate in uncontrolled, dusty environments are expensive and failure-prone. We therefore propose an alternative: bring the instrument to the sample. Specifically, we propose development of a fiber-coupled laser-induced breakdown spectrometer (LIBS) system, integrated into a 3m-class drill. LIBS uses a high-energy laser pulse to create a plasma on the surface of the material under test; the atomic emissions are collected by a spectrometer and yield elemental composition and basic molecular information. DIHeDRAL will allow profiling of an entire borehole wall, centimeter by centimeter, 360 degrees, from the top to the bottom. The proposed Phase II work will include development of a functional prototype and its integration in a drill string and test to a depth of 1m. The performance of the sensor will be tested in a chamber capable of closely reproducing the conditions of the Lunar surface.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application of DIHeDRAL is in-situ analysis for landed robotic missions to the Moon. As outlined in the National Research Council's report on Scientific Context for Exploration of the Moon, the principal goals of such missions would require detection of water and other volatiles present in the regolith, elemental analysis of the regolith, and establishment of geochronology and bombardment history. LIBS would provide information on elemental composition, and other fiber-coupled instruments could ultimately be incorporated into the same platform, depending on the requirements of the mission. Possibilities include Raman spectroscopy, which would provide more sophisticated analysis of organics and other molecules and potentially Laser Induced Fluorescence (LIF), for higher sensitivity detection. In this scenario, the high-powered LIBS laser doubles as a sort of sample preparation tool; firing a burst of "cleaning shots" exposes fresh sample (including volatiles that may have been lost from the outer surface layer). The DIHeDRAL instrument architecture could also be applied to robotic Mars missions. The focus in this case would likely be on astrobiology as opposed to resource characterization, involving Raman detection and analysis of organics trapped in Mars polar ice.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The successful integration of a LIBS instrument into a drill string or downhole probe would have several significant commercial applications. In the pit mining and quarrying industry, a downhole LIBS probe could be used for rapid rock and ore characterization using existing blast holes. This would allow more streamlined planning of operations and would result in less misclassified material. In defense and homeland security, a version of DIHeDRAL could be used for detection of buried explosives, such as land mines, improvised explosive devices (IEDs), and unexploded ordnance (UXO).

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Optical


PROPOSAL NUMBER: 09-2 S2.01-9277
PHASE-1 CONTRACT NUMBER: NNX10CE07P
SUBTOPIC TITLE: Precision Spacecraft Formations for Telescope Systems
PROPOSAL TITLE: Miniaturized Low-Power Piezo Microvalve for NanoSat and CubeSat Propulsion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Busek Co., Inc.
11 Tech Circle
Natick, MA 01760-1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Douglas Spence
doug@busek.com
11 Tech Circle
Natick,  MA 01760-1023
(508) 655-5565

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the Phase I effort, Busek developed a miniature precision piezo-actuated microvalve weighing 32g and occupying 4.5 cm^3. The valve demonstrated continuous flow regulation of 0-12 sccm nitrogen (15psi supply pressure) thru 0-500 sccm nitrogen (1000psi supply pressure), with a leak rate of better than 1.0 x 10^-5 mbar-l/s. The simple, low part-count design was developed with a critical eye toward low-rejection rate manufacturability, with several sensitive assembly operations successfully advanced toward, robust, reliable processes. Resilience under aggressive shock loading, which exhibited negligible effects upon valve operation, was demonstrated. For the Phase II effort, Busek shall continue refining critical assembly processes to improve reliability in assembly, eliminating remaining elastomers in order to achieve an all-metal architecture. Additionally, a supplementary feature for downstream volume compensation (for regulation of incompressible liquids affected by induced flows due to mechanism actuation and/or liquid thermal expansion; a necessary feature for colloid thruster operation) shall be developed. Supporting the colloid application shall be valve driver electronics able to float at thruster beam Voltage. The design shall be validated via vibration and thermovac testing, and culminate in operation of both a gas-based thruster, as well as a colloid thruster to validate the volume compensation feature.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications for the proposed technology include the following: ? Enhanced precision control and decreased valve power consumption for cold gas thrusters. Currently, cold gas thrusters operate using 'bang bang' valves that require significant power and relatively coarse thrust control. The proposed valve design requires negligible power due to its piezo-based actuator, and its flow resolution promises to enhance greatly the controllability of cold gas thrusters, enabling their use in higher-precision formation flying missions. ? Precision metering of gaseous constituents for chemical propulsion and miniature ion and Hall thrusters. ? Improvement to the extant fluid-regulating microvalve for liquid propulsion applications. ? Propellant valves for colloid thrusters on LISA mission

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA commercial applications for the proposed technology include the following: ? Precision metering of gases for chemical/process/pharmaceutical/semiconductor industries. ? Replacement of arrayed and independently valved sonic chokes with a single valve.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Micro Thrusters
Electrostatic Thrusters
Feed System Components


PROPOSAL NUMBER: 09-2 S2.02-9229
PHASE-1 CONTRACT NUMBER: NNX10CE08P
SUBTOPIC TITLE: Proximity Glare Suppression for Astronomical Coronagraphy
PROPOSAL TITLE: Compact Low-Power Driver for Deformable Mirror Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Boston Micromachines Corporation
30 Spinelli Place
Cambridge, MA 02138-1070
(617) 868-4178

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Stewart
jbs@bostonmicromachines.com
30 Spinelli Place
Cambridge,  MA 02138-1070
(617) 868-4178

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes a new concept to drive MEMS DMs using low-power, high-voltage multiplexing. Compared to other reported approaches, the proposed architecture will reduce power consumption by a factor of one hundred, to a level of a few hundred milliwatts. This estimate is supported by direct measurements obtained from prototype modules that were demonstrated in Phase I research. In the Phase II project we will scale up this innovative circuit DMs that Boston Micromachines Corporation (BMC) developed for NASA in support of the Terrestrial Planet Finding program. At the same time, we will reduce the driver's size in two successive stages of integration. In the first stage, we will implement a hybrid packaging approach in which a 993-actuator DM, HV amplifier, multiplexer components, and power supplies will all be co-located on a common multi-layered circuit board. With this driver we will demonstrate both low power consumption (~300mW) and high precision (~10pm). In the second stage of integration, we will design, fabricate, and test a High Voltage Application-Specific Integrated Circuit (HV-ASIC) version of the multiplexing architecture using a commercial foundry. We will combine a number of these 256 channel HV-ASIC modules into a driver for a 3063 actuator DM that is currently being developed by BMC to support NASA's coronography goals.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Multiplexed drive electronics introduce a few very important and enabling advantages for NASA commercial applications in planned space-based telescopes and coronagraphs. The key commercial advantages to the systems to be produced in this work are: 1) their hundredfold improvement in power efficiency is a critical enabler for space-based operation; 2) their design is specifically suited to drive tip-tilt-piston MEMS DMs already developed by BMC for NASA, and is to our knowledge uniquely capable of achieving the 10pm precision required for the visible nulling coronagraph; and 3) the cost to produce the drivers proposed will be less than that of existing drivers for MEMS DMs in use by NASA, despite its substantial improvements over the state-of-the-art in compactness, power management, and precision. These compelling features, along with highly successful Phase I results, promise to make the proposed hardware commercially attractive to NASA for various space-based applications. BMC's track record of success with DM sales to NASA and to dozens of astronomical and space science institutions around the world bodes well for the ultimate commercial viability of the Phase II research outcomes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Small stroke, high precision deformable mirrors and associated drive electronics have a few commercial applications. The decrease in size, power and cost affect many of the vertical markets to which we currently supply our products. Space surveillance:BMC has success developing arrays up to 4096 elements for astronomy which can be used for space-based systems. Decreasing the size and weight of the electronics reduces payload, a high priority of satellite programs. These programs are funded by Department of Defense administrations with classified agendas. Unmanned Aerial Systems:In unmanned aerial systems, adaptive optics can enable improved battlefield performance. Images can be obtained that are more informative for reconnaissance purposes. By implementing multiplexed drive electronics, this can be implemented on smaller vehicles. Microscopy:Adaptive optics can increase resolution in confocal and optical microscopes. Specific modalities include two-photon excitation fluorescence(2PEF), coherent anti-stokes Raman spectroscopy(CARS), scanning laser ophthalmoscopy(SLO) and optical coherence tomography(OCT). Multiplexed drive electronics can reduce the component cost of the system and enable more users to purchase high-resolution equipment for cutting-edge science. Optical communication: Fiber optic communications systems are the primary beneficiaries of this new electronics architecture which can take advantage of our devices in an optical switching enhancement capacity.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Laser
Optical
Power Management and Distribution


PROPOSAL NUMBER: 09-2 S2.02-9231
PHASE-1 CONTRACT NUMBER: NNX10CE09P
SUBTOPIC TITLE: Proximity Glare Suppression for Astronomical Coronagraphy
PROPOSAL TITLE: Enhanced Fabrication Processes Development for High Actuator Count Deformable Mirrors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Boston Micromachines Corporation
30 Spinelli Place
Cambridge, MA 02138-1070
(617) 868-4178

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Cornelissen
sac@bostonmicromachines.com
30 Spinelli Place
Cambridge,  MA 02138-1070
(617) 868-4178

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to design and fabricate a MEMS micromirror array consisting of 1021 ultra-flat, close-packed hexagonal mirror elements, each capable of 6mrad of tip and tilt, and 1.7um of piston (TTP) motion with sub-nanometer precision as required for a space-based telescope using a hyper-contrast coronagraph for terrestrial planet finding. Fabrication process enhancements developed in the Phase I effort to increase device yield by significantly reducing the defect density in polysilicon films and reduce wafer bow by modifying thin film deposition processes, will be integrated in to the DM fabrication process to produce a device with 100% actuator yield and an unpowered peak-to-valley surface figure error of <500nm - well within the dynamic range of the DM actuators. This large array of mirror segments with tip-tilt-piston degrees of freedom and &#955;/100 optical quality would constitute a significant technological advance and would become an enabling component for the high contrast visible nulling coronagraph instruments planned for exoplanet imaging missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application for small stroke, high precision deformable mirrors is that of space-based imaging and in specific, exo-planet research. As telescopes and coronagraphs are constructed, they will require control of light using adaptive optics over a larger aperture. By expanding the size of DM devices, instruments such as PECO, ACCESS, EPIC, DaVinci, and FKSI will be able to shape more light using less hardware and less stages. Given the current constraints on fabrication technology, it is necessary to develop new methods of manufacture to accommodate for larger arrays which also require more channels for control. The desire for this type of enhanced technology within the astronomy community has been detailed in a report issued from the Association of Universities for Research in Astronomy, an influential consortium which is a voice in the United States of the industry at-large.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are a range of Government agencies and commercial markets that can take advantage of small stroke, high precision deformable mirrors. One application is for large, ground-based telescopes. By expanding the size of DM devices, these observatories will be able to shape more light using less hardware and less stages. Another application is long-range optical communications (lasercomm) systems for use in satellites, airborne vehicles and ground-based nodes requiring a secure, dependable connection. By creating larger, higher-precision arrays, not only is it possible to send more data at faster rates, but the distance between communication points can be extended due to enhanced error correction capabilities. A third application is for correction of quasi-static aberrations in primary optics in surveillance satellites due to manufacturing and thermal variations. Adding to its advantages of high-resolution capability, the light weight nature of BMC MEMS DM technology allows the payload to be reduced, a high priority of military satellite projects. A final application is that of laser pulse-shaping for material characterization and laser marking and machining. By creating larger arrays, control of the pulsed beams can be enhanced. In addition, the larger arrays will allow users to take advantage of larger beam diameters. This will allow scientists to better understand the composition of materials and allow manufacturers to make larger, more complex patterns.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S2.04-9341
PHASE-1 CONTRACT NUMBER: NNX10CF19P
SUBTOPIC TITLE: Advanced Optical Component Systems
PROPOSAL TITLE: Minimally Machined HoneySiC Mirrors for Low Areal Cost and Density

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Trex Enterprises Corporation
10455 Pacific Center Court
San Diego, CA 92121-4339
(858) 646-5300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bill Goodman
bgoodman@trexenterprises.com
2701 Pan American Freeway NE
Albuquerque,  NM 87107-1647
(858) 437-3899

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A problem perceived for Trex Enterprises chemical vapor composite silicon carbide CVC SiC<SUP>TM</SUP> mirrors is the cost associated with machining and lightweighting the mirrors. Indeed these processes are labor, schedule, risk and cost drivers for our exceptional, high performance variety of silicon carbide material. Although we have made significant strides in improving our baseline CVC SiC<SUP>TM</SUP> manufacturing processes, the product is still substantially higher priced than the goals of the NASA project. In Phase I, we created and demonstrated a manufacturing process for the new ceramic matrix composite honeycomb panel silicon carbide (HoneySiC or H-SiC) which nearly eliminates the machining and lightweighting process steps for mirrors and opto-mechanical structures. The new material achieves lightweighting of 92% relative to bulk material and net production cost on the order of $38K per square meter (unpolished), less than half of NASA's goal of $100K per square meter. Web thickness, core geometries (pocket depth, pocket size), and mirror shape are easily tailored since H-SiC starts as a molded precursor material. The Phase II project will start at Technology Readiness Level 3 (TRL 3, experimental critical function and characteristic proof of concept) and end at TRL 5 (breadboard in a relevant environment).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The great observatories of the future require a mirror technology that is lightweight, dimensionally stable, high performance, and above all else, cost effective. Molded HoneySiC<SUP>TM</SUP> hexagonal panels in sizes of 1-3 meters point-to-point will allow construction of extremely large aperture UV and IR telescopes, at prices for from $38-100K per square-meter, a factor of 40 to 100 times less than present day technology. With appropriate capital equipment and infrastructure it may be possible to produce even larger parts.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low cost, lightweight, dimensionally stable SiC mirrors have use in complex telescopes for Astronomy, Imaging and Remote Sensing applications, including optical instruments/telescopes which enable imaging, surveillance, and reconnaissance missions for police and paramilitary units, fire fighters, power and pipeline monitoring, search and rescue, atmospheric and ocean monitoring, imagery and mapping for resource management, and disaster relief and communications. The dual-use nature of complex telescopes will bring affordability to national defense missions as well.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Large Antennas and Telescopes
Optical
High-Energy
Ceramics
Composites
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S2.05-8780
PHASE-1 CONTRACT NUMBER: NNX10CD71P
SUBTOPIC TITLE: Optics Manufacturing and Metrology for Telescope Optical Surfaces
PROPOSAL TITLE: Coherent Laser Radar Metrology System for Large Scale Optical Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pyxisvision Incorporated
9801 Nugget Court
Bristow, VA 20136-2430
(703) 864-5901

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Anthony Slotwinski
tony.slotwinski@pyxisvision.com
9801 Nugget Court
Bristow,  VA 20136-2430
(703) 703-5901

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new type of laser radar metrology inspection system is proposed that incorporates a novel, dual laser coherent detection scheme capable of eliminating both environmental and scanner based Doppler ranging error. Measurement of large telescope structures and optics requires both high accuracy and non-contact technology. Due to the non-contact, stand-off nature of this technology, this system can measure optics and provide nearly real-time feedback to figuring/polishing instruments without removing the part from the spindle or other optical grinding or polishing setup. For advanced levels of integration and test, the proposed large-volume metrology technology would allow fast, non-contact measurement of mirror rigid body alignment and prescription (i.e., radius, conic, aperture), with no special targets or references on the optic. This would allow these mirror parameters to be measured with respect to other optics, instruments, or mechanical- and spacecraft-related structures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential post-Phase III NASA applications for this innovation include improved performance and lower cost optical telescope assembly and instrument development. Examples of future NASA missions that will benefit include the Joint Dark Energy Mission (JDEM) and the International X-ray Observatory (IXO). For JDEM, telescope mirror fabrication and integration capabilities would be greatly enhanced. The scanner would measure the prescription and coarse figure of the large (~2m) mirror during fabrication and, after fabrication, characterize its final prescription and alignment to the telescope metering structure, with little or no custom fiducialization. The mechanical alignment of the JDEM instrument/camera would meet tighter specifications. For IXO, this improved scanner would be able to measure the super-thin, lightweight, off-axis x-ray segments in a non-contact fashion, eliminating the risk of damage and allowing measurement without distorting the segments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The post-Phase III SBIR, non-NASA commercial applications are numerous and multi-discipline. Aerospace engineering fields that would benefit include: Spacecraft integration, optical telescope assembly, optical instrument assembly, optical component-level fabrication and characterization for both large and small optics, optical metering structure assembly and characterization, and mm-wave antenna fabrication and assembly. In addition, this improved scanner has implications for greatly improving metrology in support of the aircraft and ship-building industry. Similar scanner technologies are currently employed in these areas and this improved scanner would enable better uncertainty, resulting in improved products across the board.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Erectable
Launch and Flight Vehicle
Large Antennas and Telescopes
Structural Modeling and Tools
Optical
Photonics
Earth-Supplied Resource Utilization


PROPOSAL NUMBER: 09-2 S2.05-9386
PHASE-1 CONTRACT NUMBER: NNX10CF20P
SUBTOPIC TITLE: Optics Manufacturing and Metrology for Telescope Optical Surfaces
PROPOSAL TITLE: Removing Mid-Spatial Frequency Errors with VIBE

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimax Systems, Inc.
6367 Dean Parkway
Ontario, NY 14519-8939
(585) 265-1020

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jessica Nelson
jnelson@optimaxsi.com
6367 Dean Parkway
Ontario,  NY 14519-8939
(585) 217-0776

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Optimax VIBE finishing process is a fast (<60 second), full-aperture, conformal polishing process incorporating high frequency motion that rapidly eliminates mid-spatial frequency (MSF) errors created by deterministic polishing. During Phase I, we were able to show feasibility that the Optimax VIBE finishing process was able to reduce the effects of mid-spatial frequency (MSF) errors on flat sub-aperture polished surfaces without negatively affecting the surface figure. With future funding, we anticipate advances this process will result in a cost-effective way to produce ultra-low MSF error curved surfaces for both NASA and non-NASA applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
VIBE technology to reduce and/or eliminate mid-spatial frequency errors has potential to be used for optics in many applications. Specifically those applications that are susceptible to small angle scatter sometimes referred to as flare. The International X-Ray Observatory (IXO), consisting of 361 grazing incidence nested, azimuthally segmented shell mirrors, is susceptible to mid-spatial frequency errors. These thin (0.4mm) mirrors are produced through a thermal slumping technique where a thin glass substrate replicates the shape of a mandrel (fused quartz or stainless steel). The current budgeted error for the IXO mandrels is 1.4nm rms over the 2 20mm spatial frequency range. In addition, exo-planet imaging systems require minimal scattering due to mid-spatial frequency errors on their primary and secondary mirrors. An example is the specification for the Jovian planet finder optical system was less than 1nm rms in the 4 50cycles/aperture range.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications include high energy laser systems, EUV optics (lithography), imaging systems and X-ray synchrotrons. High energy laser applications, such as Inertial Confinement Fusion National Ignition Facility (NIF) at Lawrence Livermore National Laboratory are susceptible to mid-spatial frequency errors. The MSF errors are a source of damaging intensity, specifically in the region of 120&#956;m ? 33mm. In EUV lithography, flare is a significant problem. Flare is directly associated with mid-spatial frequency error. The mid-spatial frequency errors cause light to scatter into small angles and reduce image contrast. The specific mid-spatial frequency region of interest to the EUV lithography community is between 1&#956;m ? 2mm. The mid-spatial frequency error scales as 1/(lambda)^2, which causes an increasingly significant problem as the lithography industry heads toward shorter and shorter wavelength systems.

TECHNOLOGY TAXONOMY MAPPING
Optical
Photonics
Ceramics
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 S3.01-9888
PHASE-1 CONTRACT NUMBER: NNX10CD75P
SUBTOPIC TITLE: Command, Data Handling, and Electronics
PROPOSAL TITLE: Space Qualified, Radiation Hardened, Dense Monolithic Flash Memory

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Space Micro, Inc.
10237 Flanders Court
San Diego, CA 92121-1526
(858) 332-0700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Czajkowski
dcz@spacemicro.com
10237 Flanders Court
San Diego,  CA 92121-1526
(858) 332-0700

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Space Micro proposes to build a radiation hardened by design (RHBD) flash memory, using a modified version of our RH-eDRAM Memory Controller to solve all the single event effects issues (SEU, SEFI and multiple bit errors) using either a RHBD process with NAND Flash cells. The RH-eFlash will be manufactured on known radiation characterized ASIC processes: examples being 130 nm or 65 nm TSMC or other US foundry equivalents. Using the TSMC example, the resulting RH-eFlash, fabricated on a 65 nm process, provides 512 Mbit to 1 Gbit of radiation hardened (SEU, SEFI, SEL and TID) NAND Flash memory. Operating temperature and packaging reliability is addressed through a thorough memory integrated circuit design (temperature) and post IC high-reliability package selections (i.e. ceramic packages). Note that this technology is portable to future available and radiation tested ASIC processes with even finer geometries and high density.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Virtually all NASA space programs have a demand for this proposed technology and product. NASA applications range from space shuttle, space station, earth sensing missions e.g. (EOS), and deep space missions. NASA programs/missions that will benefit include new lunar landers and orbiters e.g. (LADEE), Mars missions, solar system exploration e.g. (Titan, Juno, Europa, comet nucleus return, New Discovery, and Living with a Star (LWS). NASA programs which may continue to be funded by Congress include the Ares launcher, the Orion Crew Exploration Vehicle (CEV) and Commercial Orbiter Transportation Service (COTS) would benefit. Products (NVM devices) evolving from this SBIR will be enabling for future programs such as Dawn, Aquarius, Kepler, Ocean Vector Winds, and space interferometry (SIR).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology and evolving Space Micro products may benefit many commercial space platforms, both LEO and GEO telecommunication satellites, such as Intelsat, Direct TV, XM radio, Orbcomm and Iridium Next telecom constellation replenishment, plus standard industry busses including Lockheed's A2100, and Boeing's HS-702. Civil earth sensing applications such as weather/metrology applications e.g. (NOAA GOES and Landsat) can also benefit. The large DoD space industry, including USAF, MDA, NRO, and new Army nanosat programs at SMDC will directly benefit. Among these programs are AEHF upgrades, GPS follow-ons, MDA's STSS and PTSS, USAF TacSat family, Operationally Responsive Space (ORS), and Army SMDC nanosat family. The entire Cubesat initiative including NRO's Colony program would benefit. This technology and products will also address emerging MDA radiation threats. These programs include AKV, THAAD, AEGIS, MKV, and GMD for Blocks 2014 and beyond. With the new challenge of atmospheric neutrons to High Altitude Airship (HAA) programs and NASA or Air Force UAV programs, this R&D and NVM product will be a timely solution. Other military applications may include strategic missiles (Trident and Air Force upgrades), as well as many DoD tactical weapon programs with nuclear survival levels.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Guidance, Navigation, and Control
Highly-Reconfigurable
Photonics
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 S3.02-8213
PHASE-1 CONTRACT NUMBER: NNX10CF21P
SUBTOPIC TITLE: Thermal Control Systems
PROPOSAL TITLE: Loop Heat Pipe with Thermal Control Valve for Passive Variable Thermal Link

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Cooling Technologies, Inc.
1046 New Holland Avenue
Lancaster, PA 17601-5688
(717) 295-6061

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Hartenstine
john.hartenstine@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5688
(717) 295-6061

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future Lunar Landers and Rovers will require variable thermal links that can reject heat during daytime, and passively shut-off during lunar night. During the long lunar day, the thermal management system must remove the waste heat from the electronics and batteries keep them within the acceptable temperature limit. Since the heater power availability is restricted, a variable thermal link is therefore required to limit the amount of heat that is removed from the electronics and radiated to space during the long lunar night. Conventional Loop Heat Pipes (LHPs) can provide the required variable thermal conductance, but they consume electrical power to shut down the heat transfer. Our innovation adds a Thermal Control Valve (TCV) to the LHP, allowing it to passively shut off without consuming any electrical power. This is important since there is a severe penalty for electrical power consumption: supplying 1 W in a photovoltaic system requires roughly 5 kg of extra equipment. The TCV used in the LHP has been previously selected for thermal control in the pumped loop on the Mars Science Laboratory. The Phase I project was successful in demonstrating the feasibility of integrating the TCV in a LHP. The Phase II project will fabricate and test a LHP with a TCV at representative conditions, bringing the technology to TRL 6. The testing will include full characterization of the TCV under various LHP operation modes. Analysis and testing of different LHP condenser layouts will also be performed, as well as freeze/thaw analysis.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
One application for the TCV controlled LHP is thermal management for Lunar Landers and Rovers. An example is the Warm Electronics Box (WEB) and batteries for the NASA Anchor Node Mission for the International Lunar Network (ILN). The ILN could be powered by either solar or a radioisotope power system. The WEB and batteries face the same thermal challenges that require a variable thermal link to allow heat removal during daytime and heat preservation during nighttime. The integration of a TCV eliminates the electrical power consumption required to shut down a conventional LHP. Every 1 W of electricity saved translates to a mass saving of roughly 5kg for a solar powered system. Current Mars rover designs use a mechanically pumped single-phase fluid loop for thermal management. The proposed TCV controlled LHP could replace the mechanically pumped loop system with a complete passive system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
TCV controlled LHPs can also be used in commercial and military satellites where the radiator sink conditions change, and there is a need to maintain the electronics within a narrow temperature band. The variable thermal link passively maintains the electronics temperature during cold sink conditions, such as during an eclipse. ACT produces LHPs for these satellites, and plans to use the technology developed in this program in its commercial product line. A second application is cooling of commercial and military aircraft components, specifically for UAVs. While operating at high altitudes during daytime, the LHP can reject the thermal load to the aircraft skin or forced convection sink. At cold night, the LHP passively shuts down, limiting the heat loss and maintaining the electronics temperature.

TECHNOLOGY TAXONOMY MAPPING
Cooling


PROPOSAL NUMBER: 09-2 S3.02-9436
PHASE-1 CONTRACT NUMBER: NNX10CD76P
SUBTOPIC TITLE: Thermal Control Systems
PROPOSAL TITLE: Software for Automated Generation of Reduced Thermal Models for Spacecraft Thermal Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corp.
215 Wynn Drive, 5th Floor
Huntsville, AL 35805-1944
(256) 726-4858

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yi Wang
sxh@cfdrc.com
215 Wynn Dr.
Huntsville,  AL 35805-1944
(256) 327-0678

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Thermal analysis is increasingly used in the engineering of spacecrafts at every stage, including design, test, and ground-operation simulation. Currently used high-fidelity modeling and simulation tools at NASA are computationally prohibitive and not fully compatible with integrated analysis of spacecrafts. We propose to develop and demonstrate an innovative Model Order Reduction (MOR) software to automatically generate nonlinear reduced thermal models for spacecraft analysis. The underlying principle of our approach is to project the original full models onto a characteristic, low-dimensional subspace, yielding reduced models with markedly low computational orders. During Phase 1, key technology elements were developed and proof-of-concept was successfully demonstrated. A MOR engine encapsulating carefully selected nonlinear MOR algorithms, a reduced model solver and a verification module along with facile data exchange interfaces, were developed in an integrated software environment. By way of whole-satellite (LISA) case studies, critical evidence was established that reduced thermal models enable unprecedented speedup (10?500X) and accuracy (<0.3%) for spacecraft analysis and design. In Phase 2, MOR engines will be optimized for enhanced computational performance. Robust constituent linear algorithms and domain-wise projection spaces will be developed to improve simulation stability and accuracy. New MOR capabilities to address variable-dependent models and parameterized MOR to accommodate design perturbations will be investigated. Our MOR software will be extensively verified and demonstrated for complex spacecraft thermal analysis. An application programming interface (API) will be developed in close collaboration with leading NASA vendors (C&R Technologies) to facilitate technology insertion and transition.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed Model Order Reduction software will deliver NASA engineers a valuable tool to (1) perform rapid and computationally affordable thermal analysis for better understanding of design spaces, (2) develop advanced, reliable thermal control strategies for spacecrafts and instruments, and (3) properly arrange test procedures for rational use of instruments and facilities. The success in the proposed research will markedly shrink the development cycles of spacecrafts at reduced cost.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Among the non-NASA applications, the developed software will find use in various engineering sectors, including semiconductor industry, combustion, power and aerodynamics industry, chemical plants, biomedical companies, micro-electro-mechanical systems (MEMS) and microfluidics manufacturers among others. The product would directly contribute to these vital areas by providing a powerful tool to generate fast reduced order models, which can be extensively used to (1) analyze the industrial processes for fault diagnostics and optimized design, leading to reduced turnaround time to market; and (2) develop advanced controller strategies for on-line process monitoring and control.

TECHNOLOGY TAXONOMY MAPPING
Control Instrumentation
Operations Concepts and Requirements
Simulation Modeling Environment
Cooling
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 S3.03-8061
PHASE-1 CONTRACT NUMBER: NNX10CC98P
SUBTOPIC TITLE: Power Generation and Conversion
PROPOSAL TITLE: Thermal Management System for Long-Lived Venus Landers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Cooling Technologies, Inc.
1046 New Holland Avenue
Lancaster, PA 17601-5688
(717) 295-6061

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Calin Tarau
calin.tarau@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5688
(717) 295-6061

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall program objective is to develop a high-temperature passive thermal management system for the Radioisotope Power Conversion system that energizes the refrigeration system applicable to Venus missions. The innovation consists of a high temperature alkali metal variable conductance heat pipe (VCHP) integrated with a two-phase heat collection / transport package from the General Purpose Heat Source (GPHS) stack to the Stirling convertor heater head. The thermal management system collects the heat from the GPHS modules, and delivers heat as required to the Stirling system. Any excess heat is removed by the VCHP. Excess heat must be removed when the Stirling system is shut down, or in the early stages of a mission powered by a short-life radioisotope. In Phase I, it was demonstrated experimentally and theoretically that the VCHP allows the Stirling convertor to: stop during transit to Venus, pre-cool the system before re-entry, work on Venus and execute brief stoppages on Venus. The reservoir is exposed to the environment temperature during the mission and this is a key for the HTTMS to work passively. The other component of the system, the two-phase heat transport package (HTP), minimizes the temperature drop between the multi-GPHS stack and the heater head. In Phase II, a full scale HTTMS will be designed and a representative multi-segment of the full scale HTTMS will be build and tested in relevant environment. This multi-segment contains two or three parallel/redundant heat paths from the simulated GPHS stack to the heater head simulator, in addition to the backup cooling system (VCHP). The full-scale multi-segment HTTMS will be integrated and tested with the corresponding full scale multi-segment of the Intermediate Temperature Thermal Management System (ITTMS) of the Venus Lander.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate application for this proposal is thermal management for a long-lived Venus lander that is cooled with a Stirling system integrated with a large number of GPHS modules. The thermal management system will efficiently collect the heat from the GPHS modules and deliver it to the Stirling engine. In addition, the thermal management system will allow the Stirling convertors and cooling to be shut off during the transit to Venus, saving heater head life. More generally, the systems developed on this program are applicable to all NASA missions with high powered radioisotope systems that require a large number of GPHS modules. In particular, the system will allow the use of alternative isotopes with a shorter half-life than Pu-238. The excess heat is passively rejected. In addition, the heat collection system is useful for smaller systems that use the less efficient Am-241 based GPHS modules, because they require a larger number of modules than the systems with the standard GPHS modules. Backup cooling is also an important feature that is needed in almost all missions (and ground testing) that use GPHS modules. Beside the Venus mission applications, Beside the Venus mission applications, the developed system is applicable to deep space missions powered by alternate radioisotopes, as well as missions to other high temperature locations in the Solar System.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
One potential commercial application based on a current product line at ACT is pressure-controlled isothermal furnace liners. An isothermal furnace liner is an annular alkali metal heat pipe. Replacing the current heat pipe with a pressure controlled VCHP will allow much tighter temperature control. A second commercial application is alkali metal VCHPs in fuel cell reformers. In a fuel cell reformer, diesel fuel and air pass through a series of high temperature reactors to generate hydrogen. The operating temperature of the reactors must be closely controlled to maintain their chemical equilibrium. A typical system must maintain inlet and outlet temperatures within 30<SUP>o</SUP>C despite a turndown ratio of 5:1 in reactant flow rate. The current scheme uses a bypass valve, which has several drawbacks: it requires active control, requires power, and has a large pressure drop. ACT believes that alkali metal VCHP heat exchangers can replace the current heat exchanger and control system with a passive system that automatically maintains the output stream from the heat exchanger at a constant temperature.

TECHNOLOGY TAXONOMY MAPPING
Cooling


PROPOSAL NUMBER: 09-2 S3.03-8143
PHASE-1 CONTRACT NUMBER: NNX10CD01P
SUBTOPIC TITLE: Power Generation and Conversion
PROPOSAL TITLE: High Radiation Resistance Inverted Metamorphic Solar Cell

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MicroLink Devices
6457 Howard Street
Niles, IL 60714-3301
(847) 588-3001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Noren Pan
npan@mldevices.com
6457 West Howard St
Niles,  IL 60714-3301
(847) 588-3001

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation in this SBIR Phase II project is the development of a unique triple junction inverted metamorphic technology (IMM), which will enable the manufacturing of very lightweight, low-cost, InGaAsP-based multijunction solar cells. The proposed IMM technology is based on ELO (epitaxial lift-off) and consists of Indium (In) and Phosphorous (P) solar cell active materials, which are designed to improve the radiation resistance properties of the triple junction solar cell while maintaining a high efficiency. Because of the intrinsic radiation hardness of InP materials, this material system is of great interest for building solar cells suitable for deployment in very demanding radiation environments, such as medium earth orbit and missions to the outer planets. Due to high launch costs, weight reduction is a key driver for the development of new space solar cell technologies. Our recently developed epitaxial lift-off (ELO) process will also be applied to this new structure, which will enable the fabrication of the IMM structure without the substrate. Cells with excellent end-of-life (EOL) performance require less area to meet specific mission power requirements. The target efficiency of the proposed IMM cell at the beginning of life (BOL) is greater than 30% at AMO 1-sun. The EOL target of the IMM cell is a degradation of less than 10% in efficiency.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Radiation resistant solar cells are attractive for usage in high radiation environments such as medium earth orbit and missions to outer planets. Due to high launch costs, weight reduction is key driver for the development of new space solar cell technologies. Improved intrinsic cell radiation resistance may enable substantial weight reduction through the reduction or elimination of the heavy cover glass materials as required on conventional GaAs-based cells. High efficiency and high EOL performance is of great interest for satellite power systems since less area would be required to obtain the desired electrical power.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The IMM cells developed for this program could be modified for use in concentrator photovoltaic (CPV) systems to provide terrestrial solar power. Using an InGaP/InGaAsP/InGaAs design rather than the conventional InGaP/GaAs/InGaAs design is expected to increase the efficiency of the resulting cell because the use of the quaternary InGaAsP subcell rather than the GaAs subcell allows the use of a set of bandgaps that better match the solar spectrum. The technology described in this work is a green technology in that the GaAs substrate on which the solar cell is grown is reused multiple times via the ELO process and is ultimately recycled.

TECHNOLOGY TAXONOMY MAPPING
Semi-Conductors/Solid State Device Materials
Photovoltaic Conversion


PROPOSAL NUMBER: 09-2 S3.03-8863
PHASE-1 CONTRACT NUMBER: NNX10CD03P
SUBTOPIC TITLE: Power Generation and Conversion
PROPOSAL TITLE: Lightweight IMM Multi-Junction Photovoltaic Flexible Blanket Assembly

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Deployable Space Systems
75 Robin Hill, Building B2
Goleta, CA 93117-3108
(805) 693-1319

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Spence
Brian.Spence@DeployableSpaceSystems.com
75 Robin Hill, Building B2
Goleta,  CA 93117-3108
(805) 805-1313

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
DSS's recently completed successful NASA SBIR Phase 1 program has established a TRL 3/4 classification for an innovative IMM PV Integrated Modular Blanket Assembly (IMBA) that can be rolled or z-folded and enables NASA's emerging high voltage solar electric propulsion (SEP) missions. Significant concept feasibility, design/analysis, trade study/evaluation, and proof-of-concept hardware build/test efforts executed during the NASA SBIR Phase 1 program have validated DSS's IMM PV IMBA technology as a potentially revolutionary flexible photovoltaic blanket assembly that provides high performance in terms of; high voltage operability, high specific power / lightweight (>1000 W/kg BOL at the blanket subsystem level, and >500 W/kg BOL at the array level), compact stowage volume (>50 kW/m3 BOL), rollable or z-foldable for stowage, reliability, modularity & rapid production, flexibility/durability and robustness, affordability, and adaptability to all existing industry flexible blanket solar array products. DSS's IMBA technology also accommodates standard ZTJ PV device technologies to provide significantly improved performance over current state-of-the-art.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed IMM PV integrated flexible blanket assembly technology is applicable to all future NASA Space Science, Earth Science, and Exploration Initiative missions as a direct replacement to current-state-of-the-art. The proposed technology is a mission-enabling solution for near-to-medium term NASA Discovery, Flagship Outer-Planets and New Frontiers-class science missions, and/or other NASA missions requiring high specific power, exceptional stowed packaging efficiency, and high voltage operation capability, especially as applied to interplanetary, comet rendezvous and Solar Electric Propulsion (SEP) science missions. The innovative technology also provides a near-term and low-risk solar array panel subsystem that can significantly benefit all other NASA LEO, GEO, planetary or celestial-body Lander, planetary orbiter, and/or Deep Space applications, through weight, compact stowed volume and cost savings.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed IMM PV integrated flexible blanket assembly technology is also applicable to all non-NASA space missions (including DoD, civilian, & commercial missions), and is a direct replacement to current-state-of-the-art. The proposed technology is mission-enabling for high voltage, high specific power, and constrained-volume launch vehicle packaging applications. Applicable non-NASA space missions include: LEO surveillance, reconnaissance, communications and other critical payload/equipment satellites, LEO commercial mapping and critical payload/equipment satellites, GEO commercial communications and critical payload/equipment satellites, and GEO DoD communications and payload/equipment satellites. Non-space / commercial private sector applications include many potential power / energy production terrestrial applications for fixed ground, mobile, and roof-top mounted consumer applications, and high altitude airship applications were very-high specific power, high efficiency, and low-cost is required.

TECHNOLOGY TAXONOMY MAPPING
Highly-Reconfigurable
Composites
Semi-Conductors/Solid State Device Materials
Photovoltaic Conversion
Renewable Energy


PROPOSAL NUMBER: 09-2 S3.03-9404
PHASE-1 CONTRACT NUMBER: NNX10CD04P
SUBTOPIC TITLE: Power Generation and Conversion
PROPOSAL TITLE: Mass-Optimized Ultra Flex Solar Array with Integrated IMM Cell Flexible Blanket

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Deployable Space Systems
75 Robin Hill, Building B2
Goleta, CA 93117-3108
(805) 693-1319

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steve White
Steve.White@DeployableSpaceSystems.com
75 Robin Hill, Building B2
Goleta,  CA 93117-3108
(805) 805-1313

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Deployable Space Systems (DSS), in partnership with ATK Space and EMCORE, is focusing on the design development and optimization of the most promising advanced space photovoltaic subsystem now available: EMCORE's ultra-thin 33% BOL-efficient Inverted Metamorphic Multijunction (IMM) solar cell that is interconnected into module form and integrated onto an advanced flexible blanket (gore); specifically for implementation on the lightest solar array structural system currently in use, ATK's UltraFlex. The innovative and synergistic solutions conceptually developed during the Phase 1 effort produced a near-term, low-risk solar array system that provides breakthrough performance in terms of highest specific power (>380 W/kg BOL), light weight, scalability to large (>15 kW) wing sizes, high deployed stiffness, high deployed strength, compact stowage volume (>40 kW/m3 BOL), high voltage operation capability, reliability, affordability, and rapid commercial readiness. The Phase 2 study will successfully further increase the design fidelity (TRL) of the most promising IMM-integrated onto UltraFlex-specific triangular gore blanket solutions configured to meet key high-voltage SEP / deep space science mission requirements. The development, as performed on the cost-effective Phase 2 SBIR plan structured in detail, will allow for an expedient and low-risk commercial infusion of the ultra-lightweight integrated IMM PV UltraFlex solar array technology via continued hardware-based and test-validated development, and enables future missions, including near-to-medium term NASA Outer Planets and Solar Electric Propulsion (SEP) science missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A mass-optimized UltraFlex solar array with integrated IMM cell flexible blanket is applicable to all future NASA Space Science, Earth Science, and Exploration Initiative missions as a direct replacement to current-state-of-the-art. The IMM-optimized UltraFlex is the mission-enabling solar array system solution for near-to-medium term NASA Discovery, Flagship Outer Planets and New Frontiers-class science mission planners requiring high power (scalability), stowed packaging efficiency, high voltage design capability and highest specific power. The design will benefit interplanetary, comet rendezvous and Solar Electric Propulsion (SEP) science missions, and all other NASA LEO, GEO, planetary or celestial-body Lander, planetary orbiter, and/or Deep Space applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A mass-optimized UltraFlex solar array with integrated IMM cell flexible blanket is widely applicable to all future non-NASA GEO and LEO space missions (including DoD and commercial missions), and is a direct replacement to current-state-of-the-art. IMM-on-UltraFlex technologies are mission-enabling for high voltage, high power and constrained-volume launch vehicle packaging applications. Additionally, because of its inherent light weight and deployed stiffness/strength capability, the IMM UltraFlex is ideal for rapid-maneuvering surveillance satellite applications (can more weight-efficiently take high-G accelerations). Additionally, the next-generation of GEO spacecraft could be optimally designed to take advantage of IMM UltraFlex's high stiffness/strength to allow the arrays to remain deployed during transfer orbit burns (generating full power) and greatly reducing spacecraft ACS requirements (>10X deployed stiffness). Applicable non-NASA space missions include: LEO surveillance, reconnaissance, GEO commercial communications and critical payload/equipment satellites, and GEO DoD communications and payload/equipment satellites.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Photovoltaic Conversion


PROPOSAL NUMBER: 09-2 S3.04-8077
PHASE-1 CONTRACT NUMBER: NNX10CD05P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Low-Cost High-Performance Hall Thruster Support System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Colorado Power Electronics, Inc.
120 Commerce Drive, Unit 3
Fort Collins, CO 80524-4731
(970) 482-0191

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryce Hesterman
bryce.hesterman@c-pwr.com
120 Commerce Drive, Unit 3
Fort Collins,  CO 80524-4731
(970) 482-0191

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Colorado Power Electronics (CPE) has built an innovative modular power processing unit (PPU) for Hall Thrusters, including discharge, magnet, heater and keeper supplies, and an interface module. The innovations of this high-performance PPU are its resonant circuit topologies, magnetics design, modularity, and its stable and sustained operation during severe Hall effect thruster current oscillations. Laboratory testing at NASA Glenn Research Center (GRC) has demonstrated discharge module efficiency of 96% with is considerably higher than current state of the art. The purpose of the Phase II project is to develop an Engineering Model HiVHAc PPU that includes a digital control interface unit (DCIU) to TRL 6. This will position CPE to manufacture a qualification model PPU as a Phase III project. The prototype digitally-controlled flow controller with a PC interface developed in Phase I will serve as the foundation for a combination DCIU-Flow module to be added to the PPU in Phase II. Thermal and vibration Finite element analysis (FEA) will be performed on the reduced-mass chassis designed in Phase I, and then a test brassboard PPU will be built and tested. Additionally, the control loops of the PPU will be analyzed and a stress analysis will be performed. The test PPU will be a deliverable to NASA GRC. The results of the analysis and testing will be used to design and build an engineering model flight-like PPU that includes flight-like wire harnessing schemes, EMI filtering, enhanced modularity and the new DCIU-Flow module. At the beginning of the project, the TRL of the PPU is between 4 and 5, the TRL of the DCIU is 2, and the TRL of the valve driver is 3. At the conclusion of the Phase II effort the PPU/DCIU will be at TRL 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The purpose of the Phase II project is to further develop and refine the existing CPE PPU so that CPE will be in a position to build a qualification model as a Phase III project to be used with a Hall thruster currently under development at NASA Glenn Research Center. We were asked by NASA JPL to submit an ROM estimate for designing and building a PPU for an Ion Thruster that uses circuits similar to those utilized in this project.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Dynamic Structures & Materials, LLC has expressed an interest in having CPE develop a space-rated piezo driver based on the Phase I project. We recently developed a resonant converter for Lockheed Martin Space Systems that uses circuits similar to those utilized in this project. We currently manufacture commercial power supplies with multiple 10kW modules, and so we plan to explore opportunities for using CPE resonant converters for high-power Hall thrusters in the 10-100 kW range. We plan to investigate military applications where the extra maneuverability made possible with a PPU that can operate a Hall thruster a wide range of voltages would be advantageous. We have a joint development agreement in place with Aerojet, and will be looking for opportunities to commercialize the technology covered in US patent 7,631,482.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Radiation-Hard/Resistant Electronics
Power Management and Distribution


PROPOSAL NUMBER: 09-2 S3.04-8131
PHASE-1 CONTRACT NUMBER: NNX10CD06P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Low Mass Low Power Hall Thruster System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Busek Co., Inc.
11 Tech Circle
Natick, MA 01760-1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bruce Pote
bpote@busek.com
11 Tech Circle
Natick,  MA 01760-1023
(508) 655-5565

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In NASA is seeking an electric propulsion system capable of producing 20mN thrust with input power up to 1000W and specific impulse ranging from 1600-3500 seconds. The key technical challenge of the topic is the target mass of 1kg for the thruster and 2kg for the power processor (PPU). In Phase 1 Busek develop an overall subsystem design for the thruster/cathode, PPU and XFS. The feasibility of a low mass power processing architecture that replaces four of the DC-DC converters of a typical PPU with a single multi-functional converter and a low mass Hall thruster design employing permanent magnets was demonstrated. In Phase 2 effort will develop an engineering prototype model of the low mass BHT-600 Hall thruster system with the primary focus on the low mass PPU and thruster. The broad technical objectives are: 1) Design, fabricate and demonstrate an engineering model version of the low mass, Hall thruster PPU developed in Phase 1. The target mass is 2kg. 2) Design, fabricate and demonstrate a low mass version of the BHT-600 thruster The target mass and efficiency is 1 kg and >45%, respectively. 3) Conduct an integrated system test and deliver the prototype PPP and thruster system to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Hall thrusters have been identified as a key technology for NASA's vision of space exploration. NASA missions beyond Earth orbit can be enabled by the wide throttle range and broad Isp-thrust operation of electric thrusters. A study conducted by the SMD ISPT Project in 2004 confirmed the significant potential of REP for space science, especially with recent advancements in enabling, high ?specific-power RPS technology (from 3 to over 8 We/kg). The study also concluded that REP would be ready for near-term NASA science missions if an electric propulsion thruster with the appropriate specific impulse and propellant throughput capability could be developed. Evaluations and assessments performed over the last decade have confirmed the benefits of REP for a variety of potential missions, including orbiters about Pluto, Neptune, and Uranus; rendezvous and Centaurs, Kuiper Belt Objects and primitive bodies in the outer Solar System; and extensive surveys of major asteroid groups. In general, REP offers the benefits of nuclear electric propulsion without the need for an excessively large spacecraft and power system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The use of low power electric propulsion systems have been pioneered by the AFRL and STP. The AFRL IHPRPT Program is also investing in the development of long life low power HET systems. A key technology identified in the Beyond IHPRPT study is an extremely long life and low mass variant of the BHT-200 and 600 HET systems. The multi-functional converter concept is attractive for its reduction in overall propulsion system mass complexity and cost. Commercial satellite manufacturers; SS/L, Boeing, Lockheed Martin and Orbital Sciences have all shown a strong interest in low power HET systems for primary propulsion on LEO spacecraft and station keeping on GEOSats.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Electrostatic Thrusters
Feed System Components
Power Management and Distribution


PROPOSAL NUMBER: 09-2 S3.04-8809
PHASE-1 CONTRACT NUMBER: NNX10CD07P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: High Efficiency Hall Thruster Discharge Power Converter

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Busek Co., Inc.
11 Tech Circle
Natick, MA 01760-1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Jaquish
busek@busek.com
11 Tech Circle
Natick,  MA 01760-1023
(508) 655-5565

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Busek leveraged previous, internally sponsored, high power, Hall thruster discharge converter development which allowed it to design, build, and test new printed circuit board converter within this Phase 1 effort. The new converter consists of two series or parallel boards (slices) intended to power NASA GRC HiVHAC thruster or other similarly sized EP devices. The converter accepts 80 to 160V input and generates 200 to 700V isolated output while delivering continually adjustable 300W to 3.5kW power. Busek built and demonstrated one board which achieved <94% efficiency the first time it was turned on, with projected efficiency exceeding 97% following timing software optimization. The board has a projected specific mass of 1.2kg/kW achieved thru high frequency switching. In Phase 2 we will perform the required optimization to exceed 97% efficiency and build a second prototype in a form factor more appropriate for flight. This converter will then be integrated with a set of upgraded existing boards for powering magnets and the cathode which constitute the balance of the PPU and use the traditional input voltage of 28V. The program will culminate with integrating the entire PPU and testing it on Busek thruster at Busek and on HiVHAC thruster at NASA GRC.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Hall thrusters have been identified as a key technology for NASA's vision of space exploration. NASA missions beyond Earth orbit can be enabled by the wide throttle range and broad Isp-thrust operation of Hall thrusters. In 2004 the In-Space Propulsion Technology Program conducted a study to quantify the potential benefit of using the HiVHAC Hall thruster propulsion system. This study considered New Frontier-Class science missions, that are currently cost capped at around $800 M, and Discovery-Class science missions that are currently cost capped at around $450 M. Studies were performed for three NASA Discovery-Class missions; Vesta-Ceres rendezvous mission (Dawn Mission), Koppf comet rendezvous, and Nereus sample return mission. Results from the mission studies indicated that the HiVHAC thruster was able to close all the missions. The study also concluded that a Hall thruster system with HiVHAC performance capabilities and the ability to provide total impulses approaching that of ion thruster systems provided substantial cost and performance benefits.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High power electric propulsion systems have been identified as a key technology for transportation of DoD space assets. The AFRL IHPRPT Program is investing in the development of a dual-mode HET system. The proposed configurable/modular discharge converter is a close derivative of the discharge converter requirements for AFRL. The DARPA FAST Program is considering high power HETs as part of their in-space technology demonstration of an all electric very high power space tug and GEO servicing vehicle. Hall thruster systems in the 5-20 kW range are envisioned to assume both the orbit transfer and station keeping requirements for GEO communication satellites. The wide output voltage capability of the proposed discharge power supply is an essential feature for the dual mode requirement of high thrust for orbit raising and high Isp for station keeping. Commercial satellite manufacturers; SS/L, Boeing, Lockheed Martin and Orbital Sciences have all shown a strong interest in throttleable HET systems for their GEOSats.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Electrostatic Thrusters
Power Management and Distribution


PROPOSAL NUMBER: 09-2 S3.04-8940
PHASE-1 CONTRACT NUMBER: NNX10CD08P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Silicon Carbide (SiC) Power Processing Unit (PPU) for Hall Effect Thrusters

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Arkansas Power Electronics International, Inc.
535 W. Research Center Blvd., Suite 209
Fayetteville, AR 72701-7175
(479) 443-5759

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bradley Reese
breese@apei.net
535 W. Research Center Blvd.
Fayetteville,  AR 72701-7175
(479) 443-5759

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this SBIR project, APEI, Inc. is proposing to develop a high efficiency, rad-hard 3.8 kW silicon carbide (SiC) power supply for the Power Processing Unit (PPU) of Hall Effect thrusters. This program specifically targets the design of a PPU for the HiVHAC (High Voltage Hall ACcelerator) thruster, with target specifications of 80-160V input, 200-700V / 5A output, efficiency greater than 96%, and peak power density in excess of 2.5 kW/kg. The PPU under development utilizes SiC JFET power switches; components which APEI, Inc. has irradiated under TID conditions to greater than 3 MRad with little to zero change in device performance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are a wide range of applications within NASA on which SiC ultra-lightweight power converters could make a significant impact, including: Satellite & spacecraft power management systems? SiC converter technology that is more efficient than silicon and offers reduced weight and volume would find application in nearly every power management system in space. Satellite & spacecraft motors and actuators? Most spacecraft contain a multitude of actuators and motors to perform various functions, such as opening and rotating solar array panels, controlling robotic arms, aligning communications arrays, pointing cameras and instruments, etc. Extreme environment exploratory vehicles? While one advantage of SiC technology is to achieve higher power densities through high temperature operation, the other utilization of the technology is to operate in high temperature environments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
APEI, Inc. has identified two key applications where the proposed technology is also applicable namely, high voltage hybrid electric vehicle (HEV) battery packs, and photovoltaic energy systems. These two applications open up a path to non-military commercialization of the technology which can mean huge dividends for APEI, Inc. Other applications include Energy Exploration, Industrial Motor Drives, Electric Vehicle Motor Drives, and Military Systems.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Ultra-High Density/Low Power
Electrostatic Thrusters
Radiation-Hard/Resistant Electronics
Power Management and Distribution


PROPOSAL NUMBER: 09-2 S3.04-9095
PHASE-1 CONTRACT NUMBER: NNX10CE12P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Low Mass Electromagnetic Plasmoid Thruster with Integrated PPU

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MSNW, LLC
8551 154th Avenue NE
Redmond, WA 98052-5858
(425) 867-8900

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Kirtley
dkirtley@msnwllc.com
8551 154th Avenue NE
Redmond,  WA 98052-5858
(425) 425-8900

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Electromagnetic Plasmoid Thruster (EMPT) is a revolutionary electric propulsion thruster and power processing (PPU) system that will allow a dramatic decrease in system mass and increase in thrust efficiency over traditional 500-3000 W propulsion systems. The high specific power (>700 W/kg) and high efficiency of EMPT will enable a wide range of deep space missions such as Neptune, Pluto and Oort Cloud orbital insertion. Additionally, a solar electric EMPT system would dramatically increase the capability and reduce the travel time of an asteroid or Martian moon sample and return mission due to the variable-power, low-mass propulsion system. The EMPT employs a Rotating Magnetic Field (RMF) to produce large plasma currents inside a conical thruster creating a plasmoid that is magnetically isolated from the thruster walls. The intensified gradient magnetic field from the plasmoid together with the large plasma currents result in an enormous body force that expels the plasmoid at high velocity. The EMPT is a pulsed device, nominally operating at 1 kWe with 0.5-1 Joule discharges at 1-2 kHz. Presented is a full description of the relevant plasma physics as well as the thruster and PPU design. The Phase I EMPT demonstrated the multi-pulse formation and ejection of plasmoids at 0.1-3 Joules and 500-6,000 s Isp on both Xenon and Argon. Additionally, it demonstrated zero erosion or life limiting phenomena. The focus of the proposal is the experimental validation of an integrated thruster and PPU operating in a steady-state mode. The EMPT will be characterized over a range of parameters: input power from 200-3000 Watts, and 1,500-4,000 seconds specific impulse. The integrated thruster and PPU to be built and tested will have a total system mass of less than 1.5 kg. Successful completion of Phase II will be a fully integrated, steady-state demonstration of thruster and integrated power processing. Phase II will mature the technology from a TRL level 4 to 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has a highly varied interest in advanced propulsion systems at the 1 kW level. The high specific impulse operation of the EMPT will have applications for large earth observing science missions as a replacement for high-mass (<100 W/kg) station keeping thrusters when coupled with ultra-light solar arrays. Additionally, as more (and less massive) power is available for interplanetary science missions, such as advanced radioisotope power (REP) systems and NASA ultra-flex solar panels (SEP), electric propulsion can find even larger roles. A low mass, 1 kW REP propulsion system would enable a host of deep space Neptune, Pluto, and Oort Cloud orbiter missions. An advanced SEP system would enable small sample and return and orbiter missions from asteroids and planetary moons. Additionally, the variable power and thruster nature of the EMPT can apply immediate mass savings on any interplanetary mission with variable power requirements.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The DOD is primarily interested in propulsion systems as either station keeping for large satellites or primary propulsion for smaller satellites. The EMPT has application for small satellite main propulsion and LEO-GEO transfer in earth orbit due to its high specific power (>600 W/kg) and expected high Thrust-to-Power. Additionally, the high specific impulse operation of the EMPT will have applications for large telecom and military satellite station-keeping. Finally, the variable power and thrust nature of the EMPT has direct application to modern Operational Responsive Space (ORS) missions that require a single propulsion unit capable of in-orbit mission changes.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Fundamental Propulsion Physics
Micro Thrusters
Ultra-High Density/Low Power


PROPOSAL NUMBER: 09-2 S3.04-9659
PHASE-1 CONTRACT NUMBER: NNX10CD09P
SUBTOPIC TITLE: Propulsion Systems
PROPOSAL TITLE: Unibody Composite Pressurized Structure (UCPS) for In-Space Propulsion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microcosm, Inc.
4940 W. 147th Street
Hawthorne, CA 90250-6708
(310) 219-2700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Markus Rufer
mrufer@smad.com
4940 w. 147th Street
Hawthorne,  CA 90250-6708
(310) 219-2700

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Microcosm, in conjunction with the Scoprius Space Launch Company (SSLC), will develop a Unibody Composite Pressurized Structure (UCPS) for in-space propulsion that constitutes a clean break from traditional spacecraft design by combining what were traditionally separate spacecraft primary and secondary support structures and metal propellant tanks into a single unibody, all-composite construction that is stronger, much lighter weight, more robust and reliable, and capable of supporting much higher pressures and smaller volume than previous approaches. The single, all-composite structure will include linerless, high-pressure propellant tank(s), composite bosses, flanges, longitudinal and circumferential stringers with integral shelves, holding mechanisms, and attach features to support all of the spacecraft equipment and replace the separate, mission-critical primary support structure, tanks, struts, straps, braces, clamps, and brackets traditionally required to hold subsystem parts in place. The new structure has nearly 0 CTE over a temperature range from cryogenic to over 100 C. Phase I will determine requirements, create a preliminary UCPS design relevant to a potential SMD mission, and test material compatibility with various in-space propellants. Phase II will build two UCPS structures employing test masses for spacecraft components, and complete qualification and burst testing on one of them (including 0-g testing).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed UCPS would be applicable for numerous NASA spacecraft applications, to reduce the mass and cost of SMD spacecraft, in particular. These tanks could compose the primary structural element in a spacecraft bus, at the same time serving their primary purpose of propellant storage. The tanks allow much higher pressure chemical propulsion systems, in excess of 2,000 psi, for less tank mass than traditional systems operating at much lower pressures, providing a lighter weight and lower volume solution. These tanks will be applicable for both high pressure liquid and gaseous propellants for chemical and electric propulsion systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The UCPS can be implemented in other government spacecraft as well as any commercial spacecraft employing propulsion systems, offering the unique combination of high pressure, low volume, lightweight tanks, and primary spacecraft structural support. Further potential applications include other launch vehicles, and additional space systems that desire weight and cost reduction. These tanks can also serve in other industries. Automotive, electrical, and medical industries require similar characteristics to those that Microcosm will be demonstrating in the Phase II program. Microcosm has been aggressively working non-aerospace applications of this composite tank technology. Microcosm and SSLC have begun to enter the commercial market for smaller sized cryogenic and non-cryogenic tanks. This commercial venture will act as the base to launch operations into larger tanks. A prototype version of a tank with integrated stringers and other structural attach points has been produced with a 10" diameter core tank and one that has propellant expulsion device, a bladder, will be built and tested in Phase II. Following testing with hydrazine, this system will be offered for use on commercial spacecraft.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Monopropellants
Propellant Storage
Tankage
Feed System Components
Fluid Storage and Handling
Composites


PROPOSAL NUMBER: 09-2 S3.05-8550
PHASE-1 CONTRACT NUMBER: NNX10CD11P
SUBTOPIC TITLE: Power Management and Storage
PROPOSAL TITLE: High-Temperature, Wirebondless, Ultra-Compact Wide Bandgap Power Semiconductor Modules for Space Power Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
APECOR
3259 Progress Drive, Suite A
Orlando, FL 32826-2930
(407) 275-1174

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Elmes
jelmes@apecor.com
3259 Progress Drive, Suite A
Orlando,  FL 32826-2930
(407) 275-1174

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Silicon carbide (SiC) and other wide band-gap semiconductors offer great promise of high power rating, high operating temperature, simple thermal management, and ultra-high power density for both space and commercial power electronic systems. However, this great potential is seriously limited by the lack of reliable high temperature device packaging technology. The objective of this proposed research is to develop a ultra-compact, hybrid power module packaging technology based on the use of double leadframes and direct leadframe-to-chip transient liquid phase (TLP) bonding that allows device operation up to 450 degrees Celsius. The unique advantages of this innovative solution include very high current carrying capability, low package parasitic impedance, low thermo-mechanical stress at high temperatures, double-side cooling, and modularity for easy system-level integration. The new power module will have a very small form factor with 3-5X reduction in size and weight from the prior art, and capable of operating from 450C to -125C.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Wide operating temperature power semiconductors for space power systems and science missions such as Earth Orbiting, Venus, Europa, Titan and Lunar Quest.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed concept will have a profound impact on power electronics and energy conversion technologies and help to conserve energy and environment, as well as to reduce the nation's dependence on fossil fuels. Widespread use of efficient and cost-effective power electronics technology can potentially result in a 35% reduction in energy consumption. Power electronics, along with computer and microprocessor technology, impacts nearly every sector of the U.S. economy including automobiles, electric utility, pollution control, communications, computer systems, consumer electronics, and factory automation. For commercial applications, the proposed new packaging technology can be used in its current form or scaled down to medium or conventional temperature range with a significantly reduced cost, making it a viable and economical option for large commercial markets such as hybrid electric vehicles, renewable energy conversion, and power supplies.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid State Device Materials
Power Management and Distribution


PROPOSAL NUMBER: 09-2 S3.08-8144
PHASE-1 CONTRACT NUMBER: NNX10CF22P
SUBTOPIC TITLE: Planetary Ascent Vehicles
PROPOSAL TITLE: Refractory Coated/Lined Low Density Structures

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Materials Research and Design
300 E. Swedesford Road
Wayne, PA 19087-1858
(610) 964-9000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joseph Pluscauskis
pluscauskis@m-r-d.com
300 E. Swedesford Road
Wayne,  PA 19087-1858
(610) 964-9000

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This project addresses the development of refractory coated or lined low density structures applicable for advanced future propulsion system technologies. The fundamental idea behind this concept was to design a hot-walled refractory material (ceramic and/or metallic) in the form of a thin coating or liner and have that supported by a low density structure such as graphite or various carbon-carbon composites, offering an attractive lightweight design option. This coated or lined low density structure combines the compatibility and hermetic seal of the ceramic and/or metallic hot-walled material with a lightweight, high strength to weight ratio support material such as graphite or carbon-carbon composites. The advantage of this particular concept can be observed by both the weight and cost savings compared to, for example, current solid monolithic refractory propulsion components. Lightweight structures are desirable for space transportation vehicle systems in order to reduce launch costs, increase mission flexibility, increase mission efficiency and add robustness with respect to the ability to add weight or additional materials to the mission with minimum sacrifice in performance. This general concept is applicable to thrust vector controls, combustion chambers, nozzles and thrusters. One study has shown that replacing a solid monolithic rhenium pintle and seat with a rhenium lined graphite version can offer both weight and cost savings as high as 80 - 90%.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The results of this refractory coated or lined low density structures study will be applicable to all four of the NASA Fundamental Aeronautics Programs research thrust. Specifically, the fundamental technology and design tools developed in this Phase I effort can be expanding for design and analysis techniques/procedures for various high temperature material components such as rocket nozzles, leading edges, hypersonic airframes and ramjet engines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
MR&D's core business is design and thermal-structural analysis of high temperature composite and refractory materials. The fundamental technology and design tools developed in this SBIR program will allow us to expand our client base and offer more capabilities to our existing customers. Additionally, the technology developed here will be translated to other commercial and government applications to expand the market for refractory coatings/liners on lightweight support structures in rocket nozzles, leading edges, hypersonic airframes and ramjet engines. The results of this refractory coated or lined low density structures study will additionally have broad ranging applications in civil aerospace, governmental aerospace companies, as well as aircraft jet engine manufactures and power generation equipment manufacturing companies. Potential customers include Boeing, Lockheed Martin, General Electric Power Systems and ATK-Thiokol.

TECHNOLOGY TAXONOMY MAPPING
Chemical
High Energy Propellants (Recombinant Energy & Metallic Hydrogen)
Simulation Modeling Environment
Testing Facilities
Reuseable
Thermal Insulating Materials
Database Development and Interfacing
Ceramics
Composites
Metallics


PROPOSAL NUMBER: 09-2 S3.08-8305
PHASE-1 CONTRACT NUMBER: NNX10CC61P
SUBTOPIC TITLE: Planetary Ascent Vehicles
PROPOSAL TITLE: NOFBX Single-Stage-to-Orbit Mars Ascent Vehicle Engine

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Firestar Engineering, LLC
1122 Flightline Street, #76
Mojave, CA 93501-1610
(661) 339-9696

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Greg Mungas
greg.mungas@firestar-engineering.com
1122 Flightline Street, #76
Mojave,  CA 93501-1610
(303) 303-2698

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose the continuation of our research and development of a Nitrous Oxide Fuel Blend (NOFBXTM) Single-Stage-to-Orbit (SSTO) monopropellant propulsion system for future use on a Mars Ascent Vehicle (MAV) as part of the Mars Sample Return (MSR) architecture. This liquid monopropulsion system architecture is also readily scalable to alternative planetary ascent vehicles (PAV's) and sample return systems. Key areas of our proposed development and demonstration are in the nozzle miniaturization to support compact vehicle packaging into an MSR vehicle and use of a passive thrust vector control mechanism with three engines to avoid the necessity of a low temperature gimbal mechanism.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Successful research in this area will provide an enabling capability for planetary accent vehicle technology. The NASA applications are many, the foremost being the opportunity to supply the propulsion system for Mars Sample Return Missions. However this technology may be applied to lunar comet and other planetary missions that require an accent vehicle propulsion system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial space and military applications will likely be able take advantage of the performance enhancements for NOFBXtm propulsion systems and the thrust vectoring technology that will be developed under the proposed effort. Commercial entities already interested in NOFBXtm mono-propulsion systems include Space X, Ball Aerospace and Boeing.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Monopropellants
Propellant Storage
Feed System Components
Attitude Determination and Control
Guidance, Navigation, and Control
Composites


PROPOSAL NUMBER: 09-2 S3.08-8312
PHASE-1 CONTRACT NUMBER: NNX10CC62P
SUBTOPIC TITLE: Planetary Ascent Vehicles
PROPOSAL TITLE: Magnesium Based Rockets for Martian Exploration

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Busek Co., Inc.
11 Tech Circle
Natick, MA 01760-1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Szabo
jszabo@busek.com
11 Tech Circle
Natick,  MA 01760-1023
(508) 655-5565

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the proposed Phase II program, we will continue the development of Mg bipropellant rockets for Martian PAV applications. In Phase I, we proved the feasibility of this game-changing technology. Through chemical analysis, we determined that Mg can be combusted with CO2 condensed in-situ from the Martian atmosphere to yield Isp ~240 s. We then successfully demonstrated a low fidelity Mg-CO2 rocket in the laboratory, achieving combustion for 43s before voluntary termination. We also analyzed the use of H2O and H2O2 as oxidizers, and Al as a propellant. H2O exists at the Martian poles and below the surface, while both Mg and Al can be acquired in-situ from the Martian regolith. We determined that the ideal vacuum Isp of a 10 bar Mg-H20 rocket would be as high as ~340 s, while the Isp of a Al-steam rocket would be ~380 s, and hydrogen peroxide could yield higher density Isp and operational benefits. In Phase II we plan to develop and test an integrated high performance laboratory model system. We will first fully characterize multiple propellant oxidizer combinations in a linear combustor. Then we will design, build, and test an integrated system including both a rocket and a propellant management system. Comprehensive test results would feed back into the design, culminating in an advanced system sized for prospective near-term applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This energetic, non-toxic, storable propellant technology can be used in-space, and to explore Mars, Phobos, the Moon, and NEOs. The target application is Martian Payload Ascent Vehicle (PAV) propulsion. This application benefits from near, mid, and far-term ISRU opportunities. In the near-term; the metal can be carried to Mars while the CO2 can be compressed from the atmosphere. In the mid-term, H20 can be extracted from the sub-surface or polar caps. In the far term, Mg and Al could be extracted from the soil using electrolysis. Alternately, spent Al or Mg spacecraft structures could be processed into fuel. Similar possibilities exist on the Moon and Phobos, both of which are believed to contain large reservoirs of water ice. Once on orbit, Mg based rockets or Hall thrusters could propel the samples back Earth. This non-toxic engine technology could also supplant MMH/NTO for in-space applications such as satellite propulsion and manned service modules.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Mg and Al bipropellant rockets are high performance, non-toxic alternatives to hydrazine and MMH bipropellants. Government and commercial satellites would use metal bipropellant thrusters for on-orbit operations including orbit-raising, station-keeping, and repositioning. Metal bipropellants could also be used in upper stages and as apogee engines. In a multi-mode in-space propulsion system, a Mg-water rocket could provide high thrust while a Mg Hall thruster could provide low thrust at high Isp. This system would be both fuel efficient and responsive. Atmospheric applications of Mg-water combustion technology could include HALE aircraft. Naval applications include: a water breathing, high speed rocket propelled torpedo: a low speed , long range, unmanned undersea vehicles; long duration sensor power. Other commercial applications include very dense and green chemical hydrogen sources for fuel cell applications. This application may be of particular interest to the automobile industry.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Propellant Storage
Feed System Components
In-situ Resource Utilization
Energy Storage


PROPOSAL NUMBER: 09-2 S3.08-9779
PHASE-1 CONTRACT NUMBER: NNX10CD13P
SUBTOPIC TITLE: Planetary Ascent Vehicles
PROPOSAL TITLE: Hot Gas TVC For Planetary Ascent Vehicle

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Wickman Spacecraft & Propulsion Co.
3745A Studer
Casper, WY 82604-1339
(307) 265-5895

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Wickman
jwickman@wickmanspacecraft.com
3745A Studer
Casper,  WY 82604-1339
(307) 307-5895

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A Mars ascent vehicle (MAV) uses solid rocket motors to propel soil samples into orbit, but the motors cannot provide steering. Flexseal TVC control is planned for the first stage while hydrazine thrusters will be used for spin stabilization of the second stage. This approach is heavy and results in a spinning sample container in orbit, which is difficult to recover. Wickman Spacecraft & Propulsion Company (WSPC) proposes innovative hot gas thrusters for steering that use the gases from the solid rocket combustion chambers. This approach is lighter, improves orbit insertion accuracy and provides a non-spinning orbiting container to increase mission success probability. The MAV valves must handle metalized gases at 3,093 C. During Phase I, WSPC demonstrated a hot gas valve operating above 3,093 C with the same propellant to be used in MAV. Valves from all other companies must operate at 2,760 C or below with little metal in the exhaust gas. During Phase II, WSPC will demonstrate a MAV first stage thruster and multiple MAV first stage thrusters operating from a single solid rocket motor using MAV solid propellant. This final demonstration test will simulate a typical MAV first stage TVC duty cycle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA product is a hot gas thruster TVC system for planetary ascent vehicles that provide (1) higher mission reliability, (2) easier docking and rendezvous for returning samples to earth, (3) lower weight for higher payloads, (4) higher orbit insertion accuracy and (5) higher thrust vector angles. The technology can also be used for manned capsule escape systems with thrust management and thrust vector control. This would enable astronauts in a capsule to control the abort trajectory and land in a safe area. It could also be used for real time thrust control for solid rocket motors on planetary landers. Another application is thrust management of solid rocket boosters on small launch vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
WSPC will produce hot gas TVC systems for Star and similar motors used to boost satellites into higher orbits. These motors currently do not have any TVC capability. With WSPC's new TVC systems, satellites would be boosted into more accurate orbits without spinning the satellite. Since the satellite is not spinning, it would not have to waste precious fuel de-spinning before beginning operation in orbit. This gives satellites a longer life in orbit before running out of station keeping fuel. WSPC will produce a variable throat nozzle for tactical missiles for thrust management. These nozzles will be cheaper, lighter and require less electrical power than conventional pintle nozzles. The requirement for less power will lighten the missile and permit more range or a larger warhead for a fixed range. WSPC will also market nozzles for ejector seats and small aircraft parachute deployment systems, which use solid rocket motors.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Ablatives
Feed System Components
Attitude Determination and Control
Guidance, Navigation, and Control
Composites
Metallics


PROPOSAL NUMBER: 09-2 S3.09-8087
PHASE-1 CONTRACT NUMBER: NNX10RA58P
SUBTOPIC TITLE: Technologies for Unmanned Atmospheric Platforms
PROPOSAL TITLE: Cold Weather Technology Development for Low Altitude Ultra-Long Endurance Applications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vanilla Aircraft, LLC
2822 Mary Street
Falls Church, VA 22042-7716
(703) 849-9070

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Daniel Hatfield
daniel@vanillaaircraft.com
2822 Mary Street
Falls Church,  VA 22042-7716
(703) 849-9070

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Currently, wide area coverage with manned aircraft, or existing unmanned air systems, requires expensive logistical operations and many flight sorties, which are made especially difficult if operating from remote airfields in inhospitable climates. There is currently a need for a low-altitude long endurance unmanned aircraft that can provide the expansive coverage necessary for cryospheric investigations. Extreme cold places unique requirements on aircraft if they are to operate consistently and reliably in these environments. Building on the successful results of the Phase 1 SBIR work, this Phase 2 SBIR will test low temperature long-endurance unmanned aircraft engine and systems technologies in a relevant environment through flight test of a prototype unmanned air system and associated work.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed development will play a useful role for NASA, particularly in conjunction with Operation ICE Bridge. This program is intended as a stopgap for polar ice mapping using NASA's aerial assets until the launch of ICESat-II in 2014-15. The wide area coverage needed by NASA to assist in this mission necessitates a low-altitude long endurance unmanned aircraft capable of reliably operating in extremely cold conditions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low altitude ultra-long endurance aerial capability has broad applications outside of NASA, including other environmental research organizations and government agencies, as well as for maritime surveillance, distant search and rescue and other functions for a broad range of public and civil entities. The platform will reach a system maturity to allow maximum endurance missions by a broad range of civil and public entities at a time that coincides with the FAA time frame for broad integration of UAS into the national airspace. This integration will greatly expand the market beyond the mostly government customers that exists today.

TECHNOLOGY TAXONOMY MAPPING
Aircraft Engines


PROPOSAL NUMBER: 09-2 S3.09-8252
PHASE-1 CONTRACT NUMBER: NNX10RA52P
SUBTOPIC TITLE: Technologies for Unmanned Atmospheric Platforms
PROPOSAL TITLE: Dropsonde System for Unmanned Aerial Vehicles

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Anasphere, Inc.
106 Pronghorn Trail
Bozeman, MT 59718-6081
(406) 994-9354

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Bognar
jbognar@anasphere.com
106 Pronghorn Trail
Bozeman,  MT 59718-6081
(406) 406-9354

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A small, modular dropsonde launcher is being developed for Unmanned Aerial Vehicles (UAVs). Some critical measurement needs can only be satisfied by in-situ measurements. Key examples of such measurements include detailed atmospheric profiles, point meteorological conditions on the surface, and in-situ measurements for calibration and validation of remote sensing systems. Phase I work saw the design and fabrication of a new type of dropsonde with a novel form factor and the associated launcher. The system was installed in a representative UAV nose. System components were successfully tested. Phase II will involve finalizing the launcher and dropsonde designs, developing the associated control and data handling system, building and testing the integrated system, and finally conducting test flights on a UAV. The ultimate result of the project will be a dropsonde system that can be fitted to many NASA UAVs, including small UAVs, and enable them to gather in-situ atmospheric profiles and surface measurements using dropsondes. The Phase II entry TRL is 5; the expected exit TRL is 8.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Several areas of NASA research will be able to make use of dropsonde-equipped UAVs. One prominent area that will benefit is hurricane research: dropsondes would bring a new dimension to the data gathered by UAVs flying into hurricanes, making their measurements more comparable to those of manned aircraft. A second area is wildland firefighting operations: dropsondes would allow the UAV to return local meteorological profiles that could be used to improve the point weather forecasts developed by fire meteorologists. Atmospheric and polar research are two more generic areas of research which will benefit from a dropsonde system for UAVs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other agencies engaged in the use of UAVs for atmospheric research or operational meteorology measurements (e.g., NOAA and the Department of Defense) would be able to use this dropsonde system on their UAVs. Elements of the system, such as the dropsondes themselves, may be applied in other dropsonde launchers deployed on other platforms as well. A radiosonde derived from the dropsonde will potentially meet the needs of the very large radiosonde market.

TECHNOLOGY TAXONOMY MAPPING
Sensor Webs/Distributed Sensors


PROPOSAL NUMBER: 09-2 S4.01-9047
PHASE-1 CONTRACT NUMBER: NNX10CC28P
SUBTOPIC TITLE: Radiation Hardened High-Density Memory, High Speed Memory Controllers, Data Busses
PROPOSAL TITLE: Very Dense High Speed 3u VPX Memory and Processing Space Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SEAKR Engineering, Inc.
6221 S. Racine Circle
Centennial, CO 80111-6427
(303) 790-8499

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Coe
michael.coe@seakr.com
6221 S. Racine Circle
Centennial,  CO 80111-6427
(303) 790-8499

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
While VPX shows promise as an open standard COTS computing and memory platform, there are several challenges that must be overcome to migrate the technology for a space application. For the Phase I SBIR, SEAKR investigated the 3u VPX architecture for the space environment for advanced memory and processing systems. The SBIR investigation focused on researching innovative switch fabric architectures, identifying and qualifying the building blocks for a space qualified VPX system, and addressed some of the challenges associated with VPX flash memory modules. The areas of innovation that have been addressed are outlined below: ? Research and evaluate the basic building blocks required for a high speed switch VPX architecture ? Explore advanced EDAC and innovative wear leveling techniques for commercially upscreened flash memory for space applications ? Evaluate different techniques for very high speed flash memory access rates The Phase II SBIR will build on the Phase I study to produce a deliverable engineering model of a 3U VPX flash memory module.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are several programs that could utilize an advanced integrated memory and processing system. The NASA Earth Science Technology Office (ESTO) is funding the development of the SpaceCube 2.0 system to support the upcoming series of Earth Science Decadal Survey missions including HyspIRI, ACE, LIST, DESDynI, GEO-CAPE, and 3D-Winds. It is also in the baseline architecture for the new Robotic Servicing program called 3+ missions under Mr. Frank Cepollina (deputy director for Hubble). Several Space Science missions (MMS follow-on, TESS, next-gen telescopes, Venus mission) are considering or doing proof-of-concept demos with SpaceCube. The POC for the ESTO and SpaceCube 2.0 is Mr. Thomas Flatley, the branch head of Science Data and Processing (Code 587). He is very interested in working with SEAKR to develop a high speed NVM module and has been briefed on SEAKR's phase 1 SBIR objectives. His email is thomas.p.flatley@nasa.gov.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to NASA phase III opportunities, there are several programs within AFRL and MDA which could be potential phase III candidates. These programs are considering the 6U version because of redundancy and enhanced functionality. The Precision Tracking Space System (PTSS) is a MDA program that is being lead by the John Hopkins Advanced Physics Laboratory (APL). The PTSS optical payload processor has requirements for a high speed, low power, non-volatile memory module. The optical payload deputy, Matt Grey, is interested in having NASA fund the phase II SBIR in support of his program. His email is matthew.grey@jhuapl.edu.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
On-Board Computing and Data Management
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 S4.05-8441
PHASE-1 CONTRACT NUMBER: NNX10CC31P
SUBTOPIC TITLE: High Torque, Low Jitter Reaction Wheels or Control Moment Gyros
PROPOSAL TITLE: Reaction Wheel with Embedded MEMS IMU

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Milli Sensor Systems and Actuators, Inc.
93 Border Street
West Newton, MA 02465-2013
(617) 965-4872

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Donato (Dan) Cardarelli
dcardarelli@mssainc.com
93 Border Street
West Newton,  MA 02465-2013
(617) 965-4872

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Reaction wheels are used to stabilize satellites and to slew their orientation from object to object with precision and accuracy by varying the rotational speed of the wheels. Three or four wheels are usually used with three of them aligned along orthogonal axes. The degree to which pointing stability is achieved depends on the stability of the wheels' angular momentum vectors while spinning, which can be affected by static and dynamic unbalance contributions and other wheel construction issues. With the smaller satellites, requiring smaller wheels, the stability of the wheels will be even more challenging as the uncertainty of construction is likely to remain the same. To stabilize the smaller reaction wheels we propose to integrate a Sensor Chip containing MEMS gyroscopes and accelerometers with each reaction wheel. This allows direct measurement of the wheel motions for fine-tuning its operation. The improved wheel then becomes a means for improving IMU sensor stability for precision pointing and slewing from object to object.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MSSA's MEMS IMU Sensor Chip enables modular and programmable guidance & navigation systems with significantly reduced mass and cost for low-cost small spacecraft, microsatellites and nanosatellites. A MEMS IMU integrated with a reaction wheel enables both the measure of spin rate as well as the determination of attitude when three wheels are used. The applications are generally pointing and tracking.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
MSSA's single-chip Integrated MEMS IMU will be substantially smaller and less expensive, and will enable more highly-integrated applications than are possible with other MEMS IMUs. The principal military applications of MEMS IMUs are for interceptors and for precision-guided munitions, especially spinning munitions. Other military and commercial applications for MEMS IMUs are for the stabilization and GN&C of vehicles; for the stabilization and GN&C of small UAVs and for stabilization of UAV-borne sensors, seekers and cameras, (including Homeland Security and police operations); lower-cost IMUs for air, land and water vehicle navigation, with or without GPS-aiding; Personal Navigation for warfighters and civilian "first responders" such as fire-fighters; robotic stabilization and GN&C; precision motion tracking for portable/wearable systems (helmets & headsets); precision pointing and tracking for satellites, antennas and telescopes; and bore-hole measurement systems.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Teleoperation
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control
Autonomous Control and Monitoring
Sensor Webs/Distributed Sensors


PROPOSAL NUMBER: 09-2 S4.05-9322
PHASE-1 CONTRACT NUMBER: NNX10CC33P
SUBTOPIC TITLE: High Torque, Low Jitter Reaction Wheels or Control Moment Gyros
PROPOSAL TITLE: TORC-SP: High Torque, Low Jitter Scissored-Pair CMG Technology

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W. 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kiel Davis
davis@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(646) 459-7809

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA sees an increasing role in the near future for small satellites in the 5-100 kg size range. A potentially disruptive technology, small satellites are being eyed as platforms for the rapid demonstration of new technologies and important science missions. Currently, small satellite platforms struggle to balance the three critical tasks of collecting enough power, acquiring data and downlinking that data to ground stations in a way that maximizes mission return. For these small platforms, which usually do not benefit from steer-able solar arrays or gimbaled antennas and instruments, optimally balancing these three tasks strongly depends on the satellite's attitude control agility. Spacecraft agility has to do with rapid retargeting, fast transient settling and low jitter pointing control. Dr. Bong Wie, renowned spacecraft attitude control expert and Professor of Aerospace Engineering at Iowa State University, stated that ultimately the "measure of an agile satellite attitude control system is its ability to collect the maximum data from an area on the Earth that is rich in data-collection opportunities". A logical corollary following from this statement would be that to maximize satellite data-collection, system designers should look to increase the satellite's agility. Furthermore, in addition to data-collection, the other two critical tasks of power collection and data downlink are also maximized as agility is increased. Honeybee Robotics proposes to develop a low cost, high torque and low jitter satellite attitude control actuator derived from its Tiny Operationally Responsive CMG (TORC) design. This derivative product would combine two TORC units into a single scissored-pair configuration with SPA compatible interface. The result, a flight-certified TORC-SP, would be an actuator with the simple control interface of a reaction wheel that offers 1-2 orders of magnitude more torque per unit mass at drastically less power than a reaction wheel.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Small satellites which are low cost and can be delivered in months (as opposed to years), are being eyed as platforms for rapid demonstration of new technologies (e.g., new propulsion, communications, power collection and MEMS technologies) and even important science missions (e.g., earth and space climate observation, biological sciences). From NASA's recently launched PharmaSat sub-10 kg free-flying nanosatellite, which has just successfully completed an experiment that could help scientists better understand how effectively drugs work in space, to potential future missions like the Reef Ecosystem Spectro-Photometric Observatory (CRESPO), a ~100 kg microsatellite that will use a hyperspectral imager (HSI) to monitor the condition of more than 50% of the Earth's coral reefs over a 2-year period, NASA is counting on these small satellites to deliver.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
At MILSPACE 2009 Karyn Hayes-Ryan, Associate Chief Operating Officer of the National Reconnaissance Office (NRO) offered that CubeSats might be the next transforming innovation in space development primarily because they offer a means for rapidly maturing new technologies to ultimately be used by larger NRO intelligence gathering satellites. The vision of CubeSats as technology demonstration platforms will only be realized when their data downlink capability matches their data acquisition capability. At the moment, CubeSat communications are extremely limited. To boost communications, they need more power and they need to focus and aim that power in the form of directed transmissions. Beyond the "CubeSat as a test and demonstration platform" model, the information developed under the proposed study would inform Intelligence, Surveillance and Reconnaissance (ISR) mission planners considering the use of small agile satellites in the 3 to 50 kg range. The TORC-SP system is a scalable and rapidly reconfigurable ACS for CubeSats; allowing fast, low-cost, on-demand agile ACS development.

TECHNOLOGY TAXONOMY MAPPING
Mobility
Manipulation
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control


PROPOSAL NUMBER: 09-2 S5.02-8626
PHASE-1 CONTRACT NUMBER: NNX10CE15P
SUBTOPIC TITLE: Sample Collection, Processing, and Handling
PROPOSAL TITLE: Sealed Planetary Return Canister (SPRC)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Techno Planet Incorporated
17340 Rayen Street
Northridge, CA 91325-2936
(818) 709-7815

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Stanley
spstanley@technoplanetinc.com
17340 Rayen Street
Northridge,  CA 91325-2936
(818) 709-7815

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Sample return missions have primary importance in future planetary missions. A basic requirement is that samples be returned in pristine, uncontaminated condition, necessitating development of a canister system capable of maintaining cleanliness and seal integrity through a variety of environments. Further development of the Sealed Planetary Return Canister (SPRC), is proposed after a successful Phase 1 program. Besides providing a high integrity seal, the canister incorporates features for robotic manipulation and to allow the sample to be accessed in a controlled manner upon return to Earth. The SPRC seal system addresses the two most significant concerns for planetary samples ? seal surfaces contaminated by the sample and high pressure due to the phase change of volatiles. The SPRC incorporates a novel sealing system evolved from the only marginally successful Apollo indium knife edge seal approach but with added features to address the difficulties and inconsistencies observed. The indium is contained within a protective barrier to prevent against contamination, and the knife edge is mechanically cleaned during the sealing process. The container body can be configured to accommodate a variety of samples including rock cores, rock fragments, regolith, dust, and frozen soil. Atmospheric samples can also be preserved. The design is readily scalable and adaptable to specific missions. The prototype developed in Phase 1 demonstrated a leakage rate of less than 1e-6 cc-atm/s, meeting the primary science requirement.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential missions to targets throughout the solar system have been identified that would utilize the SPRC sample return canister, particularly missions to Mars and the Moon. Mars Sample Return is the most visible mission requiring an SPRC device. Even one funded mission would justify the continued development of the SPRC through the SBIR program. Significant savings would be realized through the repeated use of a standardized approach developed under this program. The SPRC could also find use for in-situ resource utilization (ISRU) prospecting. ISRU requires that samples be acquired and analyzed for their volatile content to determine mining locations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Additional science applications (through NASA or other government organizations such as the NSF) include terrestrial investigations requiring the securing of pristine samples, particularly those containing volatiles of interest - Arctic and Antarctic ice, untouched water reservoirs, volcanic samples etc. While containers are available commercially that can be filled and sealed by a human operator, these environments are not always accessible to humans and a robotic-compatible container would fill a currently empty niche. Non-NASA applications could include gathering samples in hostile environments such as nuclear or hazardous waste sites. These require robotic interfaces to isolate human operators from the dangerous environment.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Manipulation
Teleoperation
Sterilization/Pathogen and Microbial Control
General Public Outreach
In-situ Resource Utilization
Metallics
Organics/Bio-Materials


PROPOSAL NUMBER: 09-2 S5.02-9092
PHASE-1 CONTRACT NUMBER: NNX10CE17P
SUBTOPIC TITLE: Sample Collection, Processing, and Handling
PROPOSAL TITLE: Extreme Temperature Gearhead

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W. 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jerri Ji
ji@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(646) 459-7810

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In response to the need for actuators that can operate in the harsh Venusian environment for extended periods of time, Honeybee Robotics conducted extensive research and testing to resolve the tall poles in developing an extreme temperature gear. During the Phase I effort, multiple gear material and lubrication candidates were tested under load in Venus-like conditions (486<SUP>o</SUP>C temperature and mostly CO2 gas environment). Test results verified the feasibility of a design and confirmed that, with proper material and lubrication selection, the gear head could operate at 486<SUP>o</SUP>C for an extended period of time. In a potential Phase II effort, material and lubrication study will continue as well as a high temperature bearing study. At the end of the Phase II, an extreme environment actuator, including a HT motor, HT sensor for commutation and multi-stage HT gear head, will be developed and tested to TRL 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Fully developed and optimized versions of the gear head, as part of the high temperature actuators, could be used to actuate drills, robotic arms, and other devices outside of an environment-controlled landed platform on the surface of Venus. The device's ability to survive for extended periods in this harsh environment is a major benefit to future Venus science missions and could permit time for communication ground loops to optimize sampling and drilling target selection as well as allow for multiple samples to be acquired from the subsurface. Besides Venus applications, the HT actuators can be used for robotic exploration of terrestrial volcanoes and hydrothermal vents, gimbal systems or other devices on spacecraft that orbit close to the sun or Mercury.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other potential applications identified include (1) munitions and weapons control, (2) gas turbine starter/generators for aircraft engines, (3) actuators for turbine fuel and steam control, inlet guide vane positioning, bleed heat valve control and remote subsea system actuation, (3) furnace tending for glass/ceramic manufacturing (for example, loading and unloading of castings, glass furnaces and hot or heavy metal, glass or ceramic parts.)

TECHNOLOGY TAXONOMY MAPPING
Manipulation


PROPOSAL NUMBER: 09-2 S5.03-9090
PHASE-1 CONTRACT NUMBER: NNX10CE18P
SUBTOPIC TITLE: Surface and Subsurface Robotic Exploration
PROPOSAL TITLE: Arm-Deployed Rotary-Percussive Coring Drill

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Honeybee Robotics Ltd.
460 W. 34th Street
New York, NY 10001-2320
(212) 966-0661

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jack Wilson
wilson@honeybeerobotics.com
460 West 34th Street
New York,  NY 10001-2320
(646) 459-7816

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The continued development of automated sample acquisition and handling tools is of critical importance to future robotic missions on Mars, the Moon, Venus, and other planetary bodies. In response to the need for a compact, low mass, low power, and low weight-on-bit coring device, Honeybee Robotics proposes to continue development of an arm-deployed and arm-stabilized rotary-percussive coring tool. By using a robotic arm to deploy the coring tool into rock or soil targets and stabilize the tool while operating, the coring tool's internal deployment (or "z") axis and external stabilization devices can be removed, resulting in a more compact, lower mass device. Also, adding percussion to the coring tool will reduce average weight-on-bit and energy consumption over the duration of the coring operation. The flexibility afforded from a rover or lander arm to target outcroppings, and the relatively higher TRL of surface coring tools (vs. deeper subsurface drills), make surface coring, especially with an arm-deployed coring tool, a particularly attractive option for near term planetary exploration. During Phase I, a preliminary coring tool design was developed that weighs less than 5 kg and meets all of the current MSR requirements. Breadboard testing also demonstrated the feasibility of arm-deployed and stabilized coring. The objectives of Phase II are to further develop, demonstrate and characterize a TRL 5/6 MSR-compatible coring tool. The rotary-percussive coring tool will weigh less than 5 kg, be arm-deployed and stabilized, include a passive linear feed device, require less than 50 N weight-on-bit, produce and capture 1 cm diameter by 5 cm long cores, accommodate active bit change-out and passive bit release, and positively retain cores in core tubes when removed from the bit. The coring tool will be fully demonstrated and characterized at ambient and Mars conditions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future robotic astrobiology and geology missions such as Mars Sample Return, Astrobiology Field Laboratory and other Mid-Range Rover missions will benefit greatly from the ability to produce and capture rock and regolith cores using an arm-deployed, arm-stabilized, compact, low mass, low power device. Such a coring drill could also be deployed during lunar sortie missions by astronauts (operating as a hand-held coring drill) since it is desirable to bring small cores back to Earth as opposed to large rocks. From a science standpoint, core samples have a distinct advantage over collected drill cuttings in that the stratigraphy and morphology of the sample is preserved. This facilitates detection of localized organics and fossil biosignatures, as well as analysis of geochemistry and mineralogy. The need for a flight-ready surface coring tool has been evident in various NASA program reviews, mission concepts, and mission baselines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Rotary-percussive core drilling has many terrestrial applications in industry and in the research and development fields. Core samples are integral to the study of a wide range of fields, from geological classification to ocean drilling and surveying. Potential applications of the proposed coring technology include sidewall coring and subsampling for the petroleum industry, as well as in the study of earthquake mechanics or terrestrial biology (specifically coring in the Arctic and Antarctic.) Automation of the rotary-percussive coring process would also benefit these industries and fields, saving time and money and enabling the engineering and science goals of the various applications to be realized with reduced schedule and budget risk.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Manipulation
Perception/Sensing
Teleoperation
Tools
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 S5.03-9737
PHASE-1 CONTRACT NUMBER: NNX10CE19P
SUBTOPIC TITLE: Surface and Subsurface Robotic Exploration
PROPOSAL TITLE: High Torque, Direct Drive Electric Motor

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Bear Engineering
2415 Two Turtles Road
Maidens, VA 23102-2238
(804) 240-0814

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Myrick
tom.myrick@gmail.com
2415 Two Turtles Road
Maidens,  VA 23102-2238
(804) 240-0814

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Bear Engineering proposes to advance the development of an innovative high torque, low speed, direct drive motor in order to meet NASA's requirements for such devices. Fundamentally, all electric motors basically work on the same electromagnetic principle: a tangential electromagnetic force attracts the rotor to the stator. Just when the rotor field is closest to the stator field and the electromagnetic attraction is greatest, the power is interrupted and another set of magnetic poles repeats the cycle. Furthermore, the two magnetically attracted elements never make contact, which would otherwise offer the highest force of attraction. The proposed novel motor design, successfully demonstrated at TRL 4 in Phase 1, operates and behaves entirely differently from all other known electric motor designs and is capable of producing incredibly high, direct drive torques at low rotational speeds. Its operational performance is similar to that of a stepper motor with a 1000:1 gearhead attached, but the similarity ends there. The motor is configured such that its length to diameter aspect ratio is opposite that of traditional motors as it has a relatively large diameter and short axial length; this offers all new packaging opportunities. The design also allows for a single, large diameter bearing pair to be used for the motor's output shaft which renders it stiff enough to directly mount the driven elements. The need for additional bearing supports and bearing mounting structure is thus eliminated. By the end of Phase 2, the system will be designed, developed and tested at TRL 6 with Mars environmental conditions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
For NASA, the proposed innovation is an enabling technology for planetary exploratory missions and a number of possible applications are envisioned for the motor, some examples are: Robotic arm joints, Rover wheel steering and drive actuators, Core drill sample Break-off actuators, Antenna Mast and Solar array deployment and Launch locks.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed motor will have a number of commercial applications in areas where slow speed and high output torques or forces are needed. For example, the motor could be used in applications where pneumatic or hydraulic actuators are required for high output forces. More specifically, commercial applications for the motor are anticipated in: winches, lifts, positioning equipment, structural deployment, presses and door openers/ lifts.

TECHNOLOGY TAXONOMY MAPPING
Mobility
Manipulation
Tools
In-situ Resource Utilization


PROPOSAL NUMBER: 09-2 S5.04-8643
PHASE-1 CONTRACT NUMBER: NNX10CE20P
SUBTOPIC TITLE: Rendezvous and Docking Technologies for Orbiting Sample Capture
PROPOSAL TITLE: Reactive Rendezvous and Docking Sequencer

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Blue Sun Enterprise, Inc.
1942 Broadway Street, Suite 314
Boulder, CO 80302-5233
(720) 394-8897

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christopher Grasso
christopher.a.grasso@earthlink.net
1942 Broadway Street, Suite 314
Boulder,  CO 80302-5233
(720) 720-8897

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 6
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Mars Sample Return poses some of the most challenging operational activities of any NASA deep space mission. Rendezvous of a vehicle with a sample canister in order to return the canister to Earth requires a variety of complex mathematical processing on a changing data set, coupled with the need to safely and effectively handle a large range of off-nominal conditions and spacecraft faults. Light speed delay isolates the spacecraft from real-time operator intervention, while inertial and situational uncertainties demand reactivity not required of typical spacecraft sequencing systems. These mission features call for a new class of sequence capability: Reactive Rendezvous and Docking Sequencer (RRDS). RRDS melds the rule-based reactivity needed for rendezvous and docking with sequence characteristics common to more traditional missions. Rules watch for conditions in order to react to the current situation, allowing a wide range of complex activities and safety-related responses to be concisely represented without complex procedural programming. Responsibility for commanding elements aboard the spacecraft is divided among sequenced state machines called managers, coordinated together by a flight director which the ground commands. Underlying flight software for navigation, thruster allocation, inertial checking, attitude estimation and control, contact detection, docking mechanisms, and the like receive direction from the managers. This mediated control causes the system to reactively operate in modes with proper ordering of activities. Reactive operations are represented explicitly by states and transitions defining the managers, and do not require use of explicitly timed activities. Phase II of this SBIR will produce a Class B version of the underlaying VML 2.2 flight software capable of executing the RRDS state machines. It will also produce Class C versions of the associated VML compiler and Offline VM execution system for deployment onto flight projects.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
RRDS may be applied to a variety of commercial missions reactively operating spacecraft in complex scenarios, like deep space missions retrieving samples from a variety of planetary bodies, comets, asteroids, or moons. RRDS could also be used on uncrewed cargo flights to a space station or assembly site. Executable state machines provided by VML 2.2 allow many kinds of autonomy to be created, outside of the RRDS realm. These include: ? reactive fault protection which is cheaper to develop and more transparent in operation than a flight software implementation ? autonomy for self-directed orbital missions requiring limited operational interaction with controllers, reducing personnel costs ? autonomy for self-directed comet / asteroid sampling missions requiring limited operational interaction with controllers, reducing DSN time and personnel costs ? on-board replanning to compensate for degraded and failed systems in a high radiation, remote environment like Europa orbit ? autonomy for landed vehicles and rovers, reducing the risk to the mission and simplifying mission operations ? target-of-opportunity science collection in earth-orbiting or deep space environments, allowing detected events to result in further detailed observations (e.g. detected volcanic activity leading to taking a raster of images) ? expert systems for guiding remote experiments in real-time based on observed environmental conditions

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
VML 2.2 allows autonomy to be created for commercial low earth orbiting observation missions that would permit targets of opportunity for observations to be identified and acted upon. Autonomy in this regime could also simplify spacecraft operations by allowing onboard systems to make more decisions, and reduce the need for off-shift operations personnel. Many of the NASA commercial applications listed above also have potential terrestrial applications. VML 2.2 autonomy capabilities could be applied to autonomous vehicle control, manufacturing process controllers, airborne systems, and remote science stations with limited contact time. The state-machine approach has an advantage over autocoded systems in that the embedded software is not unique for every flight software load, reducing risk and enhancing system insight.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Teleoperation
Operations Concepts and Requirements
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Expert Systems
Human-Computer Interfaces
Software Development Environments
Manned-Maneuvering Units
Aerobrake


PROPOSAL NUMBER: 09-2 S5.04-9755
PHASE-1 CONTRACT NUMBER: NNX10CE21P
SUBTOPIC TITLE: Rendezvous and Docking Technologies for Orbiting Sample Capture
PROPOSAL TITLE: SPHERES MOSR Rendezvous and Docking with the OS (RDOS)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aurora Flight Sciences Corporation
9950 Wakeman Drive
Manassas, VA 20110-2702
(703) 369-3633

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Francis
jfrancis@aurora.aero
1 Broadway, 12th Floor
Cambridge,  MA 02142-1189
(617) 500-0276

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In order to support the tools needed to develop the Mars Sample Return (MSR) rendezvous and capture of the Orbiting Sample (OS), Aurora and MIT Space Systems Lab proposed the development of the Mars Orbiting Sample Return (MOSR) Rendezvous & Docking with the OS (RDOS) system. This system supports development of GN&C algorithms to address the "last few meters" operation between the chaser spacecraft and OS and extends the capabilities of the current SPHERES MOSR test bed. During Phase 1, the team demonstrated the feasibility of the visual navigation and controls infrastructure for the test bed. During Phase 2, the team proposes to integrate these capabilities into the test bed while engaging the NASA safety process throughout the development effort, resulting in ISS flight payload hardware ready for environmental testing and safety approval.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
? Mars Sample Return Mission ? Cometary and other missions involving sample transfer in orbit to a return vehicle ? Other missions involving on-orbit rendezvous and docking/capture ? Flat floor, parabolic flight, and on-orbit implementations

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
? Similar capabilities offered to DoD or industry researchers who require a testbed for rendezvous and capture operations

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Guidance, Navigation, and Control
On-Board Computing and Data Management


PROPOSAL NUMBER: 09-2 S5.05-9495
PHASE-1 CONTRACT NUMBER: NNX10CE24P
SUBTOPIC TITLE: Extreme Environments Technology
PROPOSAL TITLE: A Compact, Radiation Hardened, Stable, Low Power, Programmable Crystal Oscillator for Extreme Temperature and High Reliability Space Application

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Chronos Technology (Div. of FMI, Inc.)
15302 Bolsa Chica Street
Huntington Beach, CA 92649-1245
(714) 373-8100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kouros Sariri
ksariri@yahoo.com
15302 Bolsa Chica Street
Huntington Beach,  CA 92649-1245
(714) 373-8100

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Chronos Technology (Div. of FMI, Inc.) proposes to design, fabricate and deliver a conceptually proven, practical, and commercially available solution for a novel compact, radiation hardened, stable, low power, programmable crystal oscillator (RPXO), for high reliability space & extreme temperature applications. Our proposed device will be offered in a robust miniature 5x7mm industry standard surface mount package (0.24 grams only). We have engaged in the Phase I study to further refine the approach with more confidence which concludes that the proposed solution would also offer compelling features such as scalable (wide) frequency range (100KHz to 250MHz), and dual output logic compatibility (CMOS & LVDS). The compelling features of our device features include drastically improved reliability and quicker availability. The overall design of the RPXO includes a radiation hardened SiGe ASIC that operates over the extreme temperature range of -230C to +150C and holds all the necessary functions of a crystal driver circuit, synthesizer, and output buffers. The ASIC uniquely provides dual output logic compatibility (CMOS and LVDS). All aspects of radiation hardness such as TID, ELDERS and SEU have been researched and addressed in the phase 1 study. The SiGe ASIC is integrated with a high reliability and radiation hardened crystal resonator in a highly compliant yet robust miniature package.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed RPXO is intended for very demanding and high radiation missions such as Europa EJSM (JEO & JGO), Mars Sample Return, Titan, missions to comets, Juno, space station, and GPM. The compelling features and performance of the proposed RPXO makes it highly suitable for most scientific and commercial space missions that require high speed data transfer link. This device could operate during take-off, interplanetary travel, orbit entry as well as landing of the probe. RPXO can be used in processor modules, DSP, servo control, receivers, transmitters, & sensors, auxiliary memory modules, where clock signal stability (temperature, shock, vibration, etc.) and integrity (signal to noise, phase noise and phase jitter) is critical.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We have already received requirements for commercial space applications of RPXO (which we can not respond to yet) and that has further exposed the potential value of our proposition to our customers who manufacture the various instruments for NASA and other first tier space payload contractors. Sensors, controllers and communication modules are the examples of such usage. There are a number of applications for our proposed RPXO in avionics and jet engine controllers as well as other military driven system application. The jet engine market segment is a new and growing one which intends to eliminate complex, heavy and unreliable wire harnesses in the present aircrafts. Low flicker noise of SiGe HBT makes the ASIC suitable for low phase noise and low jitter applications such as instrumentation, radar, optical transceivers and high speed network applications.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Airport Infrastructure and Safety
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Control and Monitoring
RF
Instrumentation
Production
Manned-Maneuvering Units
Portable Life Support
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 S6.01-9378
PHASE-1 CONTRACT NUMBER: NNX10CC35P
SUBTOPIC TITLE: Technologies for Large-Scale Numerical Simulation
PROPOSAL TITLE: GPU-Accelerated Sparse Matrix Solvers for Large-Scale Simulations

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
EM Photonics
51 East Main Street, Suite 203
Newark, DE 19711-4685
(302) 456-9003

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Humphrey
humphrey@emphotonics.com
51 East Main St., Suite 203
Newark,  DE 19711-4685
(302) 456-9003

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
At the heart of scientific computing and numerical analysis are linear algebra solvers. In scientific computing, the focus is on the partial differential equations (PDEs) that arise from computational fluid dynamics (CFD), climate modeling, astrophysics, and structural and heat analysis that cannot be solved analytically. Certain problem formulations lead to sparse matrices, in which the majority of matrix elements are zero. Special attention is required when computing on sparse matrices in order to avoid using unrealistic amounts of memory or produce ill-performing software. Such topics have been the subject of considerable research and the limits of CPU-based performance have been reached. Recently, the graphics processing unit (GPU) has emerged as an attractive platform for high performance computing. The modern GPU boasts over 1 TFLOPS performance and as much as 6 GB onboard memory, but harnessing the power can be challenging. A library-based approach is common for HPC, with most applications using several libraries to offload well-known tasks. EM Photonics maintains a library of GPU-accelerated dense linear algebra solvers that has over 5000 users. In this project we will extend this library to include a wide range of sparse solvers, including many that have direct relevance to NASA projects.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Sparse computations arise in finite element and finite volume methods (FEM, FVM) common in the computational fluid dynamics (CFD) space, an area where NASA has many important efforts especially related to space missions and weather prediction. For example, the CFD code Overflow is widely used by NASA when designing launch and re-reentry vehicles and is used to study the air loads on the NASA space shuttles. The INS3D code is used by the space directorate to solve the incompressible Navier-Stokes equations for steady-state and time varying flow, which has been used to study the gravitational effects of blood flow in the human brain. NASA also has a vested interest in CFD-based weather prediction models. For example, the NASA Finite Volume General Circulation Model (fvGCM) and Parallel Ocean Program (POP) codes are large-scale climate prediction models important for analyzing weather effects such as global warming and hurricane predictions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Sparse solvers have applications in the entire FVM and FEM space that further expands the applicability of our project to a large number of fields involved with modeling and simulation. For instance, the models used by circuit simulation, heat transfer, and structural mechanics can all be represented by very large sparse matrices. Accelerated sparse solvers will allow engineers to more quickly turn around designs with increased detail and accuracy. Large sparse matrices commonly arise in other fields involving statistics and optimization where a large amount number of elements have various interactions. For example, electrical power systems, traffic flow optimization, economics, search index rankings, and the modeling of chemical processes are just a small sample of fields where the interaction of a large number coupled elements are represented through sparse matrices. Accelerated sparse solvers and decompositions will allow scientists to rapidly study larger problems in less time.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Computer System Architectures
Expert Systems
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 S6.02-8720
PHASE-1 CONTRACT NUMBER: NNX10CC36P
SUBTOPIC TITLE: Earth Science Applied Research and Decision Support
PROPOSAL TITLE: A Sensor Management Tool for Use with NASA World Wind

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Intelligent Automation, Inc.
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2737
(301) 294-5221

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Margaret Lyell
mlyell@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville,  MD 20855-2737
(301) 294-5223

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The number of sensors that are deployed continues to increase for scientific, commercial and intelligence related applications. Quantities of sensor data are increasingly available. NASA and NOAA are generating large quantities of sensor data involving earth, oceans and weather observations. US intelligence and commercial endeavors are also generating vast amounts of sensor data, gathered from sources ranging from satellites to vehicles. Standards have been developed that assist in making the large volume of sensor data usable. The Open Geospatial Consortium (OGC) has developed a number of specifications related to Sensor Web Enablement. OGC working groups are not only science-focused; the newest working group that is forming is an Emergency and Disaster Management Discipline Working Group (DWG). Intelligent Automation Inc (IAI) is proposing to support the data access and utilization needs of the individual researcher / scientist and the emergency incident commander through development of the Sensor Management Tool (SMT). SMT is standards-based, open source and will offer configurable views for different categories of users. In the Phase I effort IAI demonstrated feasibility and prototyped the SMT concept; this involved integration of NASA World Wind to extend SMT functionality. 'Lessons learned' provide input into our detailed plan for full-featured SMT development.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our proposed Sensor Management Tool is relevant to and can be utilize in a wide range of Earth or planetary science related endeavors. These include (1) Sensor Management Tool use in accessing and managing data for ocean studies (including Gulf of Mexico efforts), (2) Sensor Management Tool use for managing data relevant to hurricane studies, (3) Sensor Management Tool use for managing data relevant to climate and ecology studies,(4) Sensor Management Tool use for managing data from UAVs in NASA ? led technology development for western region firefighting mission efforts, (5) Sensor Management Tool for use in managing data from planetary missions (NASA World Wind earth globe would be replaced by the appropriate map), etc.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Promising Non- NASA commercial applications include: (1) Use of Sensor Management Tool with Emergency Incident Commander Views for FEMA applications, (2) Use of Sensor Management Tool for accessing, retrieving and managing data for DoD Surveillance applications, (3) Use of Sensor Management Tool regarding data related to agriculture monitoring or ecology monitoring (dept. Agriculture, various state agencies) (4) Use of Sensor Management Tool with respect to data related to infrastructure monitoring (Homeland security), (5) Use of Sensor Management Tool with respect to data related to commercial facilities monitoring, and (6) Use of Sensor Management Tool with respect to data in vehicle and fleet maintenance management, among others.

TECHNOLOGY TAXONOMY MAPPING
Human-Computer Interfaces
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 S6.03-8400
PHASE-1 CONTRACT NUMBER: NNX10RA77P
SUBTOPIC TITLE: Algorithms for Science Data Processing and Analysis
PROPOSAL TITLE: Systems and Services for Real-Time Web Access to NPP Data

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Global Science & Technology, Inc.
7855 Walker Drive, Suite 200
Greenbelt, MD 20770-3212
(240) 542-1104

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jack Kelly
jack.kelly@gst.com
7855 Walker Drive, Suite 200
Greenbelt,  MD 20770-3239
(240) 542-1104

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Global Science & Technology, Inc. (GST) proposes to build a scalable, adaptable, and interoperable information processing and delivery infrastructure that will provide near-real-time access to satellite data from the National Polar-Orbiting Environmental Satellite System (NPOESS) Preparatory Project (NPP), its follow-on the Joint Polar Satellite System (JPSS), and other near-real-time observations to modelers, forecasters, and decision-makers. Thanks to distributed Direct Broadcast facilities, a streamlined processing chain, and a scalable cloud computing environment, we propose to build technology that will reduce the latency in NPP data delivery to end-users from several hours to several minutes. Our proposed activity would serve near-real-time NPP, JPSS, and other data for the area within an antenna's satellite footprint via industry-standard Web-services, so as to maximize the use of these data by a broad set of users.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our initial target market is NASA's technical outreach to operational weather forecasters in the National Weather Service -- led by the Short-term Prediction Research and Transition (SPoRT) program. Our software may facilitate commoditizing and outsourcing the more routine data-access functions that SPoRT provides, allowing it to focus on new data streams and applications; and on more effective training and outreach to forecasters. Service-based data dissemination and scalability through cloud computing would also be useful to the new JPSS mission as a whole (especially given recent changes to the NPOESS / JPSS program), given the importance of effective, timely delivery of NPP data. To suit NASA customer needs for security or verifiability, we hope to offer the option of deploying servers in a government cloud computing environment such as NASA's Nebula, in lieu of commercial providers such as Amazon EC2. We may be also work with people in NASA or NOAA to create client software that would draw on our data services and apply them to particular user needs. We also envision applications of our technology to future NASA missions, such as DESDynI or others in the Decadal Survey or venture Class constellations; and to specialized computing needs such as those of the GSFC Scientific Visualization Studio.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We intend to reach out to a broad set of users ? from commercial shipping and delivery firms and federal, state, and local emergency services and disaster response agencies, to mass-market information services, either specialized (such as WeatherBug) or generic (such as Google Maps). We also intend to generalize our platform to support varied data sources: MODIS, NPP, and GOES data would be followed by other imagery data; by point data such as AERONET or MoPED; and by Light Detection And Ranging (LIDAR) soundings of atmospheric and surface structure, including NASA's proposed Deformation, Ecosystem Structure and Dynamics of Ice (DESDynI) mission in the longer term. This would let many different commercial, research, or government entities deploy our platform to serve their own or third-party data without needing to translate or decode complex data; or to maintain in-house server farms. Additional applications might include search and rescue operations, environmental monitoring, agriculture and forestry -- even law enforcement (e.g., working with Brazil's national remote sensing center to deter illegal logging in the Amazon).

TECHNOLOGY TAXONOMY MAPPING
Architectures and Networks
Computer System Architectures
Data Acquisition and End-to-End-Management
Database Development and Interfacing
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 S6.03-8921
PHASE-1 CONTRACT NUMBER: NNX10CD81P
SUBTOPIC TITLE: Algorithms for Science Data Processing and Analysis
PROPOSAL TITLE: Non-Linear Non Stationary Analysis of Two-Dimensional Time-Series Applied to GRACE Data

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Starodub, Inc.
3504 Littledale Road
Kensington, MD 20895-3243
(301) 929-0964

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nicolas Gagarin
nicolas.gagarin@gmail.com
3504 Littledale Road
Kensington,  MD 20895-3243
(301) 929-0964

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovative two-dimensional (2D) empirical mode decomposition (EMD) analysis was applied to NASA's Gravity Recovery and Climate Experiment (GRACE) mission database in phase I in an attempt of extracting and revealing the finest details of regional and seasonal variations. The proposed innovation is a robust and adaptive data analysis method based on a 2D adaptive isotropic decomposition approach primarily for the GRACE orbital data. The phase-I effort included a research component to optimize the prototype 2D analysis developed by Starodub. Early results using the prototype algorithms have demonstrated great potential of extracting physical cyclic components in equidistant sinusoidal grids of variations of surface density generated using spherical harmonics coefficients of GRACE. The modes associated to noise and trends were estimated and removed adaptively in 2D. In phase II, The solutions for selected NASA applications in earth sciences, space exploration, and astrophysics will be defined both at the global and regional levels: For example, the regions of Greenland, the Gulf of Alaska glacier, and Antartica will be studied for the GRACE application. The technical development will include the following areas: detection, de-noising, spectral analysis, reconstruction, and registration, and comparison of result with principal component analysis. The anticipated increases in data resolution and understanding of sources of signal noise in gravity field combined to satellite or airborne laser/radar altimetry will benefit the estimation of the Earth's gravimetry, cryosphere, hydrosphere, and ocean science.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The analysis of simultaneous and complementary observations from near-Earth orbiting satellites of the gravity field and radar or laser altimetry data can be combined for the estimation of the gravimetry, hydrosphere, and cryosphere with increased resolution and accuracy in 2-D or 3-D for a greater understanding of the Earth's system. Other potential NASA applications of the latest 2D empirical mode decomposition technologies are cosmological gravity wave and planets hunting, global primary productivity evolution map from LandSat data, non-destructive evaluation for structural health monitoring, and vibration analysis of NASA equipment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Starodub has an on-going project with FHWA on the correlation of tire-pavement interaction noise and pavement surface texture. This application will be considered as an application for the algorithm under development in the proposed project. Many Government agencies, in research, development, and operations, may benefit from this product with a reduced learning curve with the proper exposure to this technology. Since the initial collaboration between Starodub, FHWA, and Dr. Huang four years ago, FHWA has been supporting a theoretical effort at Princeton and a parallel applied research effort with Starodub. Its marketing effort to Government agencies and private entities shall be focused on illustrating the software with solutions from NASA applications output from this SBIR project and from a plethora of applications previously developed. The current list of potential non-NASA application areas includes non-destructive evaluation for structural health monitoring in highway infrastructure, vibration, speech, and acoustic signal analyses, earthquake engineering, manufacturing processes, bio-medical applications, and financial market data analysis

TECHNOLOGY TAXONOMY MAPPING
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation


PROPOSAL NUMBER: 09-2 S6.05-8885
PHASE-1 CONTRACT NUMBER: NNX10CD83P
SUBTOPIC TITLE: Software Engineering Tools for Scientific Models
PROPOSAL TITLE: Fortran Testing and Refactoring Infrastructure

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tech-X Corporation
5621 Arapahoe Avenue, Suite A
Boulder, CO 80303-1379
(303) 448-0727

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Alexander
alexanda@txcorp.com
5621 Arapahoe Ave
Boulder,  CO 80303-1379
(303) 448-7751

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Tech-X proposes to develop a comprehensive Fortran testing and refactoring infrastructure that allows developers and scientists to leverage the benefits of comprehensive Integrated Developer Environment (IDE) tools. An intriguing aspect of the infrastructure is the integration of performance measurement, unit testing, and refactoring tools with the many other features of an IDE, which will allow developers to get immediate feedback about the overall application and reduce their development cycle time. Our goal is to promote modern software engineering methodology to a broad spectrum of Fortran users. The infrastructure will facilitate refactoring newly developed and legacy codes correctly and accurately for single and multi-processor applications. Major benefits to refactoring include creating robust codes that are more easily ported to different hardware and software platforms, promoting extensibility, facilitating better collaboration, and encouraging best software engineering practices. For example, refactoring code to remove common blocks allows porting to multi-core architectures with increased thread safety. By packaging pFUnit (Fortran Unit Test Tool) into the Eclipse, combining with improved versions of Photran IDE and the Parallel Tools Platform plugins, the proposed integration we will be able to quickly contribute to the Fortran developer community, whose feedback we hope to use to guide our product development.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
While process study missions (e.g. CALIPSO/CloudSat) are critical to improve underlying climate model physics, future mission observations (e.g. CLARREO) are critical to determine the impact of those climate model improvements on the accuracy of predicting future climate change. Since the proposed tools will make it easier for NASA scientists to develop and optimize climate modeling codes, the proposed project in a sense supports all climate-related current and future missions to ensure that studies address serious accuracy issues in climate change observation and prediction. Beyond mission-related research, the proposed project has applications for all modeling efforts supported by NASA High-End Computing and the Modeling, Analysis and Prediction programs. One of our specific early adopter targets is a coupled atmosphere-ocean model called modelE developed at the NASA Goddard Institute for Space Studies (GISS). Other potential NASA applications from GISS are four mesoscale dynamics models including the Goddard Cumulus Ensemble. From Goddard Space Flight Center, the GEOS system of models could apply the proposed tools. Fortran codes in other NASA disciplines such as the CFD Codes for Turbomachinery (Glenn Research Center) are also potential applications. Related climate code targets with fringe connections to NASA include the Community Atmospheric Model and the Weather Research and Forecasting Model.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Ultimately, The Fortran testing and refactoring infrastructure can be used with all software engineering projects written in FORTAN 77, Fortran90, Fortran95 and Fortran2003. Consequently, there are a large number of non-Nasa related applications written in Fortran that could benefit from our Fortran testing and refactoring framework. The Fortran developer community at large will benefit by being able to use improved mechanisms that have been available for some time to the C and C++ communities to test and refactor Fortran codes which will result in more robust, scalable and extensible codes. More specifically, the proposing firm is fortunate to be co-located with the Climate and Global Dynamics Division (CGD) at the National Center for Atmospheric Research who is administrating the Community Earth System Model (CESM). CESM is a fully-coupled, global climate model that provides state-of-the-art computer simulations of the Earth's past, present, and future climate states supported by NSF and DOE. The firm is also leading the DOE SciDAC project, FACETS, to integrate fusion codes some of which are Fortran codes which would benefit from the proposed tools. NASTRAN variants, Computational Fluid Dynamics (CFD), combustion and geophysical data processing codes written in Fortran may benefit from our work regardless of whether they are commercial or academic ventures. We plan to work closely with the team developing the Photran Eclipse Plugin to have the broadest impact.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Software Development Environments
Software Tools for Distributed Analysis and Simulation



PROPOSAL NUMBER: 09-2 O1.01-9742
PHASE-1 CONTRACT NUMBER: NNX10CD87P
SUBTOPIC TITLE: Coding, Modulation, and Compression
PROPOSAL TITLE: Minimizing Implementation Loss in Soft-Decision GMSK Demodulators

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ORB Analytics, LLC
5 Hillside Road
Carlisle, MA 01741-1116
(978) 371-0484

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Samuel MacMullan
sam.macmullan@orbanalytics.com
5 Hillside Road
Carlisle,  MA 01741-1116
(978) 978-0484

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With more missions at high data rates demanding use of limited spectral resources, NASA's SCaN office recently coordinated a study to identify a space communications architecture to support future missions. The study recommends precoded GMSK and AR4JA LDPC codes as preferred options in most Space Network and Ground Network forward and return links and Deep Space Network return links. This modulation and coding pair provides excellent bandwidth-efficiency and greatly reduced transmitter SWaP. Unfortunately, there are no high-data-rate AR4JA LDPC devices currently available and existing GMSK receivers operate far from the performance predicted by theory, especially in the presence of severe channel and equipment impairments. Phase I provided a design of a soft-decision generating GMSK demodulator integrated with an AR4JA LDPC decoder and with estimation and compensation of a comprehensive set of severe impairments. Fixed-point simulations show performance within a small fraction of a dB of the performance with far less bandwidth-efficient modulations such as BPSK. The results of this effort show the technical and commercial viability of an integrated GMSK/AR4JA LDPC design. The proposed Phase 2 effort involves the development and delivery of a prototype transmitter and receiver to demonstrate the superior capabilities offered by this innovation and enable subsequent commercialization. A simple and highly flexible GUI system for prototype configuration and control and modular API design will allow Phase II refinement of the design and facilitate integration in future commercial products.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Future space missions at near Earth, lunar, and deep space distances that require spectral efficient communications will benefit greatly from the robustness and size, weight, and power reduction offered by the proposed GMSK and LDPC technology. Future small satellites and other miniature platforms would be able to use much more efficient power amplifiers with the given techniques, and high data rate applications such as high definition video could be more reliably supported in limited assigned frequency bands.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
GMSK is employed in fielded commercial cellular systems such as GSM and military satellite communications systems such as A-EHF SATCOM. Closely related SOQPSK and Multi-h CPM is used in UHF SATCOM and Advanced Range Telemetry (ARTM) systems. LDPC codes are used in or proposed for several commercial and DoD systems. The robust and high performance, high data rate, methods developed in this effort would offer greater capabilities and size, weight, and power reduction for each of these communications systems.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Architectures and Networks
RF
Microwave/Submillimeter
Highly-Reconfigurable


PROPOSAL NUMBER: 09-2 O1.02-8188
PHASE-1 CONTRACT NUMBER: NNX10CD88P
SUBTOPIC TITLE: Antenna Technology
PROPOSAL TITLE: Stress-Matched RF and Thermal Control Coatings for Membrane Antennas

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Surface Optics Corporation
11555 Rancho Bernardo Road
San Diego, CA 92127-1441
(858) 675-7404

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Fulton
mfulton@surfaceoptics.com
11555 Rancho Bernardo Road
San Diego,  CA 92127-1441
(858) 675-7404

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of multi-meter diameter radiofrequency (RF) antennas for NASA and DoD will have a significant impact of future space programs. Polymer membrane technologies are well suited for large area deployable space antennas by significantly reducing the mass and volume of the launch vehicle. Low CTE polymer piezoelectric membrane technology is now at a maturity level to enable the development of high performance large area electrically formal membrane reflectors. Advanced COATING technology is crucial to enabling technological developmental of high performance RF antennas. The production of a conductive and highly reflective thermal control COATING that matches the CTE of the polymer membrane is at the center of this development program. In addition, in Phase I, the piezoelectric polymeric membrane had a significant deformation at the application of the electrical potential - this manifested the need for stress balancing the coating. Specifically, the objective is to develop the thin-film stress-balanced COATING that will precisely match the CTE of the polymer to the coating material itself, resulting in a zero CTE membrane/coating composite structure. In addition, the coated membrane will exhibit the required RF performance, thermal characteristics, and environmental endurance, such as: atomic oxygen (AO) resistance; visible and ultra-violet (VUV) radiation rejection; and space temperature extremes. Surface Optics Corporation (SOC) has considerable experience in producing RF/Thermal coatings and precisely controlled intrinsic stress thin-films; both are necessary to the success of this program. NeXolve is the partnering organization with SOC, providing the polymer membranes that have the appropriate piezoelectric formulation, surface properties, and zero CTE.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications for this technology include future missions requiring RF communication. The goal of the research is to produce 94 GHz Wide Band Antennas with a surface RMS of /50. The ACE (Aerosol / Cloud / Ecosystem) mission is designed to use 94 GHz antennas and is scheduled for launch in 2017. When we demonstrate the capability to produce the ACE type of deformable membrane RF antennas, then we are on the way to the even more important application of building large area visible adaptive membrane mirrors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This program will provide a light-weight, low volume solution for large area membrane commercial RF antennas (i.e. telecommunications). In addition, DoD's future satellite needs will be well met by the technology developed in this project. As we move forward with the large area adaptive membrane antennas, applications for other, even more, demanding space optical systems will be served by this technology.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
Microwave/Submillimeter
Optical & Photonic Materials
Multifunctional/Smart Materials


PROPOSAL NUMBER: 09-2 O1.02-9839
PHASE-1 CONTRACT NUMBER: NNX10CC86P
SUBTOPIC TITLE: Antenna Technology
PROPOSAL TITLE: A Multi-Band Photonic Phased Array Antenna for High-Data Rate Communication

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Crystal Research, Inc.
48501 Warm Springs Blvd., Suite 103
Fremont, CA 94539-7750
(510) 445-0833

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Suning Tang
suningtang@eocrystal.com
48501 Warm Springs Blvd., Suite 103
Fremont,  CA 94539-7750
(510) 445-0833

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Multi-band phased array antenna (PAA) can reduce the number of antennas on shipboard platforms while offering significantly improved performance. In order to steer wideband beams, photonic beamforming techniques must be invoked so that efficient elemental vector summation in the receiving mode or in the transmit mode is independent of frequency. Crystal Research, Inc. proposes to develop a multi-band photonic antenna based on a high-speed optical true-time-delay beamformer, capable of simultaneously steering multiple independent RF beams in less than 300 ns. Such a high steering speed is 3 orders of magnitude faster than any other existing optical beamformers. Unlike other approaches, the proposed technology uses a single controlling device per operation band, which eliminates the need for massive optical switches, laser diodes and fiber Bragg gratings. More importantly, only one beamformer is needed for all antenna elements. Advantages of the proposed multi-badn photonic phased array anttena includes wideband multibeam operation, high-speed steering, microwave delay compatible, small size, light weight, low power consumption, and immune to electro-magnetic interfere. The Phase II technical goal is to extend the Phase I results into a fully functional prototype of a multi-band photonic phased array antenna, which will be delivered to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Multi-band photonic phased array antennas can be used for NASA (1) high-data rate communication and (2) remote sensing applications. Potential communications applications include: lunar and planetary exploration, landers, probes, Lunar Relay Satellites, lunar rovers, lunar habitats, lunar surface EVA, suborbital vehicles, sounding rockets, balloons, unmanned aerial vehicles (UAV's), TDRSS communication, and expendable launch vehicles (ELV's). Potential remote sensing applications include: radiometers, passive radar interferometer platforms, and synthetic aperture radar (SAR) platforms for planetary science.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed program is an important step towards the commercialization of multi-band phased array antenna for military and civilian use. There is a significant civilian market for low cost phased array antennas, particularly for mobile satellite communications applications. There is a clear market pull for versatile arrays for both military electronics and the commercial broadband wireless and satellite communications arena.

TECHNOLOGY TAXONOMY MAPPING
Laser
RF
Highly-Reconfigurable
Photonics
Optical & Photonic Materials


PROPOSAL NUMBER: 09-2 O1.03-8119
PHASE-1 CONTRACT NUMBER: NNX10CC87P
SUBTOPIC TITLE: Reconfigurable/Reprogrammable Communication Systems
PROPOSAL TITLE: Fault Tolerant Software-Defined Radio on Manycore

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MaXentric Technologies
2071 Lemoine Avenue, Suite 302
Fort Lee, NJ 07024-9212
(201) 242-9800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Ricketts
sricketts@maxentric.com
5080 Shoreham, Suite 205
San Diego,  CA 92122-5932
(858) 605-6337

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 5

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Mobile communications systems require programmable embedded platforms that can handle computationally demanding signal processing codes without the burden of high power consumption. As hardware performance improves, technology trends have shifted functionality from the gate level up to software, as demonstrated by the emergence of software defined radio. Traditionally, these platforms rely on FPGAs and DSPs, but such architectures bring with them significant software development challenges. Application demands for radiation mitigation and fault tolerance exacerbate programmability issues. Low-power general purpose processors offer improved programmability, but cannot meet performance requirements. Our solution, Resilient, provides a sweet spot with its manycore-based software defined radio. Resilient is a software defined radio for space based on rad-hard multi-core digital processing. Resilient has a number of key characteristics and capabilities. Firstly, it is based on the Maestro rad-hard multicore processor. Maestro will provide about 100 times the throughput of the current state of the art in rad-hard general purpose processors. Secondly, Resilient is a highly flexible radio, providing uninterrupted real time multimode operation, over-the-air reconfiguration and adaptability, and STRS compliance. It can also serve as a highly programmable research stage prototyping device for new waveforms and other communications technologies. Finally, Resilient can also support non-communications codes on its high performance multicore processor, co-located with the communications workload, reducing the SWaP of the overall system by aggregating processing jobs to a single board computer.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Resilient is Maxentric's radiation hardened multicore-based software defined radio. Resilient will improve the flexibility of NASA communications hardware while reducing SWaP. Maxentric is targeting NASA software radio programs such as CoNNeCT (Communication Navigation and Networking Reconfigurable Testbed), as well as space applications where flexible rad-hard computing would provide significant value such as multimode rover communications and data processing. Satellite communication is another target NASA application for Resilient. Also, Resilient can serve as a flexible research platform for NASA communications labs and research projects because of its ability to provide a fully programmable network stack from the physical layer up to the application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The applicability of Resilient is not limited to NASA markets. Military SATCOM is a primary target DoD market for Resilient. Satellite-based surveillance applications also stand to benefit from Resilient not just for communications but also to support data and image processing workloads. Aggregating communications and non-communications tasks on a single hardware component reduces SWaP and the complexity of the overall system. Commercial communications applications also are pushing for more programmability. Examples include basestations, femtocells, automotive wireless devices, and smart phones. Additionally, the rad-hard characteristics of Resilient make nuclear applications an attractive market.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Testing Requirements and Architectures
Architectures and Networks
Autonomous Control and Monitoring
RF
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Software Development Environments
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 O1.03-8382
PHASE-1 CONTRACT NUMBER: NNX10CC60P
SUBTOPIC TITLE: Reconfigurable/Reprogrammable Communication Systems
PROPOSAL TITLE: Reconfigurable VLIW Processor for Software Defined Radio

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aries Design Automation, LLC
2705 W Byron St
Chicago, IL 60618-3745
(773) 856-6633

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Miroslav Velev
miroslav.velev@aries-da.com
2705 W Byron St
Chicago,  IL 60618-3745
(773) 773-6633

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We will implement an environment for design, formal verification, compilation of code, and performance and power evaluation of Systems on a Chip (SOCs) consisting of heterogeneous processor cores that can be single-issue pipelined, superscalar, or VLIW, and are binary-code compatible with any existing Instruction Set Architecture (ISA). Particularly, we will ensure binary-code compatibility with the PowerPC 750 ISA, which is used in the radiation-hardened RAD750 flight-control computer that is utilized in many NASA space missions, including Deep Impact, the Mars Reconnaissance Orbiter, the Mars Rovers, and is planned to be used in the Crew Exploration Vehicle (CEV). The processor cores will have reconfigurable functional units and corresponding specialized instructions that can be optimized to accelerate any application. Our focus in this Phase 2 project will be on Software Defined Radio (SDR) applications. The radiation-hardening will be done at the microarchitectural level with a mechanism that will allow the detection and correction of all timing errors---caused not only by radiation, but also by variations in the voltage, frequency, manufacturing process, and aging of the chip. The binary-code compatibility of the processor cores with the PowerPC 750 ISA will allow them to seamlessly execute legacy binary code from previous space missions. We have made critical contributions to the fields of formal verification of complex pipelined microprocessors, and Boolean Satisfiability (SAT), and have developed highly efficient Electronic Design Automation (EDA) tools that we will use.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The project will result in an environment for design and formal verification of SOCs consisting of heterogeneous processor cores that are radiation-hardened, reconfigurable, and binary-code compatible with any legacy ISA. It will be possible to add new instructions that use reconfigurable functional units to accelerate specific applications, such as SDR. We have several competitive advantages: 1) we will reuse the formal definitions of the instruction semantics of the PowerPC 750 ISA that we are developing in a current NASA SBIR Phase 2 project; 2) we will apply our industrial-strength tool for design and formal verification of pipelined/superscalar/VLIW processors to prove safety, liveness, and binary-code compatibility of the processor cores with the given legacy ISA; 3) our SAT-based techniques for technology mapping of operations to reconfigurable functional units, invented on our own expenses, and up to 8 orders of magnitude faster than previous methods; 4) a tool to automatically generate a symbolic simulator and formal property checker from the formal definitions of instruction semantics of the ISA extended with new instructions, allowing the user to formally verify properties of the executables---a current NASA SBIR Phase 2 project; 5) we will combine the above tools with our GPU-based parallel SAT solver that is at least 2 orders of magnitude faster than the best publicly available solvers, and that we are developing in a current NASA SBIR Phase 2 project.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The non-NASA commercialization will target companies that would need to quickly develop processor cores and SOCs that are radiation-hardened, computationally powerful, reconfigurable, and custom-tailored to specific applications. Our competitive advantage will be due to our technology to easily design pipelined/superscalar/VLIW processors that are binary code compatible with a given ISA that has a formal definition of its semantics, and to automatically formally verify both safety and liveness of those processors. Furthermore, we will be able to provide our customers with a retargetable tool to automatically generate a symbolic simulator and formal property checker from the formal definitions of the instruction semantics of the given ISA, possibly extended with new instructions, allowing the users to formally verify properties of the executables for the new processors---we are developing this tool in a current NASA SBIR Phase 2 project. After the completion of Phase 2, the immediate customers will be the over 40 member companies of Power.org, an organization whose purpose is to develop, enable, and promote PowerPC architecture technology. We also plan to collaborate with several major companies that we have established contacts with. The reconfigurable functional units in the processor cores can be used for hardware and software obfuscation to complicate a reverse-engineering effort---of interest to companies that manufacture weapons systems.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Ultra-High Density/Low Power
On-Board Computing and Data Management
Pilot Support Systems
Architectures and Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Data Input/Output Devices
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics


PROPOSAL NUMBER: 09-2 O1.04-9344
PHASE-1 CONTRACT NUMBER: NNX10CE30P
SUBTOPIC TITLE: Miniaturized Digital EVA Radio
PROPOSAL TITLE: RF Front End Based on MEMS Components for Miniaturized Digital EVA Radio

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
AlphaSense, Inc.
470 Century Blvd.
Wilmington, DE 19808-6271
(302) 294-0116

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Xin Zhang
xin@alphasense.net
470 Century Blvd.
Wilmington,  DE 19808-2480
(302) 302-1116

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this SBIR project, AlphaSense, Inc. and the Carnegie Mellon University propose to develop a RF receiver front end based on CMOS-MEMS components for miniaturized digital EVA radio applications. In Phase I, we have proven the feasibility of implementing a compact, low power and high performance S band receiver front end based on CMOS- MEMS components. Specifically, we conducted link budget analysis to define the radio requirements for different applications, including low data rate voice, data/telemetry and high data rate, high definition video transceiving. We also identified and optimized the receiver front end architecture (i.e. a low-IF architecture), and analyzed its electrical performance based on known properties of individual CMOS- MEMS components. Finally, we fabricated two key components, a high quality factor MEMS band pass filter and a mixer-filter, and validated their performances. Phase II will be focusing on performance improvements of individual device and the whole receiver front end. We will also implement a fully integrated receiver based on the radio- on- a-chip solution, and characterize its performance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The most straightforward application of the proposed miniature MEMS based EVA radio is used by NASA for space exploration. The significantly reduced form factor and power requirements along with the increased selectivity and performance of the MEMS based EVA radio allows long duration human exploration while simultaneously increasing communication reliability and crew safety

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other than the space exploration, the proposed MEMS based EVA radio also has vast applications in the areas of wireless and mobile radio communications. For example, it can be used by first responders to enhance interoperability among police, firefighters, HazMat, homeland security and medical personnel. It can also be used by the military personnel for the soldier-centric secure communications and mode switchable on-the-fly communications. Finally, the miniature MEMS RF front end components can also find commercial applications in cell phones, pagers, Wi-Fi/Bluetooth/UWB radio integration.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Architectures and Networks
RF
Highly-Reconfigurable


PROPOSAL NUMBER: 09-2 O1.05-8381
PHASE-1 CONTRACT NUMBER: NNX10CC88P
SUBTOPIC TITLE: Transformational Communications Technology
PROPOSAL TITLE: High Fidelity Down-Conversion Source for Secure Communications using On-Demand Single Photons

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ADVR, Inc.
2310 University Way, Building 1-1
Bozeman, MT 59715-6504
(406) 522-0388

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tony Roberts
roberts@advr-inc.com
2310 University Way, Building #1-1
Bozeman,  MT 59715-6504
(406) 522-0388

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this NASA SBIR Phase II effort, AdvR will design and build an efficient, fully integrated, waveguide based, source of spectrally uncorrelated photon pairs that will enable accelerated research and development in the emerging field of quantum information science. The key innovation is the use of sub-micron periodically poled waveguides to produce counter propagating photon pairs using quasi-phase matched downconversion. This novel device will provide a high brightness source of downconversion pairs with enhanced spectral properties, low attenuation, and operation in the visible to the mid-infrared spectral region.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A waveguide based source of spectrally and spatially pure heralded photons will contribute to a wide range of NASA's advanced technology development efforts including on-demand single photon sources for high rate, spaced-based secure communications e.g. quantum key distribution, quantum metrology for precision space based navigation, quantum computation, and space-based entanglement distribution that can contribute to fundamental tests of quantum mechanical principals over large distances and probe the relationship between quantum and gravitational theories. In addition heralded single photon sources will be useful for the characterization, optimization, and calibration of detectors designed for photon starved operation and used in laser-based long distance communications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The immediate application of paired photon generation is as a tool for accelerating research and development in quantum communications and computation as well as a source for characterizing and optimization of detectors used for low light level detection. Additionally, the Federal Vision for Quantum Information Science (QIS) published by the National Science and Technology Council states that "QIS promises to have important implications not only for national security but also for future economic competitiveness in areas ranging from wholly new and innovative technologies to improvements in global positioning systems and everyday concerns like healthcare." High purity heralded single photon and entangled photon states will also propel promising research efforts such as linear optical quantum computing, generation of optical Schrodinger cat states, and teleportation-based quantum repeaters for quantum key distribution over unlimited distance.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical


PROPOSAL NUMBER: 09-2 O1.06-8122
PHASE-1 CONTRACT NUMBER: NNX10CD89P
SUBTOPIC TITLE: Long Range Optical Telecommunications
PROPOSAL TITLE: High Power Uplink Amplifier for Deep Space Communications

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optical Engines, Inc.
5412 S IL Route 31, Suite 5
Crystal Lake, CO 60012-3793
(815) 301-5922

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Donald Sipes
don.sipes@opticalenginesinc.com
842 S. Sierra Madre St STE D
Colorado Springs,  CO 80903-4100
(815) 815-8303

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Critical to the success of delivering on the promise of deep space optical communications is the creation of a stable and reliable high power multichannel optical uplink/beacon. Optical Engines proposes to deliver in phase 2 2 compact and low cost fiber amplifiers suited to the uplink application. This will be accomplished through the use of Optical Engines proprietary Multi-Fiber Coupled 2.5kW laser diode stacks, its Etched Taper All Fiber Combiner Technology and a custom designed Photonic Crystal Fiber. One of these amplifiers will be of the Coiled PCF type and one of the Rod type and will be integrated into existing NASA deep space communications up link infrastructure.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High Power Fiber amplifiers that are compact, robust, reliable and low cost can provide the basis of many potential NASA applications from Uplink beacons that are either terrestrial, airborne or space based, and also can provide the basis of high power lasers for Lidar, LIBS, and other remote sensing applications. This technology is also extend able to pulsed regimens and different wavelenghts as well

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High Power fiber lasers represent the fastest growing segment of the over $2B per year material processing market. A kW class fiber laser that is considerably smaller, and much lower cost will be a successful competitor in this market and will have a very good chance of gaining market share. The proposed fiber laser technology is extend able to the eyesafe portion of the spectrum allowing further penetration into these portions of the laser processing market. Laser processing is a small portion of the over $30B per year material processing market that can be further penetrated as the cost of these systems is reduced and flexibility of these systems is increased

TECHNOLOGY TAXONOMY MAPPING
Tethers
Laser
Optical
High-Energy
Photonics
Optical & Photonic Materials
Wireless Distribution


PROPOSAL NUMBER: 09-2 O1.06-8219
PHASE-1 CONTRACT NUMBER: NNX10CD90P
SUBTOPIC TITLE: Long Range Optical Telecommunications
PROPOSAL TITLE: High Performance Negative Feedback Near Infrared Single Photon Counting Detectors & Arrays

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Amplification Technologies, Inc.
1400 Coney Island Avenue
Brooklyn, NY 11230-4120
(718) 951-8021

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yuriy Yevtukhov
yevtukhov@amplificationtechnologies.com
1400 Coney Island Avenue
Brooklyn,  NY 11230-4120
(718) 951-8021

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 7

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Amplification Technologies Inc ("ATI") proposes to develop the enabling material and device technology for the design of ultra low noise, high gain and high speed near-infrared single photon counting photodetectors and arrays sensitive in the 1000 nm to 1600 nm spectral region for long range space communication applications, based on the already proven mechanism of internal discrete amplification technology in InGaAs/InP material system. We plan to achieve this by using the concept of internal discrete amplification mechanism in the InP material system that gave state of the art performance parameters in the 1000 to 1600nm wavelength range and the developed device design as part of the Phase I program that shows higher detection efficiency and lower jitter performance. The primary accomplishments from the Phase II effort would be the development of ultra low noise (low jitter), high detection efficiency, very high gain and high speed near-infrared photodetectors and arrays sensitive in the 1000 nm to1600 nm spectral region. The technology of internal discrete amplification enables the combination of high speed, very high gain and ultra low noise because the internal discrete amplification nullifies the effect of impact ionization coefficients and prevents the edge break down, with high detection efficiency and high speed of operation. These photodetectors might also be used in missile seekers, battlefield target identification and recognition systems, and eye-safe LADAR. Potential civilian applications include fiber-optic telecommunications, remote sensing and laser spectroscopy.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is working on the development of optical communication technologies for such important applications as long range space to ground communication links, intersatellite links, Earth orbiting to ground, networking formation flying spacecraft, and several others. All of these applications currently lack an adequate detector that would fully meet application requirements. The proposed detector has the potential to become the detector of choice for these applications and to enable the fulfillment of stated NASA mission goals of increasing data transfer rates by a factor of 10-100 compared to the currently used RF techniques. The new capabilities enabled by the detector could significantly expand the use of optical communication solutions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Military applications could also make use of high speed, sensitive photodetectors operating at 1.06 m or 1.5 m wavelengths. There are also additional potential applications such as LIDAR remote sensing at these wavelengths.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Biomolecular Sensors
Laser
Instrumentation
Biochemical
Microwave/Submillimeter
Optical
High-Energy
Photonics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 O1.06-9687
PHASE-1 CONTRACT NUMBER: NNX10CD91P
SUBTOPIC TITLE: Long Range Optical Telecommunications
PROPOSAL TITLE: NFAD Arrays for Single Photon Optical Communications at 1.5 um

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Princeton Lightwave, Inc.
2555 Route 130 South, Suite 1
Cranbury, NJ 08512-3509
(609) 495-2600

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Itzler
mitzler@princetonlightwave.com
2555 Route 130 South, Suite 1
Cranbury,  NJ 08512-3509
(609) 495-2551

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For this program, we propose to develop large pixel-count single photon counting detector arrays suitable for deployment in spacecraft terminal receivers supporting long-range laser communication systems at 1.5 um. To surmount the present obstacles to higher photon counting rate -- as well as the complexity of back-end circuitry required -- in using conventional single photon avalanche diodes (SPADs), we will leverage initial success in monolithically integrating "negative feedback" elements with state-of-the-art SPADs to beneficially modify the device avalanche dynamics. This approach can achieve extremely consistent passive quenching, and appropriate implementations can lead to rather small avalanches (e.g., ~10^4 ? 10^5 carriers), for which reduced carrier trapping provides lower afterpulsing that will no longer limit the photon counting rate. When correctly implemented, this "negative feedback" avalanche diode (NFAD) design is also extremely simple to operate: with just a fixed dc bias voltage, the NFAD will autonomously execute the entire arm, avalanche, quench, and re-arm cycle and generate an output pulse every time an avalanche event is induced. During Phase 1 of this program, we characterized 5 different discrete NFAD designs to identify specific pixel-level design opportunities for reducing afterpulsing and timing jitter. We also fabricated and characterized wafer-level test structures that show excellent feedback element yield and uniformity sufficient for large-format NFAD arrays. These proofs-of-feasibility from Phase 1 position us to demonstrate space-qualifiable large pixel-count 128 x 128 NFAD arrays during a Phase 2 effort. This effort will also include the development of appropriate test platforms for NFAD array packaging and characterization.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are two primary NASA applications for the negative feedback avalanche diode (NFADs) arrays to be developed during this proposed SBIR program. First, free space optical (laser) communications over interplanetary distances epitomizes photon-starved applications, and viable spacecraft receiver technologies should have high-performance single photon detection to enable coding schemes such as pulse position modulation while imposing minimal size, weight, and power requirements. The need for simultaneous pointing and tracking is a driver for array-based detector solutions. Second, active remote sensing optical instruments require higher performance photon detectors to improve the performance of existing direct detection lidar systems used to perform atmospheric measurements (e.g., aerosol backscattering) and surface mapping (e.g., ice sheets and forest canopy density).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are a number of potential non-NASA commercial applications that will benefit from the development of NFAD arrays. Range-finding and ladar applications present many commercial opportunities (e.g., terrain/vegetation mapping, flood/landslide risk mapping, civil engineering projects, etc.) in which the availability of single photon sensitivity could be a disruptive improvement over existing optical remote sensing technologies. Just as NASA is pursuing free space optical links, commercial FSO systems will be able to leverage capabilities realized from the development of NFAD arrays for photon-starved free space links, particularly in cases for which pointing and tracking are required, such as in satellite communications. As with NASA remote sensing applications, there are commercial applications for NFADs in various types of lidar systems for measuring atmospheric properties such as wind and weather patterns, air pollution, and general trace gas analysis. Finally, high-performance photon counting capability in the near- and shortwave-infrared is desirable for the detection of low light output fluorescence, photoluminescence and photoemission processes, particularly for biomedical applications.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Laser
Optical
Photonics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 O1.07-9345
PHASE-1 CONTRACT NUMBER: NNX10CD93P
SUBTOPIC TITLE: Long Range Space RF Telecommunications
PROPOSAL TITLE: Nano-Particle Scandate Cathode for Space Communications Phase 2

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
E-Beam, Inc.
21070 SW Tile Flat Road
Beaverton, OR 97007-8739
(503) 628-0703

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bernard Vancil
bernie@ebeaminc.com
21070 SW Tile Flat Road
Beaverton,  OR 97007-8739
(503) 503-0703

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose an improved cathode based on our novel theory of the role of scandium oxide in enhancing emission in tungsten-impregnated cathodes. Recent results have demonstrated the efficacy of nano-particle scandium oxide, but a detailed theory on the mechanism of operation has been lacking. Our theory explains published data and points to an optimized cathode, which we propose here to build and test. The cathode is the performance-limiting component in high-frequency linear beam amplifiers such as traveling wave tubes and klystrons. The required bandwidth, data rate, number of channels, frequency, and output power are going up. The performance of linear beam amplifiers is acutely limited by current cathode performance. Scandate cathodes offer a way to increase top emission from 10 A/cm2 to at least 50 A/cm2. Phase I proved the feasibility of applying layers on unagglomerated scandium oxide on impregnated cathodes. Phase II will optimize, test, and commercialize the process.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Data transmission and power levels from NASA space probes are inadequate. Fast transmission of high-resolution images during fly-bys is curcial to mission success. Also, upcoming Mars missions require faster data transmission. The time scales of these mission extend into years, even tens of years. The life-limiting component in space is the cathode in a traveling wave tube. The proposed scandate cathode will extend the life, and increase bandwidth and power.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The long life (estimated 100,000 hours) of this cathode will lower system acquisition and maintenance costs in satellites and space probes, as well as terrestrial communications and radars. Higher emission current density will permit higher frequencies, more bandwidth, and more power than current art. There is a shortage in bandwidth and channels in many wireless networks. The scandate cathode provides a way out.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Electrostatic Thrusters
RF
Data Input/Output Devices
Radiation-Hard/Resistant Electronics
Ceramics
Composites
Metallics
Optical & Photonic Materials
Wireless Distribution


PROPOSAL NUMBER: 09-2 O1.07-9857
PHASE-1 CONTRACT NUMBER: NNX10CD94P
SUBTOPIC TITLE: Long Range Space RF Telecommunications
PROPOSAL TITLE: GaN Bulk Growth and Epitaxy from Ca-Ga-N Solutions

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The IIIAN Company, LLC
2700 East 28th Street, Suite 120
Minneapolis, MN 55406-1575
(612) 226-1249

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jody Klaassen
jklaassen@alum.mit.edu
2700 East 28th Street, Suite 120
Minneapolis,  MN 55406-1575
(612) 612-1249

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovations proposed here are Ka-band (38 GHz) group III-nitride power FETs and the dislocation density reducing epitaxial growth methods (LPE) needed for their optimal performance and reliability. Ka-band power transistors with >60% Power Added Efficiency (PAE) are not commercially available. The primary limitations to their manufacture are lack of mature process technology at major GaN foundries for sib-100nm lithography necessary for gate definition, and the difficulty of obtaining low dislocation density GaN templates in a suitable wafer size format (3-inch SiC and 6-inch Si) for mass production. Demonstration of Ka-band operation in the group III-nitrides has, to date, been primarily the realm of academic research labs. IIIAN's proposal bridges the gap between commercially available nitride foundry capabilities and pure research by utilizing proven process technology at RFMD for processes not requiring deep, submicron lithography and utilizing state-of-the-art nanofabrication technology available at the University of Minnesota's NanoFabrication Center.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work is in direct response to the call in subtopic O1.07 in the 2009 NASA SBIR solicitation for "High-efficiency (> 60%) Solid-State Power Amplifiers (SSPAs), of both medium output power (10 W-50 W) and high-output power (150 W-1 KW), using power combining techniques and/or wide band-gap semiconductor devices at X-band (8.4 GHz) and Ka-band (26 GHz, 32 GHz and 38GHz)" and "Epitaxial GaN films with threading dislocations less than 106 per cm2 for use in space qualified wide band-gap semiconductor devices at X- and Ka-band." These calls for technical advancement are in turn directly related to high data rate communications with future NASA missions to the moon, to Mars, and to the outer solar system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Group III-nitride semiconductor technology for discrete transistors and MMICs has a wide range of applications for cell phones, wireless infrastructure (base stations), switching power supplies, and in high performance military electronics. Most of these applications are related to power amplification, but group III-nitrides having much higher breakdown voltages than other compound semiconductors like GaAs or InP also offer significant advantages for toughened, low noise receivers. Low dislocation density GaN films are also a necessity for long-lived blue and UV semiconductor lasers, and a more robust and cost efficient GaN template technology will directly impact the viability of solid state lighting.

TECHNOLOGY TAXONOMY MAPPING
RF
Radiation-Hard/Resistant Electronics
Semi-Conductors/Solid State Device Materials


PROPOSAL NUMBER: 09-2 O2.02-8697
PHASE-1 CONTRACT NUMBER: NNX10CF36P
SUBTOPIC TITLE: Ground Test Facility Technologies
PROPOSAL TITLE: Energy-Based Acoustic Measurement System for Rocket Noise

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Blue Ridge Research and Consulting
13 1/2 W. Walnut Street
Asheville, NC 28801-8102
(828) 252-2209

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael James
Michael.James@BlueRidgeResearch.com
13 1/2 W. Walnut Street
Asheville,  NC 28801-8102
(828) 252-2209

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 7
End: 8

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Accurate estimates of the vibroacoustic loading placed on space vehicles and payloads during launch require knowledge of the rocket noise source properties. Given the extreme nature of acoustic environments near the plume, data sufficient to characterize the noise source region have been difficult to acquire. Without these data, structures may be designed to handle insufficient or excessive vibroacoustic loads, resulting in either an overbuilt structure (and extra weight), or an under-designed vibration isolation system that could result in damaged cargos. Current energy-based acoustic probe designs have limited frequency bandwidth due to physical limitations. A new set of probe designs is proposed that incorporate both a new physical probe design but also a more advanced signal processing methodology that will significantly increase the usable frequency bandwidth of the probes while reducing the manufacturing and maintenance costs of the probes. The probe system will also include the design of a complete data acquisition system capable of recording data under the harsh conditions present in typical rocket motor test firings.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The initial target market for the energy-based probe and data analysis tool is a core community of potential users interested in near-field rocket noise. The primary users are NASA facilities: Stennis Space Center, Marshall Space Flight Center, and Kennedy Space Center, who all perform rocket (static or lift-off) noise measurements for community noise, on vehicle loads, and/or support structure loads assessments. Our proposed system will provide a better understanding of the acoustic near-field with acoustical energy-based measures as opposed to simple pressure and intensity measures. This tool will provide a superior technical advantage over other measurements based on the ability of acoustical energy-based probes to characterize rocket noise. Once this capability is demonstrated and proved during Phase II, we fully expect energy-based measurement to be the most accurate method to characterize near-field rocket noise and as such, that NASA will require it for their noise measurement programs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Like NASA, the Air Force Space Division (AFSD) and the Aerospace Corporation perform noise measurements for community noise, on vehicle loads, and/or support structure loads assessments in support of military satellite programs, as do large rocket engine manufacturers including ATK Launch Systems (Morton-Thiokol) and UTC's Rocketdyne. Private space launch vehicle companies such as Orbital Systems Corporation, United Space Alliance, and Space Exploration Technologies are poised for growth. All of these companies will benefit from the improved technology that the energy-based probe presents. In addition, Jet engine manufacturers including Rolls-Royce (with its outdoor test facility at Stennis Space Center), UTC Pratt & Whitney, and GE Aviation perform jet engine source-noise characterization. Helicopter manufacturers Boeing, Bell, and UTC Sikorsky, as well as heavy machinery manufacturers (e.g. Caterpillar, Komatsu, John Deere) are another potential user group. As system development occurs during Phase II, alternative applications will be explored to expand the customer base.

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
Autonomous Control and Monitoring
Data Acquisition and End-to-End-Management
Portable Data Acquisition or Analysis Tools


PROPOSAL NUMBER: 09-2 O3.01-8967
PHASE-1 CONTRACT NUMBER: NNX10CC92P
SUBTOPIC TITLE: Human Interface Systems and Technologies
PROPOSAL TITLE: Tactile Data Entry System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2559
(434) 973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Adams
adams@bainet.com
1410 Sachem Place, SUite 202
Charlottesville,  VI 22901-2559
(434) 973-1215

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Building on our successful Phase I Tactile Data Entry program, Barron Associates proposes development of a Glove-Enabled Computer Operations (GECO) system to permit suited crewmembers to perform virtual keyboard/mouse interactions using an instrumented EVA glove. The Phase II system will use two-hand motion tracking, multi-finger gesture recognition, and vibrotactile feedback to create an intuitive human-computer interface that mirrors familiar desktop data entry modalities. The program will deliver demonstration hardware and software compatible with laboratory, field, and on-orbit testing of crewmember performance in relevant data entry tasks. The prototype will include functional EVA gloves with integrated motion sensing and vibrotactile transducers that couple to existing NASA suits via a quick-connect fitting. We will produce right and left hand gloves, lower arm suit sections, and a specialized two-port acrylic glove box to enable human subject evaluations in a realistic pressurized environment. Initial trials at Barron Associates will permit refinement of design concepts, followed by more extensive usability, comfort, and durability testing at NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Minutes during EVA operations, whether in an orbital or planetary setting, are among the most challenging, and expensive, spent by humans. In these task-saturated, dynamic environments, it is essential that data entry interfaces to computing and networking resources are flexible, easy to use, and efficient. To this end, the GECO system strives to replicate the familiar capabilities of standard desktop interfaces using the gloves on the crewmember's hands as controls. The technology promises to open the door to an expansive set of information system-enabled applications, including surface navigation, document editing, communications, and telerobotic control. Our vision for the tactile data entry system extends, well beyond Phase II, to integration into next-generation NASA EVA suit designs. We intend to make a compelling case for this new technology by demonstrating the benefits of the proposed system for increasing performance and user satisfaction.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to future NASA support, Barron Associates will aggressively pursue private-sector application of technology derived from the tactile data entry system. The enhanced data processing, communications, navigation, and situational awareness capabilities enabled by the GECO system also have the potential to be critical enablers for non-NASA missions. Of particular interest are applications involving individuals or small units operating in hazardous, information-rich environments. Examples include deep sea construction/repair, firefighting, explosive ordinance disposal, hazardous material handling, and military aviation.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Data Input/Output Devices
Human-Computer Interfaces
Suits


PROPOSAL NUMBER: 09-2 O3.02-9623
PHASE-1 CONTRACT NUMBER: NNX10CE56P
SUBTOPIC TITLE: Vehicle Integration and Ground Processing
PROPOSAL TITLE: Polymer-Reinforced, Nonbrittle, Lightweight Cryogenic Insulation for Reduced Life-Cycle Costs

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Innosense, LLC
2531 West 237th Street, Suite 127
Torrance, CA 90505-5245
(310) 530-2011

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Hess
david.hess-1@innosense.us
2531 West 237th Street, Suite 127
Torrance,  CA 90505-5245
(310) 310-2011

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase II SBIR project focuses to continue developing cryogenic insulation foams that are flexible, deforming under compression. InnoSense LLC (ISL) demonstrated enhanced structural and insulation properties in Phase I to establish NASA use potential. In particular, ISL demonstrated a 30% increase in thermal shielding properties over baseline polyurethane foams. These foams were easily formed into a variety of shapes resisting high impact loads without damage. The coated foams were extremely hydrophobic showing excellent resistance to moisture. These materials insulated liquid nitrogen temperatures with one inch of insulation thickness. Upon fine tuning the foam formulations in Phase II, cryogenic insulation performance will be tested at liquid hydrogen and liquid oxygen temperatures. ISL has teamed with a large NASA prime contractor for computer modeling and performance validation during Phase II. For assuring success, ISL has committed $100K of co-funding during Phase II, and secured $300K as Phase III Follow-on funding from a commercialization partner. A technical and business team is now in place for successful execution of the project. At project end, we expect to achieve a TRL Level of at least 6 from 3 in the beginning.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Current NASA spacecrafts are fueled by liquid hydrogen and oxygen. To complete NASA missions cost-effectively, it is necessary to conserve these fuels by limiting cryogenic fuel boil-off. Current insulations absorb water while at the launch pad, thus increasing the overall liftoff load by up to 1000 lbs. NASA would greatly benefit from an advanced cryogenic insulation system that would reduce fuel boil-off and atmospheric water absorption. Such insulation would reduce liftoff weight by not only limiting water uptake, but also by reducing the necessary insulation thickness to maintain liquid fuel. Applications for such a material would include rocket fuel systems, terrestrial launch pad fuel transport lines, and orbital depot systems. This insulation could also be expanded for use in advance technology research including superconductors and advanced energy systems. Currently ground and launch operations account for 45 ? 60% of total costs. The outcome of this project will greatly reduce these costs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Efficient and affordable insulation is very attractive for a wide range of consumer applications ranging from pipeline insulation to advanced technology research. Currently aerogel-lined fabrics are used for extreme temperature insulation in clothing and other building materials. ISL's technology introduces a lightweight, inexpensive, and moldable foam insulation that can be customized to a variety of shapes and flexibilities. The immediate market for the foam lies in the Aerospace industry. ISL's foam technology has the potential to insulate advanced aircraft fuel tanks while providing a flame-resistant layer. Currently, new and exciting products are implementing aerogel technology that ISL is utilizing.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Launch and Flight Vehicle
Simulation Modeling Environment
Testing Facilities
Spaceport Infrastructure and Safety
Cooling
Reuseable
Thermal Insulating Materials
Modular Interconnects
Structural Modeling and Tools
Tankage
Airport Infrastructure and Safety
Fluid Storage and Handling
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Composites
Radiation Shielding Materials
Multifunctional/Smart Materials
Superconductors and Magnetic
Combustion
Liquid-Liquid Interfaces


PROPOSAL NUMBER: 09-2 O3.03-9290
PHASE-1 CONTRACT NUMBER: NNX10CC94P
SUBTOPIC TITLE: Enabling Research for ISS
PROPOSAL TITLE: Observation Platform for Dynamic Biomedical and Biotechnology Experiments using the ISS Light Microscopy Module

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Techshot, Inc.
7200 Highway 150
Greenville, IN 47124-9515
(812) 923-9591

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Todd
ptodd@techshot.com
7200 Highway 150
Greenville,  IN 47124-9515
(812) 923-9591

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of the research is the completion of an observation platform for the ISS Light Microscopy Module (LMM) as it currently resides on the U.S. Fluids Integration Rack (FIR). In its current configuration the LMM accommodates a Contained Bubble Experiment, and it has no substage illuminator and limited epi-illumination. There is a need for future use of the LMM in more versatile fluids and biological experiments. A modular observation platform consisting of an electronics module and the first two of an eventual suite of experiment modules is proposed. A life science experiment module that allows investigators to load up to two different fluids and combine them in a hollow glass slide under the LMM objective lenses has been designed and built. It is suitable for the imaging, enumeration and evaluation of biological cells in suspension or attached to the glass surface of the hollow slide for on-orbit, real-time image cytometry. Fluids can be changed to initiate a process, fix biological samples or retrieve suspended cells. The colloid science experiment module will be designed for conduct of certain microparticle and nanoparticle experiments for investigation of the colloid self-assembly (CSA) phenomenon, among others. The colloid science module is being developed in response to the high level of interest in such a facility. It includes a hollow glass slide and heating elements for the creation of a thermal gradient from one end of the slide to the other. The life science and colloid science experiment modules mount atop the electronics module in the position on the LMM where the stage would be. The electronics module that contains a diffuse illuminator, power supplies for two piezo pumps, controller boards for pumps, valves and illuminator The electronics module is designed to receive power and control signals from the FIR/LMM system. The same electronics module will support the life science and colloid science experiment modules.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Targeted application(s) of the proposed innovation and associated products and services relative to NASA needs (infusion into NASA mission needs and projects) consist of on-orbit analysis of cultured cells from biotechnology experiments aboard ISS, cultivation and analysis of microbial samples aboard ISS, examination of crew members' blood samples, real-time observation of cell growth and differentiation, physical self-assembly and crystallization experiments. Heavy use is anticipated by researchers supported by the National Institutes of Health ISS utilization project, which is expected to fund some 10 investigations beginning in 2009, 2010 and 2011. Techshot is one of a few companies functioning as a regular Implementation Partner in the latter program, and opportunities exist to serve customers using the LMM Dynamic Stage. There are two potential business models for doing this: Utilize hardware via NASA that has already been delivered to NASA by Techshot, or to custom-build space qualified derivatives of the hardware. The NASA Human Research Program (HRP) is expected to be a significant customer, given that on-orbit blood analysis opportunities are expected to be scarce. As these opportunities develop there will be a need for placement of the Observation Platforms in investigators' laboratories. For their benefit Techshot will also provide a LMM controller simulation package.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Techshot regularly serves the commercial sector in its ground-based projects in which prototype products are developed for potential manufacturers. Techshot will continue to explore the market potential and if significant could pursue the path discussed in the remainder of this section. A company that was organized in Indiana in 2005, IKOTECH, is selling medical and scientific devices to help diagnose and treat certain types of cancer and enable a cure for type I (juvenile) diabetes through innovative magnetic cell separation and analysis technologies developed by and licensed from Techshot, Ohio State University and the Cleveland Clinic. The Dynamic microscope could fit into the IKOTECH product pipeline. More importantly IKOTECH is expected to be well-positioned to license the technology from Techshot at the end of the development period. Techshot will make this product known to the various components of the commercial space flight community: Zero-g, Bigelow Aerospace, sub-orbital firms such as Virgin Galactic and Masten Aerospace. For this market Techshot will develop its own video microscope stand based on its own Cell Tracking Velocimeter platform (a commercial derivative of NASA-sponsored ground-based "Dynascope"), which includes high-speed image processing and analysis as well as HD image recording.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biophysical Utilization
Liquid-Liquid Interfaces


PROPOSAL NUMBER: 09-2 O4.02-8458
PHASE-1 CONTRACT NUMBER: NNX10CD44P
SUBTOPIC TITLE: On-Orbit PNT (Positioning, Navigation, and Timing) Sensors and Components
PROPOSAL TITLE: Multi-Purpose Radio Signal Generation System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Emergent Space Technologies, Inc.
6301 Ivy Lane, Suite 720
Greenbelt, MD 20770-6333
(301) 345-1535

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kenn Gold
kenn.gold@emergentspace.com
7150 Campus Drive, Suite 245
Colorado Springs,  CO 80920-6503
(720) 841-6331

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Early Hardware-in-the-Loop (HWIL) simulation is essential to early retirement of space mission development risks. Upcoming NASA missions such as MMS involve complex high Earth orbits making the use of GPS difficult, though NASA has developed GPS receivers capable of performing in these environments. Space GPS simulation needs are typically seen as a niche market, and the resulting solutions, which are often simply adaptations of terrestrial products, can be sub-optimal and at best handle simple, low dynamic LEO missions. Further, space simulation solutions are frequently inflexible and cannot be modified by the end-user. Given the broad but unique needs of HWIL testing involving RF systems, Emergent proposes to develop the Multi-purpose Radio Signal Generation (MRSiG) system to address these needs, which are essential to early risk mitigation. The MRSiG system will provide for easy mission specific customization and generation of multiple waveforms used in ground testing applications and will return the expertise to simulate these complex environments to NASA. MRSiG will accomplish this difficult task by harnessing the latest in open Software Defined Radio (SDR) technologies. Simulation complexity for RF signal generation is moved into software, enabling the emulation of many RF waveforms/protocols including, but not limited to GPS, 802.11, S-Band, WiMAX, etc.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MRSiG will be able to replace many of the expensive, highly specialized RF signal generators with cheaper generic boxes that can be customized as the technologies are updated. MRSiG boxes can be utilized throughout the entire RF hardware development cycle, from the breadboard to the flight stages. Their relatively low cost point will allow more simulators in the labs, and less resource contention for developing projects. The portability of the MRSiG allows testing outside the lab, including environmental test chambers and during spacecraft integration. In particular, MRSiG could be utilized as a GPS simulator, replacing the Spirent GPS signal generators currently in use. As the Constellation program continues to ramp up, these boxes could be utilized to simulate anything from lunar ground communication, ground-lunar relay communication, and even lunar to Earth communications. MRSiG could potentially be instrumental in performing formation flying or rendezvous and docking simulations if RF data is exchanged.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
GOES-R is the first unclassified mission that will use GPS at HEO. If the GPS tracking proves successful in that orbit, this opens a whole new regime for GPS tracking, and the current commercial GPS simulators on the market can not adequately address these orbits. The potential applications outside of NASA mirror those inside, but on a much larger scale. Laboratories and universities would have ready access to a low-cost simulation capability that can be customized for their needs. For example, GPS simulation equipment currently tagged at $250,000 could be replaced with MRSiG and a SDR receiver for less than 1/10 the price, opening the door to smaller institutions while encouraging development and innovation. Similar arguments can be made for the modeling of spacecraft communications systems, TDRSS modeling, or most wireless communication systems.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Facilities
Guidance, Navigation, and Control
RF


PROPOSAL NUMBER: 09-2 O4.02-9182
PHASE-1 CONTRACT NUMBER: NNX10CD45P
SUBTOPIC TITLE: On-Orbit PNT (Positioning, Navigation, and Timing) Sensors and Components
PROPOSAL TITLE: X-ray Detection and Processing Models for Spacecraft Navigation and Timing

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microcosm, Inc.
4940 W. 147th Street
Hawthorne, CA 90250-6708
(310) 219-2700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Graven
pgraven@smad.com
4940 w. 147th Street
Hawthorne,  CA 90250-6708
(310) 219-2700

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In Phase II, XNAV performance will be enhanced through the development of single photon processing algorithms, which utilize all available photon time data to improve the accuracy of XNAV. A detailed model of the XNAV system, including single photon techniques will be implemented in Orbit Determination Toolbox (ODTBX), increasing its functionality and providing a valuable mission design tool. ODTBX will be further refined by enhancements to detector and source models, including addition of new pulsars as their properties are better determined (including low flux sources). Time transfer and barycenter correction effects will be added. XNAV measurement types will include additional absolute range measurement types and range rate measurements. Functions developed for ODTBX will provide support for XNAV and XTIM studies including: enhanced dynamic functions and linearized process models for inclusion of clock and other bias states; and performance prediction for the single photon processing approaches. The team will work with NRL, JHU/APL, and NASA GSFC, focusing on sources and detectors to develop improved models, and assessing timing accuracy. This work will further validate the utility of XNAV for NASA, and develop and test relevant new technology to provide a rapid path to full flight software development should opportunity arise.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
XNAV is a game changing technology for NASA, enabling new missions, providing navigation autonomy and redundancy and offering a path to reduce the scheduling demands on DSN, a valuable NASA asset. There are several promising NASA applications for XNAV where the improvements in navigational accuracy will either enable new missions, or reduce their costs, including missions to the outer planets, and non-planetary missions to deep space. Missions to Mars and the moon can take advantage of the autonomous navigation capabilities of XNAV, providing redundancy and reducing the need for regular DSN contacts, lessening the burden on this over-taxed system, XNAV can supplement DSN and enhance DSN navigation performance by making complementary measurements and can provide higher redundancy for manned missions. It can provide a common, universally available, independent time reference with accuracy comparable to an atomic clock as well, for any mission, from Earth orbit to deep space.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary non-NASA XNAV applications would be to provide primary or secondary navigation services for DoD missions. For MEO, GEO, HEO, and even cis-lunar missions, where GPS has limited availability, XNAV can provide primary autonomous navigation capability. In addition, XNAV could provide an essential backup navigation capability for missions that normally rely on GPS, but have a need for continuity of operations in the event of loss or denial of GPS. These applications were being actively studied through DARPA's first XNAV program in 2004-06, and key Microcosm team members had strong ties to that program.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Autonomous Control and Monitoring


PROPOSAL NUMBER: 09-2 O4.03-9337
PHASE-1 CONTRACT NUMBER: NNX10CC95P
SUBTOPIC TITLE: Lunar Surface Navigation
PROPOSAL TITLE: Advanced Bayesian Methods for Lunar Surface Navigation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Autonomous Exploration, Inc.
385 High Plain Road
Andover, MA 01810-3234
(978) 683-0290

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Julian Center
jcenter@ieee.org
385 High Plain Road
Andover,  MA 01810-3234
(978) 269-4120

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation of this project is the application of advanced Bayesian methods to integrate real-time dense stereo vision and high-speed optical flow with an Inertial Measurement Unit (IMU) to produce a highly accurate planetary rover navigation system. The software developed in this project leverages current computing technology to implement advanced Visual Odometry (VO) methods that will accurately track much faster rover movements. Our fully Bayesian approach to VO will utilizes information from the images than previous methods are capable of using. Our Bayesian VO does not explicitly select features to track. Instead it implicitly determines what can be learned from each image pixel and weights the information accordingly. This means that our approach can work with images that have no distinct corners, which can be a significant advantage with low contrast images from permanently shadowed areas. We have shown that the error characteristics of the visual processing are complementary to the error characteristics of a low-cost IMU. Therefore, the combination of the two can provide highly accurate navigation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Visual Odometry (VO) has played a key role in Mars exploration with the Spirit and Opportunity Mars Exploration Rovers (MERs). However, limitations in onboard computing power severely limit the speed of movement that can be tracked by MERS VO, requiring an order of magnitude reduction in forward progress in area where VO was required. The software developed in this project will leverage current computing technology to implement advanced VO methods that will accurately track much faster rover movements. This will greatly increase exploration productivity. This improvement will become even more significant when exploring the more distant planetary bodies. This project will also investigate whether combining vision with a low-cost, lightweight, low-power Micro-ElectroMechanical System (MEMS) Inertial Measurement Unit (IMU) can produce acceptable accuracy for lunar and planetary exploration. If so, this will facilitate the design of lower-cost, light-weight rovers, which will make it feasible to launch a team of rovers for wide area exploration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There will be many potential terrestrial applications for a Bayesian VO system. Although GPS-IMU systems can work well in open outdoor settings, GPS is degraded or unavailable in indoor settings or in outdoor areas with significant tree cover. A navigation system combining a GPS and an IMU with Bayesian VO could provide continuous operation in all environments. The success of this project should lay the groundwork for low-cost, low-power, light-weight integrated navigation systems for robots and autonomous vehicles operating in a wide range of environments. One potential market for this technology is the Department of Defense (DoD). Congress has given DoD a mandate that by 2020 30% of ground vehicles should be robotic. An accurate, low-cost VO system should allow many of these vehicles to be semi-autonomous, enabling only supervisory control for many missions.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Intelligence
Perception/Sensing
Autonomous Control and Monitoring


PROPOSAL NUMBER: 09-2 O4.04-8246
PHASE-1 CONTRACT NUMBER: NNX10CE34P
SUBTOPIC TITLE: Flight Dynamics Technologies and Software
PROPOSAL TITLE: Advanced Filtering Techniques Applied to Spaceflight

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
IST-Rolla
11560 Forest Lake Drive
Rolla, MO 65401-7305
(673) 201-1068

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Searcy
jsearcy@istrolla.com
710 University Drive, Suite 200
Rolla,  MO 65401-2109
(502) 655-1952

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 2
End: 3

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
IST-Rolla developed two nonlinear filters for spacecraft orbit determination during the Phase I contract. The theta-D filter and the cost based filter, CBF, were developed and used in various orbit determination scenarios. The scenarios were application to low Earth orbit, range only, and range and range rate estimation. The modified state observer was also developed to estimate uncertainty in the dynamic model besides estimation of orbital states. Phase I research showed that there is a problem with the linear-like form that is used by many nonlinear filters such as the State Dependant Riccati Equation filter (SDRE filter), and the theta-D and CBF. A study of the observability led to important discoveries about the lack of observabilty in some formulations. Detailed study of the working of the proposed nonlinear filters in terms of observability and their application to more precise orbit determination and model uncertainty estimation will be undertaken in Phase II. Also learned from Phase I, IST-Rolla will focus more on how and where these nonlinear filters can help NASA. There will be three main applications studied during Phase II: interplanetary orbit determination, space debris tracking, and interplanetary landing spacecraft tracking. These applications were chosen because of their relevance to current NASA missions and the nonlinearity of the measurements involved should show the need for the nonlinear filters. Furthermore, working algorithms and software will be given to NASA to test on ongoing applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The algorithms provided by IST-Rolla, the theta-D, CBF and neural network estimator, will be set up so that the end user can provide the current estimate and the measurements, then the filter will adjust to those measurements and provide an estimate. This will be packaged into a C code, and an attempt will be made to create a filtering toolbox for MATLAB as well. These steps will allow the end user to apply and adapt these filters and with the analysis provided by IST-Rolla in Phase I and Phase II, the user will know exactly what to expect from the algorithms. The accuracy and efficiency will be a valuable asset to NASA's repertoire of orbit determination technologies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Most of the applications for NASA apply here as well. Once packaged, these algorithms will provide a powerful tool to spacecraft designers and will be easy to implement and test. IST-Rolla strives to make all commercial products as user friendly, and applicable in as many cases as possible. Furthermore, these set of algorithms along with the EKF, the unscented Kalman filter will be made into a tool box that can be sold to educational organizations for teaching courses on estimation and orbit determination as well as companies like aerospace, automotive industry for use in design.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control


PROPOSAL NUMBER: 09-2 O4.04-8416
PHASE-1 CONTRACT NUMBER: NNX10CD47P
SUBTOPIC TITLE: Flight Dynamics Technologies and Software
PROPOSAL TITLE: Continuation Methods and Non-Linear/Non-Gaussian Estimation for Flight Dynamics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Numerica Corporation
4850 Hahns Peak Drive, Suite 200
Loveland, CO 80538-6010
(970) 461-2000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Randy Paffenroth
randy.paffenroth@numerica.us
4850 Hahns Peak Drive, Suite 200
Loveland,  CO 80538-6003
(970) 461-2000

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose herein to augment current NASA spaceflight dynamics programs with algorithms and software from three domains. First, we use parameter continuation methods to assist in computation of trajectories in complicated dynamical situations. Numerical parameter continuation methods have been used extensively to compute a menagerie of structures in dynamical systems including fixed points, periodic orbits, simple bifurcations and invariant manifolds. Perhaps more important for the current work, such methods have already proven their worth in flight dynamics problems, especially those having to do with the complicated dynamics near libration points. Second, we propose to use Continuous Mechanics and Optimal Control (CMOC). Algorithms based the CMOC formalism promises to support optimal trajectory design using both discrete and continuous control. Third, we propose to use advanced filtering techniques and representations of probability density functions to appropriately compute and manage the uncertainty in the trajectories. While advanced methods for understanding and leveraging the underlying dynamics are clearly necessary for effective mission design, planning, and analysis, we contend that they do not suffice. In particular, they do not, in and of themselves, address the issue of uncertainty. Herein we discuss methods that balance the accuracy of the uncertainty representation against computational tractability.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are several current state-of-the-art software packages that are clear and direct transition paths for the proposed work. In particular, there are the GPS-Enhanced Onboard Navigation Software (GEONS), the GPS-Inferred Positioning System and Orbit Analysis Software (GIPSY), and the General Mission Analysis Tool (GMAT). Of the various packages, GMAT is the most directly applicable and will be the focus of the Phase I effort. Accordingly, these algorithms will find applicability in any pre-flight mission design, planning, and analysis activities that utilize the aforementioned software packages. One domain of particular note in space craft missions is the neighborhood of libration points, where the underlying dynamics are rather complicated and the dynamics effect on uncertainty is important. Another domain that we see of prime importance is that of spacecraft formation flying where, again, the dynamics and the uncertainty play a key role.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The satellite market is large and growing. For example, analysis firm Forecast International is projecting worldwide deliveries of about 262 geostationary or medium-Earth orbit commercial communications satellites by 2019. This implies a strong market for the technology described in this proposal. In particular, as space becomes more crowded with commercial and government spacecraft, and space debris, the robust calculation of trajectories along with accurate estimates of uncertainty can only become more important. The global space and satellite market is expected to reach $158 Billion by 2010. This market involves numerous government agencies and permeates many parts of both the U.S. Military and commercial entities. In particular, large players in this market include Boeing, TerreStar, and Northrop Grumman. The algorithms and software proposed herein will find applicability to many challenging problems for DoD and commercial entities where complicated dynamics and uncertainty play a role.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control


PROPOSAL NUMBER: 09-2 O4.04-9179
PHASE-1 CONTRACT NUMBER: NNX10CD48P
SUBTOPIC TITLE: Flight Dynamics Technologies and Software
PROPOSAL TITLE: Deep Space Navigation and Timing Architecture and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microcosm, Inc.
4940 W. 147th Street
Hawthorne, CA 90250-6708
(310) 219-2700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Graven
pgraven@smad.com
4940 W. 147th Street
Hawthorne,  CA 90250-6708
(310) 219-2700

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Microcosm team will complete the simulation tool architecture early in Phase II, and in parallel begin to develop the simulation. The tool is architected for carrying out performance analysis and rapid trade study assessments of competing navigation/timing architecture options for future NASA missions, incorporating state-of-the art radiometric, x-ray pulsar, and laser communications measurements, among others, in the Orbit Determination Toolbox (ODTBX) environment. The solution centers on inclusion of a navigation layer as part of the communications architecture and on the maintenance and propagation of navigation states, time and associated uncertainties onboard each platform with filtering capabilities enabling updates based on any available measurements. Such measurements include: direct state and uncertainty updates via ground communication, radiometric- and lasercom-based range and range rate data from communication with ground stations and other spacecraft, time transfer from ground stations and other spacecraft, X-ray pulsar-based navigation and time measurements (XNAV), and others as they become available. This would be game-changing for spacecraft autonomy ?enabling platforms to operate using onboard state information rather than relying almost entirely on ground based tracking and activity scheduling. Additionally, architectures that include long-range intersatellite communication (e.g. relay spacecraft) can provide favorable geometries for significantly improved 3D precision navigation solar-system-wide.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed navigation and timing architecture simulation capability will provide a tool to support performance evaluation of SCaN architecture concepts in addition to enabling mission planning for human exploration, robotic and infrastructure missions integrating into a future SCaN architecture. Incorporating these new capabilities, including X-ray pulsar-based navigation/timing, lasercom-based navigation, and time distribution into ODTBX, and creating interfaces with other existing analysis and performance assessment tools, will provide enhanced navigation and timing solutions for next-generation space missions from low Earth orbit to the outer solar system. Microcosm envisions several approaches to commercialization to NASA customers and programs: ? Basic capabilities delivered via updates to open-source ODTBX ? Contracts to support SCaN architecture evaluation/analysis ? Contracts to support relevant mission engineering activities ? Contracts to support integration of tool capabilities with NASA/contractor legacy tools ? Contracts to support navigation analysis and associated flight software development for NASA programs

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A key non-NASA application would be to provide primary or secondary navigation and timing services for DoD missions. The software modules developed for navigation and timing solutions for NASA can be easily transitioned to DoD space systems. The overall navigation and timing architecture concept developed for NASA systems can be adapted to DoD space systems in a straightforward manner. Additionally, commercial systems which may derive benefits from application of non-traditional spacecraft navigation techniques such as XNAV and LNAV, as primary or backup capabilities, may become future customers of the software capabilities developed in the proposed program as well as potential users of the NASA infrastructure. In each case there are a variety of modalities for Microcosm to support from consulting in support of missions/programs to software implementation and integration support.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Autonomous Control and Monitoring


PROPOSAL NUMBER: 09-2 O4.04-9465
PHASE-1 CONTRACT NUMBER: NNX10CC97P
SUBTOPIC TITLE: Flight Dynamics Technologies and Software
PROPOSAL TITLE: Desensitized Optimal Filtering and Sensor Fusion Tool Kit

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Analytical Mechanics Associates, Inc.
303 Butler Farm Road, Suite 104A
Hampton, VA 23666-1568
(757) 865-0000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christopher Karlgaard
karlgaard@ama-inc.com
303 Butler Farm Road, Suite 104A
Hampton,  VA 23666-1568
(757) 865-0000

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Research on desensitized optimal filtering techniques and a navigation and sensor fusion tool kit using advanced filtering techniques is proposed. Research focuses on reducing the sensitivity of Kalman filters with respect to model parameter uncertainties using a robust trajectory optimization approach called Desensitized Optimal Control, developed by the proposing company. The proposed tool kit implements the research results as well as recent advances in robust and/or adaptive generalized Kalman and Sigma-Point filters for non-Gaussian problems with uncertain error statistics. The proposed research and development brings new filtering and sensor fusion techniques to NASA and industry in a convenient package which can be used as a stand-alone toolbox, either for ground support or for onboard applications. Its modular structure enables it to be readily integrated with other tools, and thus enhances the existing fleet of applications. The desensitized optimal filtering research and the feasibility study on components of the proposed tool kit will be carried out concurrently. The tool kit is a generic stand-alone application, and has a modularized structure which facilitates easy integration with existing tools. A suite of sensor models and noise distributions as well as Monte-Carlo analysis capability are included to enable statistical performance evaluations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Expected NASA applications are in the areas of spacecraft and aircraft navigation analyses. The intended modular nature of the tool kit allows for a wide variety of applications, including ground or onboard facilities to process navigational data from multiple sensor sources, and analysis and testing of flight software and onboard data processing algorithms. Existing NASA software packages such as GPS-Enhanced Onboard Navigation Software (GEONS) may benefit from these advanced filtering techniques by interchanging the native navigation processor with one chosen from the proposed tool kit.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool kit has applications in a wide range of industries besides NASA, including aerospace engineering, mechanical engineering, electrical engineering, atmospheric data assimilation and economic modeling, etc., where sensors are commonly used to collect a large quantity of raw data which need to be processed with filtering techniques. Specific examples of non-NASA applications may include marine vessel navigation, commercial airliner navigation, seismic data acquisition and analysis, atmospheric observation data collection and processing, and so on. The fact that the tool kit is built in a generic environment makes it readily applicable to any of these areas. Existing tools can also be enhanced by incorporating the advanced filtering modules provided in the proposed tool kit.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
On-Board Computing and Data Management


PROPOSAL NUMBER: 09-2 O4.05-9401
PHASE-1 CONTRACT NUMBER: NNX10CD49P
SUBTOPIC TITLE: Space-Based Range Technologies
PROPOSAL TITLE: A Light Weight, Mini Inertial Measurement System for Position and Attitude Estimation on Dynamic Platforms

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Impact Technologies, LLC
200 Canal View Blvd.
Rochester, NY 14623-2893
(585) 424-1990

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Liang Tang
liang.tang@impact-tek.com
200 Canal View Blvd
Rochester,  NY 14623-2893
(585) 424-1990

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 3
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Impact Technologies, LLC in collaboration with the Rochester Institute of Technology, proposes to develop and demonstrate a flight-worthy hardware prototype of a miniature, low cost/weight/ power device that provides stable and highly accurate near continuous positioning, attitude, and inertial measurements while being subjected to highly dynamic maneuvers and high vibration effects. In contrast to conventional methods that utilize either unreliable magnetic field sensors or extensive ground-based real-time tracking and control units that are expensive, large and power-consuming to operate, our innovative design focuses on identifying the gravitational vector onboard in real-time to bound sensor drift errors to achieve high degree of accuracy. The objective is achieved by a unique design that combines a dual-arc low-cost accelerometer array with three-axis rate gyros and GPS. Advanced filtering techniques such as the Unscented Kalman Filter are proposed to estimate sensor bias and drift effects. High vibration effects are estimated and eliminated by subtracting the imposed loading from the accelerometer measurements to provide a highly robust system in the presence of highly dynamical and vibrational conditions. Testing of the prototype system includes shaker table laboratory and hardware-in-the-loop tests along with an optional relevant vehicle platform test with support from NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The successful completion of the proposed work will lead to improvements in the safe operations of commercial and general aviation (GA) aircraft and address the goals of the NASA Space Communication and Navigation Office. The proposed technologies with an emphasis on real-time attitude estimation through the use of a coupled accelerometer array and GPS unit will be directly applicable to Reusable Launch Vehicles, low cost attitude determination on low dynamics sub-orbital carriers, inertial measurement estimation in non-GPS friendly environments and space-based range applications. It will lead to benefits in the form of improved reliability, accuracy, and sustainability of safety-critical aerospace systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The potential commercial use of the developed technologies is extensive. Examples of key application areas that could benefit through use of the developed technologies include: underwater vehicle navigation, Tx/Rx Antenna steering, UAV Auto Pilot, the guidance/control of precise munitions, and numerous unmanned missions involving operations in subterranean, remote, unknown and hostile enclosed environments such as natural cave networks, underground and underwater tunnel networks, building floors, and spaces within a collapsed building rubble field.

TECHNOLOGY TAXONOMY MAPPING
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Autonomous Control and Monitoring
Gravitational