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NASA 2012 SBIR Select Phase II Solicitation


PROPOSAL NUMBER:12-2 E2.01-8514
PHASE-1 CONTRACT NUMBER:NNX13CL49C
SUBTOPIC TITLE: Air Traffic Management Research and Development
PROPOSAL TITLE: METROSIM: Metroplex-Wide Flight Planning and Optimization

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: 4
End: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation of this effort is the development of a Metroplex-based arrival, departure, and surface optimization system which we call MetroSim. Linking with both the NASA-developed Traffic Management Advisor (TMA) tool, the NASA-developed System Oriented Runway Management (SORM) tool, the FAA-proposed Terminal Flight Data Management (TFDM) system, or alternatively with live or recorded flight data, MetroSim allows airport planners, traffic flow management experts, airline dispatchers, air traffic controllers, and pilots to reduce the uncertainty in operations planning, recover quickly from disruptive events, maintain high throughput even in adverse weather conditions, and handle the uncertainties associated with irregular operations. Not only are we proposing innovations that improve Metroplex flight management, but we are also proposing innovations in the way aviation software is structured. In order to manage the high volume of flights in the New York airspace effectively, and simultaneously improve the arrival stream, departure stream, and surface operations, the MetroSim architecture contains a collection of different tools, some of which are analytic computations, some of which are physics-based computations, and some of which are mathematical optimization calculations, interoperating in a distributed computational environment. Finally, the architecture allows Metrosim to be adapted to any Metroplex.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed solution has application in every Metroplex in the National Airspace System. The way Metrosim is designed, it can be adapted to any Metroplex. Metrosim can be a decision support tool for controllers, advising them on the best routes, best departure and arrival sequence for each airport, and best pushback time and taxi route to the assigned runway. It can be used inside a human-in-the-loop simulation, as a "pseudo controller" to provide pilots with guidance. Finally, airline dispatchers can use the tool to aid them in route planning, to clue them on what routes and taxi paths are likely to be assigned by controllers long before a flight departs or (for arrivals) enters the Metroplex

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Metrosim can be used as a research tool for NASA aviation researchers. By experimenting with different algorithms for the Metroplex Planner or the Airport Planner, or even by providing Metrosim with a different route structure or different traffix mix, a NASA researcher can explore many areas. Some of these areas are (1) the effect of a different route structure on the Metroplex performance; (2) the introduction of new vehicle types, such as UAS aircraft, on Metroplex performance; (3) the effect of a different traffic mix or traffic intensity on Metrosim metrics.

TECHNOLOGY TAXONOMY MAPPING
Air Transportation & Safety
Analytical Methods
Software Tools (Analysis, Design)
Simulation & Modeling


PROPOSAL NUMBER:12-2 E1.01-8239
PHASE-1 CONTRACT NUMBER:NNX13CC12C
SUBTOPIC TITLE: High Power Electric Propulsion Systems
PROPOSAL TITLE: 300C/15 kW power converter with AlGaN/GaN-Si MOS-HFETs for electric propulsion systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
GeneSiC Semiconductor Inc.
43670 Trade Center Place, Suite 155
Dulles, VA 20166-2123
(703) 996-8200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Siddarth Sundaresan
siddarth.sundaresan@genesicsemi.com
43670 Trade Center Place, Suite 155
Dulles,  VA 20166-2123
(703) 996-8200

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Capitalizing on a strong expertise in III-Nitride epitaxy, GaN-Si power device designs, and wide-bandgap power electronics, researchers at GeneSiC Semiconductor propose a SBIR program focused on the development of 15 kW/300C-rated power converters using AlGaN/GaN-Si MOS-HFETs and Schottky rectifiers. The proposed AlGaN/GaN-Si power converters to be developed in this program will usher in a new generation of high-efficiency, low-cost, and radiation-hard power conversion units on-board future NASA spacecraft. Phase I of this proposed work focussed on the optimization of the design and fabrication of the AlGaN/GaN-Si MOS-HFET and NSJ SBR devices. Phase II will be focused on the design and integration of Si/GaN gate-drive circuitry with the power SBRs and transistors to create high-power integrated circuits. Another major objective during Phase II will be the construction of Rad-Hard packaging for the power ICs. At the end of Phase II of this program, a fully-functional 15 kW/300C rated power converter IC equipped with AlGaN/GaN-on-Si MOS-HFETs, Natural SuperJunction (NSJ) SBRs as free-wheeling diodes and on-chip SiC or III-Nitride gate drive circuitry will be demonstrated at a switching frequency of ≥ 1 MHz and at a temperature of ≥ 300C. As compared to the existing state-of-the-art power electronics technology, the proposed AlGaN/GaN-on-Si power converters will offer (A) Lower on-state losses, 300C operation and 1 MHz switching capability (B) A Lateral device architecture, which is highly desirable for construction for monolithic power integrated circuits (C) Possibility of hybrid interconnection of III-Nitride Power Devices with on-chip Rad-Hard AlGaN/GaN Gate Drive Circuitry (D) Desirable Normally-OFF Power Switches

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The specifications of the power switch to be developed in this program are ideally suited for most Air Force PMAD applications. This includes propulsion system externals like actuators, pumps, and starters, weapons ejection, fuel transfer, lighting, avionics, RADAR, landing gears & breaks, steering, powered doors and ramps, gun drives, anti-icing, environmental control and auxiliary emergency power systems. The realization of a high power density switchmode power supplies and DC-DC conversion circuits will benefit Army's Future Combat System (FCS) by offering it an important part of the subsystem. An electric and hybrid vehicle technology directly affects the M113 APC, Bradley infantry fighting vehicle, HMMWV, 5-ton M939A1 truck, AAAV, 50-ft personnel boat and a more electric aircraft by making them highly deployable, sustainable, survivable, lethal and affordable. An integrated electric power system made using GaN high power devices will increase component placement flexibility within vehicles, double fuel economy by continuously operating smaller engines under optimum conditions, and reduce armor protected volume. Commercial switchmode power supplies will also benefit from the development of such components. Such power supplies are used in computer power supplies, cellular phone base station power supplies, consumer electronics, lighting applications, and robotic and motor control applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology developed here is fundamental to a wide range of NASA PMAD and motor control applications. Drive and control electronics for motors in the next generation robotic systems such as rovers have to be directly placed on the motor housing. Integration of 300C capable power electronics with the motor enables creation of distributed actuator systems with significantly reduced interconnects and wiring. The motor sensing electronics consists of a position sensor, digitizer, digital controller and digital to analog converter. For DC-DC converters, power ICs developed in this program connects power sources in a wide variety of NASA mission systems with power sources as Solar arrays, Brayton rotating unit, stirling radioscopes, and fuel cells with various loads like electric propulsion, communications systems, instruments and actuators. A power IC is also the building block for the interface between energy storage devices like batteries and flywheels with the energy sources and loads. Switchmode power supplies improved by high frequency, high temperature power switch is critical for NASA synthetic aperture RADAR's (SAR) antenna array T/R modules. T/R modules typically operate in a pulsed mode, drawing current pulses from a power supply on a periodic basis determined by the operation of the overall RADAR system. The ripple in the output voltage of the T/R module power supply impacts the performance of the RADAR system.

TECHNOLOGY TAXONOMY MAPPING
Navigation & Guidance
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Robotics (see also Control & Monitoring; Sensors)
Amplifiers/Repeaters/Translators
Power Combiners/Splitters
Transmitters/Receivers
Process Monitoring & Control
Telemetry/Tracking (Cooperative/Noncooperative; see also Planetary Navigation, Tracking, & Telemetry)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Manufacturing Methods
Materials (Insulator, Semiconductor, Substrate)
Conversion
Distribution/Management
Storage
Models & Simulations (see also Testing & Evaluation)
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)
Polymers
Actuators & Motors
Machines/Mechanical Subsystems
Electromagnetic


PROPOSAL NUMBER:12-2 E1.01-9072
PHASE-1 CONTRACT NUMBER:NNX13CC16C
SUBTOPIC TITLE: High Power Electric Propulsion Systems
PROPOSAL TITLE: Hall Effect Thruster for High Power Solar Electric Propulsion Technology Demonstration

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Busek Company, Inc.
11 Tech Circle
Natick, MA 01760-1023
(508) 655-5565

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vlad Hruby
vhruby@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: 6

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In Phase I Busek matured the design of an existing 15-kW laboratory thruster. Magnetic modeling was performed to generate a circuit incorporating magnetic shielding. Erosion modeling predicts extremely long lifetime and high throughput. A detailed mechanical design of the thruster resulted in an overall assembly with specific mass <3kg/kW. Modal, dynamic and thermal analyses were performed to calculate resonance frequencies, mode shapes, stress and fatigue values and temperature limits. Experiments using the existing laboratory thruster evaluated a modified anode/gas distributor and a B-field distribution representative of the proposed magnetic shielded configuration. Performance results suggest similar efficiency and performance as the baseline thruster. Visual observation of the plume illustrated the characteristics of magnetic shielding were achieved. In Phase II Busek will complete the detailed design of the thruster and a center mounted hollow cathode. A prototype unit will be fabricated and performance tested included limited duration testing at Busek. Depending on facility availability the thruster will independently tested at GRC. Busek will hold a MRR and CDR then fabricate, assemble, and fully test a qualification model thruster/cathode to raise the maturity to TRL 6. The thruster will be delivered to NASA for extended duration testing to complete the qualification.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A 15kW thruster with throttle ability to 5kW has applications on DoD and commercial ComSats. Hall thrusters could enhance many high power DoD and commercial missions such as satellite servicing, orbit maintenance, orbit raising and lowering, inclination changes, and repositioning. The system could also find near term application on an all-electric upper stage derived from Busek's ESPA orbit maneuvering system (OMS), a free flying S/C based on the ESPA ring. The high power (30kW) version would be used for transportation of propellant to a LaGrange positioned fuel depot.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA has identified 30kW-class SEP systems as a high-value intermediate step towards higher power systems due to broad cross-cutting capability. Current NASA investments include advanced next-generation solar arrays and higher power electric propulsion technologies to enable 30kW-class SEP. The ESPA ring is one approach being considered for partner-based mission concepts and those capable of being launched as secondary payloads. In addition NASA is investing in EP development of 15kW class HET system using either direct-drive and/or high voltage power processing unit. The possibility for using Hall thrusters for lunar and Mars missions has also been well investigated.

TECHNOLOGY TAXONOMY MAPPING
Models & Simulations (see also Testing & Evaluation)
Ceramics
Fuels/Propellants
Maneuvering/Stationkeeping/Attitude Control Devices
Spacecraft Main Engine
Simulation & Modeling
Passive Systems


PROPOSAL NUMBER:12-2 E1.02-8486
PHASE-1 CONTRACT NUMBER:NNX13CK02C
SUBTOPIC TITLE: Nano/Micro Satellite Launch Vehicle Technology
PROPOSAL TITLE: Platform Independent Launch Vehicle Avionics with GPS Metric Tracking

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tyvak Nano-Satellite Systems LLC
15265 Alton Parkway, Suite 200
Irvine, CA 92618-2606
(480) 227-1113

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Austin Williams
Austin@tyvak.com
15265 Alton Parkway, Suite 200
Irvine,  CA 92618-2606
(480) 227-1113

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For this award, Tyvak proposes to develop a complete suite of avionics for a Nano-Launch Vehicle (NLV) based on the architecture determinations performed during Phase I. This system will address the unique avionics challenges of a dedicated small launch vehicle and will utilize heritage and lessons learned from Tyvak's CubeSat avionics systems, modifying and optimizing its existing products for use with this new class of launch vehicles. The major technical objectives are: - Provide broad compatibility with all known NLV systems in development - Determine and provide appropriate performance and reliability metrics while maintaining the low-cost/low-mass approach made possible by commercial electronic systems - Implement the latest network protocols with support for wireless systems in the NLV environment - Develop a GPS metric tracking system and perform requirement verification to meet range safety recommendations - Demonstrate the reliability of low-cost/low-mass/low-power/redundant automatic flight termination system (AFTS) by combining the latest generation of commercial miniature GPS systems with high performance computer systems currently used by Tyvak - Validate functionality and performance for the entire NLV avionics suite through a series of incremental tests, from vibration and thermal vacuum, through a stratospheric balloon flight, an inert test article flight, to final demonstration on a NLV proxy.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Currently there are over 100 CubeSat developers worldwide building CubeSats, which comprise of government agencies, commercial businesses, non-profits, universities, and high schools. The U.S. Army currently has a program called Soldier-Warfighter Operationally Responsive Deployer for Space (SWORDS) and DARPA has a program called Airborne Launch Assist Space Access (ALASA), which both aim to increase the technology readiness level of nano-satellite and small-satellite class launch vehicles. In addition, there are multiple commercial businesses that require reliable sources for nanosat launch. The technology developed under this NASA SBIR would have direct tangible benefits to both U.S. Government and commercial programs alike. In addition to the specific launch vehicle applications, Tyvak has also been exploring additional areas of commercialization where low-mass, high-integration, flexibility, and reliability are paramount. The unmanned vehicles industry is a natural target for additional applications, and using the avionics suite in ground, aerial, surface and underwater vehicles would modernize UAV capabilities in the same way Tyvak is modernizing small-satellite and Launch Vehicle platforms. Additionally, this avionics package could be used for other upcoming space applications like small interplanetary landers (e.g. for the Google Lunar X-Prize), where mass and reliability play a very important part.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The interest in CubeSats and nanosats from both a spacecraft/payload and launch perspective has grown dramatically over the last decade. NASA has played a significant role in fostering the growth of the CubeSat community. Despite the growing interest in CubeSat and NanoSat missions, launch opportunities for this class of spacecraft is only available as secondary payloads. NASA and other government agencies have recently expressed interest in the development of small launch vehicles specifically designed to carry NanoSats as primary payloads. The NEXT program is a clear example of NASA commercial applications. Generation Orbit Launch Services recently won this award, with Tyvak and Ventions as sub-contractors, to deliver a NLV launch opportunity in 2016 to demonstrate their GO-2 dedicated launch vehicle for nano-satellites.

TECHNOLOGY TAXONOMY MAPPING
Avionics (see also Control and Monitoring)
Navigation & Guidance
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Space Transportation & Safety
Autonomous Control (see also Control & Monitoring)
Robotics (see also Control & Monitoring; Sensors)
Antennas
Architecture/Framework/Protocols
Network Integration
Transmitters/Receivers
Algorithms/Control Software & Systems (see also Autonomous Systems)
Attitude Determination & Control
Command & Control
Condition Monitoring (see also Sensors)
Process Monitoring & Control
Sequencing & Scheduling
Telemetry/Tracking (Cooperative/Noncooperative; see also Planetary Navigation, Tracking, & Telemetry)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Models & Simulations (see also Testing & Evaluation)
Prototyping
Computer System Architectures
Data Acquisition (see also Sensors)
Microelectromechanical Systems (MEMS) and smaller
Vehicles (see also Autonomous Systems)
GPS/Radiometric (see also Sensors)
Inertial (see also Sensors)
Ranging/Tracking
Telemetry (see also Control & Monitoring)
Positioning (Attitude Determination, Location X-Y-Z)
Sensor Nodes & Webs (see also Communications, Networking & Signal Transport)
Operating Systems
Hardware-in-the-Loop Testing
Simulation & Modeling


PROPOSAL NUMBER:12-2 E1.02-9215
PHASE-1 CONTRACT NUMBER:NNX13CK05C
SUBTOPIC TITLE: Nano/Micro Satellite Launch Vehicle Technology
PROPOSAL TITLE: A high performance, electric pump-fed LOX / RP propulsion system

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: 4

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 that builds on previously-demonstrated technologies (under DARPA and NASA sponsored efforts) to design, fabricate and hot-fire test a pump-fed, 3,000lbf LOX/RP propulsion system.

POTENTIAL NASA COMMERCIAL 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. Four specific applications that Ventions has already received customer level support from are: 1. Prototype upper stage for DARPA's XS-1 program; 2. DARPA's next generation rocket engine exploring feasibility of modular rocket approaches such as aero-spike engines; 3. DARPA's ALASA program; and 4. Lunar lander propulsion for a commercial customer.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A high-performance, pump-fed LOX / RP propulsion system can be expected to have several NASA applications including nano-sat launch, lunar ascent / descent (precursors, rovers, cargo, man-rated vehicles, etc.), planetary missions (ascent vehicles for payload and sample placement into orbit, sample return, etc.), and Near-Earth-Object (NEO) missions (sample return). Three specific applications that Ventions has already received customer level support from are: 1. 1st stage booster for LSP's NEXT launch vehicle; 2. Outer planet orbit capture / insertion for missions such as Europa and Uranus orbiters; and 3. Planetary ascent applications in the Mars Ascent Vehicle.

TECHNOLOGY TAXONOMY MAPPING
Launch Engine/Booster
Spacecraft Main Engine


PROPOSAL NUMBER:12-2 E1.03-8501
PHASE-1 CONTRACT NUMBER:NNX13CA49C
SUBTOPIC TITLE: International Space Station Utilization
PROPOSAL TITLE: Zero G Mass Measurement Device (ZGMMD)

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 Richter
richterr@orbitec.com
1212 Fourier Drive, Ste 400
Madison,  WI 53717-1961
(608) 229-2726

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Zero Gravity Mass Measurement Device (ZGMMD) provides the ability to measure the mass of samples in a microgravity environment, like that found on the International Space Station (ISS). One of the primary measurements often taken during science experiments is mass. This is even more relevant in biology, where mass is often one of the key measurements taken for analysis. During the Phase I effort, a ZGMMD prototype was developed, tested, and demonstrated the feasibility of a means to determine the mass of samples less than 1kg, without the use of earth's gravity. The ZGMMD's innovative way of determining the mass, of low mass objects, in microgravity environments has been shown to be feasible, and effective. The Phase I prototype has shown to be able to provide great mass measurement capabilities, exceeding the Phase I requirements, specifically in accuracy and precision.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ZGMMD also has the potential for uses in other Non NASA applications, for commercial companies involved with providing space research platforms, like Bigelow Aerospace, Virgin Galactic, Sierra Nevada, Blue Origins, Boeing, SpaceX, and Orbital Sciences. ZGMMD may prove valuable in not only orbital situations, but perhaps even in sub-orbital flights in which mass may be valuable to collect under those conditions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ZGMMD has an immediate application for NASA aboard the ISS. It could be utilized right away with a number of fundamental space biology experiments that are either in progress, or will be starting soon. The ZGMMD offers a very desirable capability often utilized in most lab settings for mice, plants, and

TECHNOLOGY TAXONOMY MAPPING
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Autonomous Control (see also Control & Monitoring)
Robotics (see also Control & Monitoring; Sensors)
Health Monitoring & Sensing (see also Sensors)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Actuators & Motors
Machines/Mechanical Subsystems
Biological (see also Biological Health/Life Support)
Inertial
Biophysical Utilization


PROPOSAL NUMBER:12-2 E3.01-9470
PHASE-1 CONTRACT NUMBER:NNX13CL08C
SUBTOPIC TITLE: Laser Transmitters and Receivers for Targeted Earth Science Measurements
PROPOSAL TITLE: Solid State Transmitters for Water Vapor and Ozone DIAL Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Fibertek, Inc.
13605 Dulles Technology Drive
Herndon, VA 20171-4603
(703) 471-7671

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ti Chuang
tchuang@fibertek.com
13605 Dulles Technology Dr.
Herndon,  VA 20171-4603
(703) 471-7671

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The focus of this Select Phase II program is to build and deliver laser components both for airborne water vapor and ozone DIAL systems. Specifically, Fibertek proposes to deliver to NASA the following prototype systems: 1) A complete water vapor DIAL transmitter with single-line output tunable over the 936 nm water vapor line, 2) A wavelength converter for ozone DIAL compatible with the GOLD (Global Ozone Lidar Demonstrator) pump laser, with an output on two lines between 300 and 320 nm. Fibertek has developed a common architecture for wavelength converters for both water vapor and ozone DIAL applications. Use of common technology allows us to economically manufacture components for both applications that are compatible with provide improved performance from instruments planned or previously developed by NASA Langley Research Center (LaRC). The laser systems delivered will provide NASA with the critical components needed for a new generation of airborne lidar sensors for measurement of stratospheric and upper tropospheric species central to improved weather forecasting and understanding of global climatology. The laser systems developed also provide a stepping-stone to space-based sensors &#150; utilizing components and architectures that are scalable and traceable to space based operations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our primary non-NASA application is for spin-off of the innovations into other products. These include underwater lidar for the Navy and 3D imaging ladar for all services. The non-linear technology will find application in sensor systems from UV (explosive and cnem.-bio. detection) to the Mid IR ( remote sensing through obscurants). We will be actively marketing the technology developed under this NASA SBIR to all of these potential customers and applications

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA and commercial remote sensing systems for long-lived airborne and space-based DIAL instruments. The high efficiency narrow linewidth, tunable sources being developed in this SBIR meet an unfilled need form our existing customer base and new customers. &#61557; State-or-the-art airborne and UAV based DIAL systems for high-altitude and space-based measurements. This program will provide laser technology that is commercially unavailable to NASA and enable the development of a highly desired instrument for measuring global water vapor and ozone concentration in support of atmospheric modeling and climatology. &#61557; Transition to space-based missions supported by the Decadal Survey such as ACE and ASCENDS. The development of an airborne system is a critical step in technology maturation and position Fibertek to offer laser transmitters for future space missions. &#61557; The prototype UV converter developed under this Phase II program will reduce the technical risk for manufacture of low-cost converter systems for ground-based ozone DIAL. An architecture mating a relatively low-cost commercial pump laser with the specialized UV converters developed under this SBIR program offers a viable path to establishing a broadly-based network of sensors for ground based ozone sensing.

TECHNOLOGY TAXONOMY MAPPING
Robotics (see also Control & Monitoring; Sensors)
Prototyping
Lasers (Ladar/Lidar)


PROPOSAL NUMBER:12-2 E3.01-9948
PHASE-1 CONTRACT NUMBER:NNX13CG08C
SUBTOPIC TITLE: Laser Transmitters and Receivers for Targeted Earth Science Measurements
PROPOSAL TITLE: Atmospheric Lidar with Cross-Track Scanning

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Litespar, Inc.
7010 North Doane Drive
Tucson, AZ 85718-1118
(520) 302-5506

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Austin
baustin@litespar.com
7010 North Doane Drive
Tucson,  AZ 85718-1118
(520) 404-7982

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An eye-safe, multispectral cross-track scan subsystem with a large receiver aperture and a narrow FOV is proposed for the NASA Cloud Physics Lidar (CPL) to increase the horizontal scan area coverage. The /-14 degree cross-track scan capability will cover /- 5 km from nadir at a 20 km altitude. The cross-track scanner uses a bidirectional scan pattern, which collects 10,000 data points per cross track scan at a 5 kHz transmitter rep rate. Solar background is reduced with narrow bandpass filters and a narrow transmitter linewidth with center wavelength control. The scanner accounts for the return pulse lag angle due to pulse time of flight. The existing CPL vertical resolution is maintained at 30 m. Photon counting SPAD detectors and PMT's are used with photon counting modules and multichannel scalers, which support eye-safe operation. The compact receiver telescope design is achieved with a configuration that uses a fixed primary mirror and a scanning secondary mirror, which directs the return signal through a Coude path to the the detector optics bench. The multispectral lidar uses polarization discrimination on two of the three receiver channels, and the optics design supports a 100 urad receiver Instantaneous Field Of View to minimize the solar background noise.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The LSI compact, efficient scanning lidar technology enables new applications for smaller UAV's with payloads less than 10 lbs, and can also replace some existing lidar systems for manned platforms. Scaling to smaller platforms provides a solution for UAV based corridor monitoring for power lines, pipelines, railroads, and many other applications that are served by larger, higher cost hardware and significantly higher cost manned platforms with greater operating expenses. Commercial and military applications for an affordable UAV based, compact, efficient, and wide field of regard scanning lidar include: 1) active multispectral imaging for day and night missions such as crop management, forest and forest fire management, 2) border security, 3) change detection, 4) 3D imaging for law enforcement, 5) natural disaster assessment, and 6) Imaging Laser Altimetry for topographic mapping. The list of existing and emerging scanning lidar applications is growing rapidly. Sensor fusion is also possible with this scan approach and would enable simultaneous thermal imaging and UV, visible, and/or NIR imaging with high 3D resolution in a compact, efficient scanning lidar that could operate at any altitude with a large field of regard.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology provides a scanning solution to increase the cross-track horizontal scan capability of the CPL lidar system used in NASA Earth Science missions. The scanner is scalable to space platforms such as satellites and the International Space Station, and to UAV's. Two Cloud Physics Lidar (CPL) systems are currently operational in the NASA ER-2 and Global Hawk platforms, and have participated in about two dozen missions. The CPL instrument has been operational for over 10 years and is a proven NASA instrument for collecting multispectral atmospheric lidar data at nadir from about 20 km altitude. The LSI scanning lidar instrument will provide aircraft based, off-nadir lidar profiling of clouds and aerosols for the first time, and will bring scanning capability to platforms such as satellites and the ISS. The LSI Phase II prototype integrated into the NASA ER-2 aircraft will provide new capabilities to examine changes in smoke properties along a plume, measure variability of aerosols in urban regions, and measure variability in the shortwave radiation field of clouds.

TECHNOLOGY TAXONOMY MAPPING
3D Imaging
Actuators & Motors
Filtering
Gratings
Lenses
Mirrors
Detectors (see also Sensors)
Lasers (Ladar/Lidar)
Multispectral/Hyperspectral


PROPOSAL NUMBER:12-2 E3.02-8944
PHASE-1 CONTRACT NUMBER:NNX13CM03C
SUBTOPIC TITLE: Advanced Technology Telescope for Balloon Mission
PROPOSAL TITLE: Low Cost, Cosmic Microwave Background Telescopes (P-NASA12-003-1)

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vanguard Space Technologies, Inc.
9431 Dowdy Drive
San Diego, CA 92126-4336
(858) 587-4200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Loomis
jloomis@vst-inc.com
9431 Dowdy Drive
San Diego,  CA 92126-4336
(858) 587-4210

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Existing and proposed missions with ambitious science goals demand ever larger primary mirrors which, in turn, require the development of new light-weight, low-cost mirror technologies. For Phase 2, Vanguard Space Technologies (VST) proposes to deliver a 2.5 meter, composite, on-axis, telescope by building upon the success of the Phase I effort. The telescope will be suitable for use on the Super BLAST-pol mission. VST proposes building upon the success and leveraging the lessons learned from previous technology demonstration programs, leading to a successful CDR that includes a final design with budgeted errors, a detailed manufacturing plan, and a mature recurring cost model and estimate. A CDR package and one high efficiency telescope system will be provided during Phase II. The envisioned telescope system will feature 2X lower areal mass and comparable areal cost for Unit Two+ than BLAST. The Super BLAST-pol team at UPenn is committed to flight test this new technology on the maiden flight in 2016.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Northrup Grumman &#150; Baltimore, an aerospace prime contractor, was contacted on November 5, 2013, and briefly informed of our activities. NG expressed interest in the technology and Phase 1 results. Vanguard will meet with NG personnel within 1-2 months. Our target application is tactical missions for DoD, possibly surveillance and/or communications related.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Vanguard met with Alan Kogut at GSFC on 11/7/13. The technology may also be of interest to a future NASA GSFC program currently referred to as BOBCAT. BOBCAT is still in the concept/design phase and open to change. The telescope functions mainly as a "light bucket" for the spectrometer, and will not feed a large pixelized focal plane. The current design envisions an on-axis system (similar to BLAST). Tentative requirements include a 3-4 meter primary; operating frequency: initially 300-700 GHz, eventually 300 GHz to several THz (submil-far infrared); operating temperature: 40K or below; system overall mass &#150; 5 metric tons (includes dewar); mid-latitude environment (not Antartica); and launched in desert environment.

TECHNOLOGY TAXONOMY MAPPING
Antennas
Coatings/Surface Treatments
Composites
Structures
Mirrors
Infrared
Terahertz (Sub-millimeter)


PROPOSAL NUMBER:12-2 E3.03-8875
PHASE-1 CONTRACT NUMBER:NNX13CL51C
SUBTOPIC TITLE: Extreme Environments Technology
PROPOSAL TITLE: Extreme Environment Circuit Blocks for Spacecraft Power & Propulsion System & Other High Reliability Applications

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: 4

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Chronos Technology (DIv of FMI, Inc.) proposes to design, fabricate, and deliver a performance proven, and commercially available set of extreme high operating temperature PWM controller and circuit blocks (EXTEC1). These rad-hard (TID, SEU, ELDERS) components are intended to be used in a variety of spacecraft power and propulsion systems (PPU) along with smart power sub-assemblies for a wide range of both manned and unmanned space missions and payloads. The resulting devices would meet and exceed the required performance under extreme environment, high temperature while being offered commercially in very light, small and rugged package sizes and footprints. The described performance would be superior to any present-day alternatives that may only be available at much lower operating temperatures with no provisions for radiation hardness. The proposed range of circuit blocks that will be fabricated in Silicon Carbide (SiC) technology includes monolithic Pulse Width Modulator (PWM) controller as well as basic circuit blocks such as logic gate(s), counter(s), multivibrator, ramp generator, voltage reference, oscillator, buffer(s) and driver circuits. Logically and synergistically, many of the aforementioned circuit blocks would be used in the integrated PWM design.The significant points of innovation that we propose to bring to realization are: 1-Design and fabrication of a SiC MSI (medium-scale integration) Mixed-Signal ASIC. The proposed PWM controller ASIC is a mixed-signal system. 2-Design and fabrication of a precision, high-temperature capable, voltage reference on SiC at the integrated circuit level (used in the PWM and other applications). 3-Design and fabrication of precision, extreme high-temperature capable, timing circuits on SiC at the integrated circuit level (used in the PWM and other applications). 4-Common approach to the yield packaged extreme environment component encapsulation among the various devices designed and fabricated in the project

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The potential non-NASA applications are divided into non-NASA space applications on the one side while other avionics, jet engine controller, down-hole and various advanced "all electrical" vehicle for defense and other industrial automotive applications would round up the segment. The non-NASA space applications would follow the NASA applications closely. The variety of DC-DC converters and solar power inverters are quite common examples. Our direct market observations and discussions indicate that there are a variety of smart power module designs for commercial space and non-NASA scientific space applications that would benefit from the availability of reliable and radiation hardened PWM controllers for power inverter applications. The potential market segments within the non-radiation hardened area are rather diversified. Down-hole oil and gas exploration and geothermal energy generation represent a serious market for the PWM controller. FMI has received very positive written statements of interest from the leading companies in that industry. FMI has already made efforts at the prototype level for timing control applications in the jet engine control market segment. It is a logical approach to leverage such effort to introduce the performance results of the proposed SiC devices to the jet engine control market. Electric vehicle applications could be another potential for the developed devices. This includes the DOD's next generation, all electrical combat vehicle.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Spacecraft power and propulsion (PPU) system requirements as well as other related smart power module applications is the main driver behind this proposal. A number of NASA centers have been working on such applications. Published work such as the recent paper by NASA Kennedy space center, Langley Research Center and JPL (IEEE 978-1-4673-1813-6/13) captures the closest perspective to the needed innovation for solar electric propulsion. Given that most of the attention is taken on the high power side of the utilized circuit blocks, the proposed work here would offer the best match to meet and exceed the NASA objectives. In parallel with offering response to meet the PPU demand, other future NASA mission targets with some emphasis on "hot planets" could be well served not only by the integrated PWM controller but also the standalone circuit blocks could play pivotal role in mitigating the challenges for electronic circuit operation at extreme high temperatures and in small form-factors. pulse width modulator (PWM) controller could be used in smart power (inverter/converter) applications in NASA missions with diverse base of power generation and distribution schemes. Missions to hot planets, atmospheric probes, deep space missions and any missions requiring space propulsion cover the potential application base for the PWM controller. The standalone devices will have additional application in motor controllers, timers and stable clocks in extreme high temperature environments

TECHNOLOGY TAXONOMY MAPPING
Airship/Lighter-than-Air Craft
Air Transportation & Safety
Avionics (see also Control and Monitoring)
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Space Transportation & Safety
Tools/EVA Tools
Autonomous Control (see also Control & Monitoring)
Man-Machine Interaction
Perception/Vision
Robotics (see also Control & Monitoring; Sensors)
Command & Control
Condition Monitoring (see also Sensors)
Process Monitoring & Control
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Manufacturing Methods
Materials (Insulator, Semiconductor, Substrate)
Conversion
Distribution/Management
Generation
Sources (Renewable, Nonrenewable)
Storage
Characterization
Models & Simulations (see also Testing & Evaluation)
Prototyping
Quality/Reliability
Software Tools (Analysis, Design)
Support
In Situ Manufacturing
Processing Methods
Coatings/Surface Treatments
Metallics
Actuators & Motors
Deployment
Exciters/Igniters
Microelectromechanical Systems (MEMS) and smaller
Pressure & Vacuum Systems
Vehicles (see also Autonomous Systems)
Atmospheric Propulsion
Extravehicular Activity (EVA) Propulsion
Photon Sails (Solar; Laser)
Spacecraft Main Engine
Surface Propulsion
Tethers
Acoustic/Vibration
Chemical/Environmental (see also Biological Health/Life Support)
Pressure/Vacuum
Sensor Nodes & Webs (see also Communications, Networking & Signal Transport)
Thermal
Destructive Testing
Lifetime Testing
Simulation & Modeling