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NASA 2017 SBIR Phase II Solicitation


PROPOSAL NUMBER:17-2 A1.01-9469
PHASE-I CONTRACT NUMBER:NNX17CL53P
SUBTOPIC TITLE: Structural Efficiency-Tailored Airframe & Structures
PROPOSAL TITLE: Single-Process, Unitized, Composite Fuselage
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
510 Earl Boulevard
Miamisburg,OH 45342 -6411 (937) 320-1877
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryan Pelley
pelleybm@crgrp.com
510 Earl Blvd.
Miamisburg ,OH 45342 -6411
(937) 320-1877 Ext: 1198

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA seeks tailored airframes and structures to reduce structural mass in support of the NASA Aeronautics Strategic Implementation Plan (2015), following the Roadmap for Ultra-Efficient Commercial Vehicles, Subsonic Transport. Tailored structures are comprised of the right materials, at the right place, in the right orientation, in the right amount. Whatever the material or structural configuration, excess weight is driven out through optimization, within the limitations of the manufacturing approach. NASA’s Advanced Composites Project is focused on the manufacturing approaches that enable more efficient composite structures. CRG has been laying the foundation for the design and production of tailored structures for more than a decade. CRG’s vision for tailored airframes and structures begins with unitization, enabled by Smart Tooling for affordable manufacturing of complex composites. CRG began work on Smart Tooling for fuselages in 2005, targeting fully-integrated, single-process skins, stringers, and frames. CRG subsidiary Spintech launched in 2010 to commercialize Smart Tooling into the aerospace industry. Today, CRG brings robust capabilities in composite structural optimization, expanding capabilities in aerospace composite fabrication, and Spintech’s Smart Tooling technology to provide NASA with unitized fuselage configurations with an unmatched combination of affordability and structural efficiency.

POTENTIAL NASA COMMERCIAL 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.
Government systems that would derive the same benefits would include future DoD aircraft, both manned and UAS.
This technology's attributes for reduced manufacturing costs and reduced operating costs should yield a high potential for private sector commercialization for aircraft production by the major OEMs, prime contractors, and Tier 1 suppliers in both the commercial aircraft and defense industries.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Supporting NASA's Aeronautics Research Mission Directorate, this project's technologies directly address requirements for tailored airframes and structures resulting in mass reduction for improved fuselage structural efficiency. The goals support NASA's roadmap for Ultra-Efficient Commercial Vehicles - Subsonic Transport, and the Advanced Composites Project. This project's technologies enabling structural unitization lead to reduced manufacturing cost, reduced operating costs resulting from reduced fuel burn, and reduced emissions, leading to cleaner and more affordable flight in the future.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Air Transportation & Safety
Prototyping
Processing Methods


PROPOSAL NUMBER:17-2 A1.02-9654
PHASE-I CONTRACT NUMBER:NNX17CA36P
SUBTOPIC TITLE: Quiet Performance - Airframe Noise Reduction
PROPOSAL TITLE: High Channel Count, High Density Microphone Arrays for Wind Tunnel Environments
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Interdisciplinary Consulting Corporation
5745 Southwest 75th Street, #364
Gainesville,FL 32608 -5504 (352) 283-8110
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Stephen Horowitz
shorowitz@thinkIC2.com
5745 Southwest 75th Street, #364
Gainesville ,FL 32608 -5504
(256) 698-6175

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The Interdisciplinary Consulting Corporation (IC2) proposes the development of high channel count, high density, reduced cost per channel, directional microphone arrays for noise source measurement using microelectromechanical systems (MEMS) based piezoelectric microphones with backside contacts and advanced packaging technology. The goal of this research is to develop an advanced phased-array technology to revolutionize array measurement capabilities through increases in array density and channel count while easing installation into wind-tunnels and significantly reducing cost per channel. Specifically, this array technology will be developed to address NASA needs for acoustic and relevant flow field measurement methods for subsonic, transonic and supersonic vehicles targeted specifically at airframe noise sources and the noise sources due to the aerodynamic and acoustic interaction of airframe and engines, as per Subtopic A1.02 Quiet Performance - Airframe Noise Reduction of the NASA FY 2017 SBIR/STTR Solicitation. This work is aimed at meeting the aerospace industrys need for economically viable array technology that meets required metrics.  The focus of this project is to combine proven MEMS design principles and established device structures to develop high channel count, high-density acoustic arrays.  The end results of this innovative approach are higher density acoustic arrays, with significantly-reduced cost per channel enabling higher channel arrays comprised of high bandwidth, high dynamic range, flush-mounted aeroacoustic microphones.  Further, the thin form factor of the resulting array eases installation constraints and placement restrictions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed instrumentation technology has the potential to be implemented across government, industry and academic institution test facilities. The target market is instrumentation and measurement microphones and arrays for the aerospace industry. The target application is as wind tunnel instrumentation for phased-array beamforming to enable noise source localization. In addition to wind-tunnel testing, the proposed microphone technology is also applicable to the types of technological solutions sought for pressure measurements and focusing acoustic measurements that can be used in a flight-test tunnel environment and ground test instrumentation for static engine testing. The primary characteristic of this market is the need for high performance measurements with relatively low volume requirements. Ultimately, the cost per unit and size constraints of existing technologies limit the array size and density below customer desired levels. IC2 seeks to change that dynamic via microphones with reduced size and complexity, at drastically lower cost (roughly an order of magnitude), enabling vastly larger, affordable arrays of higher density. We achieve those goals while meeting individual microphone performance requirements,leading to potentially game-changing improvements in array performance. Potential commercial customers include industry aircraft manufacturers, such as Boeing, Northrop Grumman, Lockheed Martin, Gulfstream, Bombardier, and the academic research community.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed instrumentation technology has the potential to be transportable across multiple NASA facility classes as well as implemented across government-owned test facilities. The target application for entry into NASA ATP is as wind tunnel instrumentation for phase-array beamforming to enable noise source localization. In addition to wind-tunnel testing, the proposed microphone technology is also applicable to the types of technological solutions sought for pressure measurements and focusing acoustic measurements that can be used a flight-test tunnel environment and ground test instrumentation for static engine testing. The proposed innovation is applicable to NASA Langleys Subsonic Wind Tunnel for advanced phased array measurements of fixed- and rotary-wing civil and military aircraft, the Acoustics Research Laboratory's 20 x 24 x 30 anechoic quiet-flow facility, as well as LaRC's Aeroacoustics Branch by supplying validation of simulation of the Rotorcraft, the Subsonic Fixed Wing, and the Supersonic Projects. Additionally,it is useful for multiple NASA GRC facilities in the Acoustics Branch, the Aero-Acoustics Propulsion Laboratory, Small Hot Jet Acoustic Rig, Nozzle Acoustic Test Rig, and Advanced Noise Control Fan Rig. At NASA Ames, the technology benefits the Experimental Aerophysics Branch, and facilities such as the 7-by 10-Foot Wind Tunnel.

TECHNOLOGY TAXONOMY MAPPING (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.)
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)
Microelectromechanical Systems (MEMS) and smaller
Atmospheric Propulsion
Acoustic/Vibration
Pressure/Vacuum
Aerodynamics
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Materials (Insulator, Semiconductor, Substrate)
Characterization
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)


PROPOSAL NUMBER:17-2 A1.03-9411
PHASE-I CONTRACT NUMBER:NNX17CC51P
SUBTOPIC TITLE: Low Emissions Propulsion and Power-Turboelectric and Hybrid Electric Aircraft Propulsion
PROPOSAL TITLE: Low AC-Loss Superconducting Cable Technology for Electric Aircraft Propulsion
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Hyper Tech Research, Inc.
539 Industrial Mile Road
Columbus,OH 43228 -2412 (614) 481-8050
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Matthew Rindfleisch
mrindfleisch@hypertechresearch.com
539 Industrial Mile Rd
Columbus ,OH 43228 -2412
(614) 481-8050 Ext: 2438

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The availability of low AC loss magnesium diboride (MgB2) superconducting wires enables much lighter weight superconducting stator coils than with any other metal or ceramic superconductor. This, together with Hyper Tech’s capability to fabricate long piece-length (potentially 60 km) wires, in turn enables lighter superconducting motors/generators, essential components in the turboelectric aircraft propulsion system with high power densities (over 10 kW/kg) and high efficiency superconducting components envisioned in next generation Air Vehicle Technologies. To that end, this proposed SBIR Phase II program focuses on developing MgB2 multifilament superconducting cables with exceptionally low AC losses (targeting a loss budget of 1 W/cm3) because superconductors in a cable form is arguably the only easily-accomplished and viable way to push down AC losses while retaining high operating current levels in the stator coils. Two recent advancements at Hyper Tech greatly increase the odds of success in developing superconducting cable technology in the Phase I: 1) the development of cutting-edge superconductor strand architecture designs with fine filaments, small twist pitches and resistive components for reducing AC losses and 2) improved wire manufacturing capability to fabricate multi-strand cables in significant length. A second benefit of using superconducting cable technology, beyond AC loss reduction, is the much lower heat load produced or enabled by the conductor.

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Superconducting transformers, motors, generators, fault current limiters, DC transmission cables, 4 to 20 MW wind and wave turbine generators, aircraft turbo-generators, offshore oil platform motors, marine propulsion and generation systems, portable emergency power systems, and conduction cooled (liquid helium bath free) 1.5T and 3.0T MRI systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aircraft power components (motors, generators, cables), transformers, inductors, power conditioning equipment, ADR coils, magnetic bearings, actuators, MHD magnets, spacecraft electric propulsion systems (e.g. MPD and VASIMR thruster), magnetic shielding for spacecraft structures, magnetic launch devices and other applications where light weight power components are required.

TECHNOLOGY TAXONOMY MAPPING (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.)
Nanomaterials
Atmospheric Propulsion
Cryogenic/Fluid Systems
Air Transportation & Safety
Superconductance/Magnetics
Processing Methods


PROPOSAL NUMBER:17-2 A1.03-9836
PHASE-1 CONTRACT NUMBER:NNX17CC35P
SUBTOPIC TITLE: Low Emissions Propulsion and Power-Turboelectric and Hybrid Electric Aircraft Propulsion
PROPOSAL TITLE: A Software Toolkit to Accelerate Emission Predictions for Turboelectric/Hybrid Electric Aircraft Propulsion

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)
Andrea Zambon
azambon@craft-tech.com
6210 Keller's Church Rd.
Pipersville,  PA 18947-1020
(215) 766-1520

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
<p>Electric propulsion represents an attractive path for reducing overall emissions. For larger commercial aircrafts operating in the mega-watt range, power turboelectric and hybrid electric aircraft propulsion will continue to rely on gas turbine engines/generators to provide part of the thrust, charging batteries and driving generators. As a result, reduction of emissions such as oxides of nitrogen (NOx) remains a key concern. The innovation proposed is a software toolkit supporting high-fidelity yet computationally-tractable predictions of NOx emissions and other pollutants in gas-turbine engines/generators within the context of unsteady Computational Fluid Dynamics (CFD) simulations. A well-known difficulty limiting the accurate prediction of NOx levels in turbulent flames is related to the fact that NOx production can evolve through several different chemical pathways characterized by drastically different time scales. In this regard, a fast-running turbulent combustion approach called Multi-TimeScale Flamelet/Progress Variable (MTS-FPV) is being developed to address NOx emissions in a computationally-tractable manner and by capturing the relevant characteristic chemical time scales. The MTS-FPV formulation will be matured and extended to model two-phase droplet vaporization and then subsequently packaged as a software toolkit. Furthermore, this software toolkit will be interfaced with NASA&rsquo;s OpenNCC CFD code. As a result, at the conclusion of the SBIR program, NASA will have available in-house (i) the enhanced emission prediction capabilities of OpenNCC as well as (ii) a methodology for leveraging these capabilities in system-level trade analyses of hybrid electric aircraft propulsion concepts.</p>

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The commercial market for this product includes the broad aerospace, power-generation and defense industry. The primary driver for the commercial market for this product is represented by commercial aircraft gas turbine engines. The proposed software toolkit directly addresses the resulting increased demand for high-fidelity design tools that accurately characterize emissions and unsteady combustion effects and will benefit commercial gas turbine OEMs (both commercial and military) by providing them with a powerful and tractable supplement to minimize the need for experimental testing. Other applications encompass power-generation turbines and internal combustion, HCCI and diesel engines, e.g., using engine recirculation (EGR) devices to mitigate harmful NOx production. DoD applications include the design of gas-turbine engines, scramjets, pulse-detonation-engines (PDEs), augmentors, UAVs propulsion systems and rocket engines. Of particular relevance is the Army single fuel policy mandate to use jet fuel in ground vehicle diesel engines to simplify the supply chain logistics in the battle space and to strengthen domestic energy security. Also noteworthy is the DoD growing interest in fuel blends with alternative or renewable fuels, e.g., synthetic paraffinic kerosene or camelina-derived bio-fuel, as an acceptable form of "drop-in" fuels.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This product addresses NASA Aeronautics Research Mission Directorate (ARMD) core needs for enabling safe and reliable operation of next-generation (e.g., N+3 generation and beyond) ultra low-emission power turboelectric and hybrid electric aircraft propulsion, where gas turbine engines will continue to play a critical role. With increasingly stringent environmental regulations, reduction of emissions, including NOx, remains a key concern, in particular for larger aircrafts operating in the mega-watt range. In hybrid electric propulsion concepts such as STAR-ABL, emission requirements are also coupled with the need for the optimal budgeting of the power requirements for propulsion and power generation. This product also addresses core needs of NASA's vision for next-generation aircraft systems with hybrid integrated wing/body systems that feature significant improvements in engine performance, emissions and noise reduction. Since low-emission combustor designs tend to operate at fuel lean conditions near the flame lean blow-out limit, a detailed understanding of flame dynamics and unsteady combustion effects is required to develop fuel-efficient, low-emission, stable combustor designs. Advanced CFD design tools can provide fundamental physical insight that is difficult or cost-prohibitive to obtain experimentally. Given the inherent modularity of the MTS-FPV approach, interfacing with the OpenNCC will provide NASA with a powerful design support tool.

TECHNOLOGY TAXONOMY MAPPING
Atmospheric Propulsion
Fuels/Propellants
Simulation & Modeling
Generation
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Support


PROPOSAL NUMBER:17-2 A1.04-8890
PHASE-I CONTRACT NUMBER:NNX17CL28P
SUBTOPIC TITLE: Aerodynamic Efficiency-Active Flow Control Actuators and Design Tools
PROPOSAL TITLE: Active Flow Control System for Commercial Aircraft Using Synthetic Jet
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Actasys, Inc.
8 Callaway Circle
Loudonville,NY 12211 -2640 (917) 621-5322
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Menicovich
david.menicovich@gmail.com
8 callaway circle
Loudonville ,NY 12211 -2640
(917) 621-5322

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

In order to enable widespread application of Active Flow Control (AFC) technology on commercial aircraft, Actasys, Inc. (Actasys), in collaboration with The Center for Advanced of Multifunctional Material Systems at University of California, Los Angeles (CAMMS-UCLA) , The University of Michigan (UMich), and The Boeing Company (Boeing) intend to build upon the foundational work implemented in phase I to develop and prepare for flight tests a module containing an array of  Synthetic Jet Actuators (SJA). Over a period of 18 months, the project will be divided into two parts. The first part will be dedicated primarily to improving actuator power output as well as preparing a module prototype.  In order to achieve the required SJA performance levels, system properties, and functionality as determined by Boeing, the team shall use the computational approach developed in phase I coupled with investigations into new active materials. In the second part, Actasys and Boeing shall collaborate on testing the prototype in order to determine flight test readiness.  Actasys’ post Phase II plans include testing SJA module performance on a Boeing 757 commercial aircraft to demonstrate targeted aerodynamic impact and fuel efficiency. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The developed technology has the potential to be commercialized in a wide set of markets and for a wide set of purposes. By leveraging its ability to reduce the drag of vehicles, the developed system can be used to increase the fuel efficiency of a range of ground vehicles, including tractor-trailers, SUV, sports cars, trains, and buses. Furthermore, similarly to ground vehicles, the developed system can be used to reduce the aerodynamic drag of large marine vessels, increasing their fuel efficiency (both in commercial and military applications). By leveraging its ability to enhance maneuverability and stability, the new system can be applied to high-speed boats (both for military and commercial applications) and to sports cars. Furthermore, it can be integrated with wind turbine blades to enhance their energy output and reduce their mechanical vibrations, ultimately prolonging their life. Finally, the developed system can be utilized to enhance cooling and heating in a variety of applications, ranging from computer and power electronics to HVAC systems in buildings.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Fuel efficiency improvement of commercial flying vehicles is only one of several potential applications of the developed system within the aerospace industry. Another application that would benefit NASA is the use of the developed technology to enhance the maneuverability of a wide set of applications, including rockets, missiles, UAVs and landing payloads. By integrating the developed system into such devices it will be possible to achieve a higher degree of maneuverability with very small amount of power. Furthermore, synthetic jet technology can in principle be used to enhance cooling of computer and power electronics, a critical aspect of several NASA missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Atmospheric Propulsion
Aerodynamics
Air Transportation & Safety
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)


PROPOSAL NUMBER:17-2 A1.05-8647
PHASE-I CONTRACT NUMBER:NNX17CL64P
SUBTOPIC TITLE: Computational Methods & Tools - High Fidelity Mesh and Geometry Tools
PROPOSAL TITLE: HeldenSurface: A CAD Tool to Generate High-Quality Surfaces
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Helden Aerospace Corporation
2463 Saluda Drive
Acworth,GA 30101 -8088 (678) 849-9420
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Hooker
rick@heldenaero.com
2463 Saluda Drive
Acworth ,GA 30101 -8088
(678) 849-8420

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

One of the primary shortcomings identified during the NASA sponsored CFD Vision 2030 Study conducted during 2012-2014 was that the generation of meshes suitable for CFD simulations constitutes a principal bottleneck in the workflow process as it requires significant human intervention.  Our solution to this problem is the development of HeldenSurface, which is a robust tool for automatially converting arbitrary starting geometry definitions into a collection of watertight CAD surfaces.  These CAD surfaces are then used as the starting point for existing commercial grid generators such as our HeldenMesh unstructured grid generator.  This represents a critical capability needed to automate the CFD mesh generation process – permitting the thousands of engineers performing CFD to focus their efforts on interpreting results instead of generating meshes.  The feasibility of HeldenSurface was proven during our Phase I effort through its successful demonstration on multiple test cases.  Our Phase II effort builds upon this past success by focusing on its further development and demonstration, testing, and completion of commercialization assessments.  We offer a proven path to commercialization of HeldenSurface by leveraging our current success with the commercialization of our HeldenMesh grid generation software and we anticipate offering HeldenSurface as a commercial product within 2 years of completion of the Phase II effort.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Helden Aerospace has already successfully transitioned its existing HeldenMesh commercial grid generator to companies such as Gulfstream, Boom Technologies, The Spaceship Company, and NASA Langley Research Center. These same customers have been repeatedly requesting the capabilities that HeldenSurface offer -- indicating strong demand for the product. The completion of this Phase II effort would further improve the HeldenMesh grid generation process through nearly complete automation. The development of HeldenSurface will result in a product with strong commercial viability. We offer a viable commercialization strategy by first offering HeldenSurface to our existing customers, expanding our customer base within the aerospace industry, and then growing our market into universities and non-aerospace applications (automotive, oil and gas, electronic, etc.).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The successful completion of our proposed Phase II effort results in a validated method (HeldenSurface) for automatically converting arbitrary geometries (such as a cloud of points, "dirty" CAD, or CFD meshes) into a collection of watertight CAD surfaces that are smooth, connected, and split into as few number of surfaces as possible. As described in the technical proposal, this represents a critical capability needed to automate the CFD mesh generation process, which is the primary bottleneck in the application of CFD. The development of HeldenSurface would permit the hundreds NASA's engineers performing CFD to focus their energies on interpreting results instead of generating meshes.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Aerodynamics
Analytical Methods
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 A1.05-8731
PHASE-I CONTRACT NUMBER:NNX17CL83P
SUBTOPIC TITLE: Computational Methods & Tools - High Fidelity Mesh and Geometry Tools
PROPOSAL TITLE: High Order Mesh Curving and Geometry Access
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pointwise, Inc.
213 South Jennings Avenue
Fort Worth,TX 76104 -7610 (817) 377-2807
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steve Karman
skarman@pointwise.com
213 S. Jennings Ave.
Fort Worth ,TX 76104 -1107
(817) 377-2807 Ext: 1602

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Phase II effort will focus on enhancements to CurveMesh, interfacing with geometry through Project Geode and enabling surface splining of discrete geometry in a commercial mesh tool using SLUGS. CurveMesh will be modified to enable mixed order meshes and h-p adaptation in a parallel computing environment. A demonstration of the h-p adaption will be performed by loosely coupling CurveMesh with FUNSAFE (UTC FEM solver) on simple to realistic configurations. A schema will be developed and documented that allows geometry to mesh associativity to be defined for mesh operations downstream of the original mesh creation. The surface splining software, SLUGS, will be incorporated into the Graphical User Interface for Pointwise to permit users to create smooth analytic surfaces from discrete tessellated input geometry.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Phase II tools will also benefit other high order FEM flow solver developers by providing a means to create curved meshes for realistic geometries. The existing CurveMesh code has been used to create curved meshes for the 6th AIAA Drag Prediction Workshop, the 3rd High Lift Prediction Workshop and the 5th High Order CFD Workshop. Generated meshes have been analyzed by PyFR, CREATE-AV COFFE and others. Knowledge from Project Geode integration into CurveMesh will also benefit other researchers in need of geometry access.

The possible commercialization of CurveMesh will benefit any Pointwise users in need of high order meshes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase II will produce usable tools that could be beneficial to NASA. The enhancement of CurveMesh is potentially beneficial to any NASA unstructured CFD FEM code that can use high-order meshes. FUN3D is under development to include a high order FEM flow solver. It?s core methods are similar to the FUNSAFE methods under development by Dr. Sreenivas. Enhancements to Project Geode with the planned schema will conceivably work with other meshing tools. Knowledge gained about implementing these new features into CurveMesh will be shared with the CFD community. FUN3D is again a tool that could use Project Geode for adaptive refinement and shape optimization.

Phase II will lead to a possible commercial implementation of the CurveMesh methods in Pointwise. NASA engineers with Pointwise licenses will benefit from this implementation.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Aerodynamics
Analytical Methods
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 A1.06-8527
PHASE-I CONTRACT NUMBER:NNX17CC27P
SUBTOPIC TITLE: Vertical Lift Technology
PROPOSAL TITLE: Intelligent Electronic Speed Controller
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
4D Tech Solutions, Inc.
1275 Stewartstown Road, Suite 200
Morgantown,WV 26505 -3636 (443) 604-0256
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Eric Sorton
esorton@4dtechsolutions.com
1275 Stewartstown Road, Suite 200
Morgantown ,WV 26505 -3636
(304) 685-9436

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This project will result in the commercialization of an Intelligent Electronic Speed Controller (IESC) for use on Unmanned Aerial Vehicles (UAVs). The IESC will advance the state-of-the-art of health-state awareness. This will be achieved through the integration of propulsion system health monitoring sensors that - in unison with an Intelligent Rule Set - will be able to monitor system and component performance trends and predict propulsion system faults. The system is designed to provide the analytic capability necessary to predict propulsion system degradation, maintenance or repair needs. An Artificial Neural Network (ANN) will be trained on data from IESC sensors from nominal flights and those with known faults leading to failure. After training, an initial Intelligent Rule Set will be extracted to represent the knowledge of the ANN and used in the system to predict failures. This set of rules will be periodically updated as more flight data is collected.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA use will target manufacturers of Unmanned Aerial Vehicles (UAVs) in the commercial market sectors that provide their end-users with highly reliable UAVs. Currently, there are 35,000 FAA-certified UAV pilots. Reliability will become increasingly important in these market sectors as the cost and complexity of payloads increases and as proximity to humans and property decreases. The technology developed will be low-cost and will integrate seamlessly with existing designs. UAVs are well-suited to performing many types of missions including those that are inherently dangerous to humans, those that require precision flight for data collection, and those that need to be performed within a limited budget. Applications for UAVs include aerial photography, remote sensing, disaster response, agricultural monitoring, forestry service support (including forest fires), infrastructure inspection, mining and quarrying, and environmental surveys to name a few.
As submitted: Manufacturers of Unmanned Aerial Vehicles (UAVs) that sell systems for valuable payloads are the primary customers. The technology will integrate seamlessly with existing UAV designs. Commercial applications include aerial photography, remote sensing, disaster response, agricultural monitoring, forestry service support, infrastructure inspection, mining and quarrying, and environmental surveys.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This effort supports the objectives of the NASA Unmanned Aerial System Traffic Management (UTM) system concept and also the activities of NASA's Small Unmanned Aerial Vehicle Laboratory (SUAVE Lab). Successful implementation of the UTM concept will require that UAVs operate without failure or fault to the greatest extent possible. UTM Technical Capability Level Four will involve higher-density urban areas for autonomous vehicles used for news gathering and package delivery (with a demonstration target of 2019); flight incidents in urban areas could result in injury to humans or damage to property of loss of control incidents occur. The SUAVE Lab designs, develops, builds and tests small UAVs and provides expertise to national level organizations on small UAV designs, operations and airspace integration. The technology serves to ensure the reliability of small UAV systems advances as needed to support expansion of their use in the future.

TECHNOLOGY TAXONOMY MAPPING (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.)
Acoustic/Vibration
Inertial
Thermal
Diagnostics/Prognostics
Recovery (see also Autonomous Systems)
Autonomous Control (see also Control & Monitoring)
Intelligence
Algorithms/Control Software & Systems (see also Autonomous Systems)
Condition Monitoring (see also Sensors)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)


PROPOSAL NUMBER:17-2 A1.07-9737
PHASE-I CONTRACT NUMBER:NNX17CC34P
SUBTOPIC TITLE: Propulsion Efficiency-Propulsion Materials and Structures
PROPOSAL TITLE: Integrated Fluid and Materials Modeling of Environmental Barrier Coatings
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corporation
701 McMillian Way Northwest, Suite D
Huntsville,AL 35806 -2923 (256) 726-4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryce Devine
Bryce.Devine@cfdrc.com
701 McMillian Way Northwest, Suite D
Huntsville ,AL 35806 -2923
(256) 726-4816

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Environmental barrier coatings (EBC) prevent oxidation of ceramic materials in reactive, high temperature environments such as the exhaust regions of gas turbine engines. CFDRC proposes to develop a physics based model of an EBC system interacting with the flow environment to provide better understanding of the dynamic processes that effect EBC durability under propulsion conditions. The model uses computational fluid dynamics to establish the conditions and species concentrations across the surface of the structure. The response within the coating to the environments is predicted using microscale simulations where each component of the composite coating system is discretely resolved. The micromechanics models are based on peridynamics, a mesh free theory of continuum mechanics that simultaneously solves for thermal, mechanical and concentration gradients coupled with damage to the material. Results of numerous microscale simulations are used to inform a time, temperature and stress based damage criteria for a homogenized coating material which in turn can be used to predict the extent of coating break down and mass loss at each integration point within boundary of a CFD simulation.

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Rolls-Royce and Lockheed Martin Corporation are advising the direction and application of the Phase II project. CFDRC will develop the modules for industrial turbine problems and apply expert support based on their guidance

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The final product developed during Phase II will be a computational toolkit to model damage profiles in EBCs. The software modules will be linked to the CFD and FEM modeling tools currently in use at NASA Glenn Research Center, directly interfacing with their current turbine materials research programs. These modules will combine automated scripts with high-fidelity simulation programs to model and analyze EBC material behavior.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Composites
Atmospheric Propulsion
Launch Engine/Booster
Models & Simulations (see also Testing & Evaluation)
Quality/Reliability
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 A1.08-9629
PHASE-I CONTRACT NUMBER:NNX17CL70P
SUBTOPIC TITLE: Aeronautics Ground Test and Measurements Technologies
PROPOSAL TITLE: Fast Response, Fiber-Optic Micromachined Five-Hole Probe for Three-Dimensional Flow Measurements in Harsh Environments
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Interdisciplinary Consulting Corporation
5745 Southwest 75th Street, #364
Gainesville,FL 32608 -5504 (352) 283-8110
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Stephen Horowitz
shorowitz@thinkIC2.com
5745 Southwest 75th Street, #364
Gainesville ,FL 32608 -5504
(256) 698-6175

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The Interdisciplinary Consulting Corporation (IC2) proposes the development of a fiber-optic, micromachined five-hole probe for three-dimensional flow measurements in harsh environments. The goal of this research is to develop a microelectromechanical systems (MEMS) based, optical probe capable of significantly improved performance compared to existing available sensors, by enabling faster response time, higher bandwidth transduction and increased angular measurement range while reducing sensor power requirements. The proposed technology offers these benefits in a compact, high-temperature capable package, extending past successes in fiber-optic, micromachined pressure sensing technology. Specifically, this sensor technology will be developed to address NASAs objective to develop innovative tools and technologies that can be applied in NASA ground-based test facilities to revolutionize wind tunnel testing and measurement capabilities and improve utilization and efficiency as per subtopic A1.08 Aeronautics Ground Test and Measurements Technologies of the NASA FY 2017 SBIR/STTR Solicitation. 

The proposed innovations will specifically provide the following benefits for wind-tunnel applications:

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary commercial applications targeted for this technology are in the scientific test, measurement and instrumentation market, specifically for aircraft design and development. The proposed technology seeks to meet all performance and operational requirements for the scientific instrumentation market, first addressing ground-test applications followed later by flight-test. Potential commercial customers include industry aircraft manufacturers, such as Boeing, Northrop Grumman, Airbus, Lockheed Martin, Gulfstream, Bombardier, and many smaller developers. Additionally, we have been making inroads into the academic research community with our current commercial products and see similar potential (for scientific test) for this product. Additional commercial applications target operational in-flight air data probes sensors for aircraft feedback and control. Potential customers include the same batch of customers as described above for aircraft development but for operational rather than design environments. Another major market is the UAV market, via miniaturization of the system for use as an air data probe. Potential customers include the multitude of small commercial UAV system and service providers (e.g. Prioria Robotics), large corporate entities developing commercial and military UAV/UAS (e.g. General Atomics and Aerovironment) and various branches of government (e.g. NASA, USDA, DHS, DOD).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed instrumentation technology has the potential to be transportable across multiple NASA test facility classes. The target application for entry is as wind-tunnel instrumentation for improved flow angularity measurements. Currently, similar measurements are performed at NASA Langley (Flow Physics & Control Branch), but are limited by the performance specifications of available measurement tools. These measurements are critical to the design and validation of vehicles with improved aerodynamic performance. The target application for entry into the NASA Aeronautics Test Program is as instrumentation for 3D flow measurements within ground test facilities such as those at NASA Langley, Glenn, and Ames Research Centers. In addition, the instrumentation can be further miniaturized to enable entry into flight test facilities, such as those at Neil A. Armstrong Flight Research Center. Existing and state-of-the-art multi-hole probe technology available to NASA and industry limit measurement capabilities due to large sensor probe diameters, long pressure ports for routing to transducers located distantly or outside the flow field, and restricted operational temperature ranges. The existing technological limitations introduce excessive angular error and long settling and response times, limiting measurement to either static operation or at best, minimal bandwidth dynamic operation (Telionis, 2009). Our proposed technology surmounts these constraints.

TECHNOLOGY TAXONOMY MAPPING (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.)
Microelectromechanical Systems (MEMS) and smaller
Fiber (see also Communications, Networking & Signal Transport; Photonics)
Positioning (Attitude Determination, Location X-Y-Z)
Pressure/Vacuum
Aerodynamics
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Autonomous Control (see also Control & Monitoring)
Attitude Determination & Control
Characterization
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)


PROPOSAL NUMBER:17-2 A1.09-8639
PHASE-I CONTRACT NUMBER:NNX17CD08P
SUBTOPIC TITLE: Vehicle Safety- Internal Situational Awareness and Response
PROPOSAL TITLE: Improved UAS Robustness Through Augmented Onboard Intelligence
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Black Swift Technologies, LLC
3200 Valmont Road, Suite 7
Boulder,CO 80301 -2887 (720) 638-9656
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jack Elston
elstonj@blackswifttech.com
2100 Central Avenue, Suite 102
Boulder ,CO 80301 -2887
(720) 933-4503

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The overall goal of the technology developed in this SBIR is to aid in enabling ubiquitous operations of UAS in the national airspace. This includes beyond-line-of-sight operations, flights over populated areas, and fully autonomous operations without direct human oversight. This overarching vision will require many new advancements such as collision avoidance capabilities, GPS denied navigation, and improvements in overall system reliability and robustness. The specific technology gap addressed in this SBIR is focused on improving reliability, subsystem failure tolerance, and automated diagnostics. The specific technical objectives of this Phase II include:

  1. Finalize and validate the design of the new subsystems including the actuator and battery monitoring nodes, the vision node, and the flight management node.

  2. Continued iterative design and testing of machine learning techniques for identifying failures and required maintenance as well as machine learning algorithms for safe landing detection. These will be built and improved using the new hardware and additional flight experiments.

  3. Bench-top testing and hardware-in-the-loop simulation of monitoring systems to gather training data, validate sensor selection, processing bandwidth, and algorithm implementation

  4. Implementation of new features in the current user interface to alert the operator in an intuitive manner of subsystem failures or required maintenance. This will be based on standards and concepts that have been proven in manned aircraft.

  5. Deployment of a customer-facing online portal to iteratively test and deploy algorithms in a commercial space using flight data.

  6. Validation of the full system through flight testing on the BST S2 aircraft with analysis on the achieved reliability metrics. This tasks will include early-on flight experiments to gather training data with certain features and failures along with testing of the full system to validate the overall performance towards the end of the Phase II project.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
BST aims to utilize the proposed monitoring technology to further lower the barrier of entry and reduce the risk of mission failure due to maintenance mistakes or user error during off nominal flight conditions. Increasing industry confidence in UAS technology is required to continue to grow the market. Furthermore increasing reliability will allow customers to operate increasingly expensive payloads. This will enable more advanced capabilities for UAS, growing the size of the potential market and leading to wider adoption by commercial operators and higher demand for the new capabilities by their customers. As an example, survey and GIS companies can regularly begin using sensors such as GPS RTK and scanning LIDAR without the fear of the prohibitively high cost associated with an accident. These specific sensors will create more demand; there are many areas that need 3D mapping where photogrammetry does not work well due to trees and other vegetation. Those areas are currently rarely serviced by UAS due to the high cost of the sensors. More reliable UAS are also essential for making a safety case with the FAA to allow new types of missions. Reducing failure likelihood due to consistent maintenance and improving flight anomaly detection and mitigation will be important factors in enabling beyond visual line of sight operations and eventually fully autonomous flights without direct human oversight. Many markets and missions will take advantage of these sorts of capabilities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
It is the goal of this technology to greatly reduce the amount of training and expertise needed to fly UAS, and enable operators such as NASA scientists to directly conduct field campaigns without sacrificing safety. Within NASA, this capability will allow wider adoption where UAS can be operated with less training, less focus on maintenance, and more focus on the data and information gathered by the aircraft. This will be enabled by automatically communicating the need for specific routine maintenance to the user. Furthermore, automated warnings and actions in the form of popup checklists on the user interface during flight will reduce the need for expert operators to be able to deal with these contingencies.

NASA also has a history of conducting new and difficult missions with UAS in challenging environments, such as the deployment of the Sierra UAS in the Arctic environment and the DragonEye to perform volcanic plume characterization. The proposed system will be designed to extend monitoring capabilities to new types of missions and reduce flight risks, such as the detection of aircraft icing using machine learning approaches. The small size of the proposed system will ensure this type of capability can then be employed in small UAS, enabling operations in areas that would historically be considered too risky. This will enable more frequent and capable flight campaigns for NASA Earth Science missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Hardware-in-the-Loop Testing
Diagnostics/Prognostics
Recovery (see also Autonomous Systems)
Air Transportation & Safety
Avionics (see also Control and Monitoring)
Autonomous Control (see also Control & Monitoring)
Intelligence
Algorithms/Control Software & Systems (see also Autonomous Systems)
Data Acquisition (see also Sensors)
Data Fusion


PROPOSAL NUMBER:17-2 A1.10-9734
PHASE-I CONTRACT NUMBER:NNX17CL48P
SUBTOPIC TITLE: Hypersonic Technology-Improvement in Solar Operability Predictions using Computational Algorithms
PROPOSAL TITLE: Non-Intrusive Computational Method and Uncertainty Quantification Tool for Isolator Operability Calculations
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corporation
701 McMillian Way Northwest, Suite D
Huntsville,AL 35806 -2923 (256) 726-4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ragini Acharya
ragini.acharya@cfdrc.com
701 McMillian Way, Suite D
Huntsville ,AL 35806 -2923
(256) 726-4800

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Computational fluid dynamics (CFD) technology plays a strong role in the design and development of aerospace and defense vehicles such as high-speed applications where testing under the correct operational conditions is not yet viable.  Despite decades of research towards making CFD predictive and reliable, it has not proven so due to the significant uncertainties in physical models, initial/boundary conditions, computational mesh, numerical schemes and methods. In the proposed effort CFDRC in partnership with Virginia Tech and UTSI, aims to directly address these issues by integrating dimensionally adaptive sparse grid uncertainty quantification (UQ) method with an existing reacting CFD solver. The proposers demonstrated this approach to be suitable for achieving this objective during Phase I on a NASA-LaRC nozzle-isolator lab-scale setup. The proposed effort will deliver a practical user-friendly automated software tool combining UQ with CFD (UQCFD), capable of identifying and characterizing regions of high-uncertainty in the CFD code and the associated work-flow, and thereby, provide guidance to the CFD modeler to increase fidelity of those regions. UQCFD software has the potential to make significant impact on a wide variety of application utilizing CFD predictions including design and development of next generation supersonic and hypersonic flight vehicles.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The work established in this project including the Uncertainty Quantification workflow process and automated software tool can be generalized for potential applications to a wide range of applications utilizing CFD software. More specifically, this work can be transitioned to support a significant number of other non-NASA applications where reacting CFD modeling tools are utilized. Energy and propulsion applications such as gas-turbine combustors, augmentors, rockets, and many others can benefit from the product developed in the proposed work.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-intrusive uncertainty quantification, that does not require the CFD code to be modified, has been identified as an enabling technology by NASA to advance the role of computational fluid dynamics codes in the Design Development Research and Engineering community developed by the aerospace industry, ultimately leading to utilization for flight certification. The proposed computational product offers a direct solution to link the various sources of uncertainties to predictions made by CFD tools, thereby enabling the usability of CFD tools for making risk-informed design decisions. The adaptive sparse grid method offers a significant advantage over other uncertainty quantification methods due to the ability to handle non-smooth system response with complex probability density distributions and much smaller number of required CFD simulations. This product can be a highly effective tool for wider applications requiring aerothermodynamics calculations where the lack of confidence in modeling parameters and predictive capability of the CFD codes has limited their impact.

TECHNOLOGY TAXONOMY MAPPING (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.)
Atmospheric Propulsion
Verification/Validation Tools
Aerodynamics
Air Transportation & Safety
Models & Simulations (see also Testing & Evaluation)
Quality/Reliability
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 A2.01-8831
PHASE-I CONTRACT NUMBER:NNX17CC85P
SUBTOPIC TITLE: Flight Test and Measurements Technologies
PROPOSAL TITLE: A Combined Health Estimation and Active Balancing Electronic System for the Life Enhancement of Batteries in Hybrid and/or All-Electric Propulsion Systems
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
X-wave Innovations, Inc.
555 Quince Orchard Road, Suite 510
Gaithersburg,MD 20878 -1464 (301) 355-0488
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Carlos Rentel
crentel@x-waveinnovations.com
555 Quince Orchard Road, Suite 510
Gaithersburg ,MD 20878 -1464
(301) 355-0488

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA seeks intelligent monitoring for hybrid and/or all electric propulsion systems, as well as methods to significantly extend the life of electric aircraft propulsion energy sources and their safety. The requirement to advance towards more fuel efficient and environmentally friendly aircrafts demands battery systems that can operate for longer periods of time in a safer and more reliable manner. An attractive technique that can be used to increase battery pack life is that of active balancing. Active balancing is typically used to increase the amount of energy put into or extracted out of a battery. If performed efficiently and accurately, active balancing can translate into longer battery life and more efficient battery utilization. Active balancers presently equalize either voltage or State of Charge (SOC) in a group of cells or super-cells in series. The more accurate in-operando SOC active balancers depend on on-line SOC estimation algorithms that are typically based on terminal voltage, current, and temperature. These algorithms (e.g., Coulomb counting, Kalman-based filter estimation, etc) accumulate errors and/or become unstable as a consequence of measurement errors, model simplifications, and the lack of an accurate battery parameter determination and tracking method, which is critical as the battery ages and/or operates under unforeseen conditions. To assist with this problem we propose to develop an active balancing electronic system that can jointly balance the battery pack and measure battery health related parameters without additional hardware. We propose to use this efficient electronic system to demonstrate an improved active balancing system capable of battery life enhancement and safety operation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system has many market applications in different industries such as exploration, defense, terrestrial hybrid and all-electric vehicles, unmanned vehicles, and energy sectors. Other government agencies, including DOD, DOE, DOT, and commercial sectors will benefit from this technology. Battery technologies are constantly being sought for renewable systems, such as solar, wind, and hybrid and electric vehicles. Besides propulsion systems batteries are used in commercial airplanes for auxiliary load support among others. Civilian efforts in Hybrid Propulsion Systems, such as Boeing SUGAR.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA has great interest in methods and approaches for intelligent monitoring and innovative techniques that enable extended and safer operation of aircraft with electric propulsion systems. NASA is specifically interested in battery life and health improvement methods for fuel-efficient and environmentally friendly aircrafts. This includes the development of systems capable of improving battery utilization and safety via prognostics and fault detection. Projects that can bemefit from this technology include: AATT, FDC, and TTT. Also NASA efforts within the Hybrid Electric Propulsion Systems

TECHNOLOGY TAXONOMY MAPPING (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.)
Spacecraft Main Engine
Diagnostics/Prognostics
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Condition Monitoring (see also Sensors)
Process Monitoring & Control
Conversion
Distribution/Management
Sources (Renewable, Nonrenewable)
Storage


PROPOSAL NUMBER:17-2 A2.01-8971
PHASE-I CONTRACT NUMBER:NNX17CD15P
SUBTOPIC TITLE: Flight Test and Measurements Technologies
PROPOSAL TITLE: Tunable Laser for High-Performance, Low-Cost Distributed Sensing Platform
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sequent Logic, LLC
3265 North 1950 East
North Logan,UT 84341 -2063 (435) 915-4425
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ryan Seeley
seeleyr@sequentlogic.com
3265 North 1950 East
North Logan ,UT 84341 -2063
(435) 915-4425

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposed effort will integrate identified performance optimization approaches to produce a tunable laser module exhibiting cost and performance characteristics appropriate for NASA’s needs. The technology will considerably improve NASA's flight test measurement and in-situ monitoring capability over the current state of the art, opening up new distributed sensing possibilities for real-time, in-situ airframe / space frame measurements. In addition to supporting distributed static strain and temperature measurements, the technology helps enable distributed modal analysis, non-destructive evaluation, and identification / characterization of transient events. With an improved understanding of distributed airframe / space frame structural dynamics, the technology will lead to improved airframe and component designs. With improved, integrated real-time feedback control signal generation and structural health monitoring, future aircraft and space-flight vehicles will operate more safely, predictably, and efficiently.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications of the technology include renewable wind energy, commercial aerospace & aviation, oil & gas, automotive, nuclear energy, and perimeter security. In wind energy, the technology could inform real-time turbine control decisions for enhanced power generation efficiency. In addition, the subject technology could be used to measure deterioration of blades over their operational lifetime and detect adverse conditions or damage events, informing condition-based maintenance schedules. Commercial aerospace companies would find use for the proposed technology in applications similar to those of NASA. In particular, real-time distributed thermal monitoring of critical propulsion and fuel-storage system components appears to be an excellent application for the technology. The technology would benefit commercial aviation applications by informing condition-based maintenance schedules to reduce operational cost and improve passenger safety. In automotive applications, the proposed technology could be used for real-time structural monitoring during road testing and/or crash testing. It could also be applied to thermal monitoring of electric vehicle battery banks.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology enables acquisition of real-time, in-flight strain and/or temperature data related to structural dynamics analysis and health monitoring of airframes and space frames. In addition, the technology enables feedback control signal generation, distributed NDE / modal analysis, and distributed thermal profiling. The technology can be applied to components, structures, aerodynamic surfaces, fixed and morphable flight control surfaces, and electrical propulsion system power sources. The proposed technology has particular applicability to laboratory and in-flight testing of airframes and space frames. Distributed strain measurements can be used to infer distributed loading throughout a structure, and can additionally be used to infer shape of a structure. Most notably, the technology opens up possibilities for distributed modal analysis, distributed resonance mapping, and other sensing modalities. The technology is particularly applicable to incredibly harsh shock/vibe environments such as the launch vehicle environment.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Measuring/Sensing)
Acoustic/Vibration
Interferometric (see also Analysis)
Optical/Photonic (see also Photonics)
Thermal
Lifetime Testing
Nondestructive Evaluation (NDE; NDT)
Diagnostics/Prognostics
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Condition Monitoring (see also Sensors)


PROPOSAL NUMBER:17-2 A2.01-9699
PHASE-I CONTRACT NUMBER:NNX17CD09P
SUBTOPIC TITLE: Flight Test and Measurements Technologies
PROPOSAL TITLE: Active Battery Management System with Physics Based Life Modeling Topology
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Electric Power Systems
4233 South Bedford Drive
Chandler,AZ 85249 -4597 (480) 416-2624
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Randy Dunn
randy.dunn@ep-sys.net
16125 E Gale AVe
Industry ,CA 91745 -1709
(714) 200-3209

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Robust Data Acquisition on flight applications enables Researchers to rapidly advance technology. Distributed Electric Propulsion (DEP) and Hybrid Electric architectures rely heavily on batteries to achieve fuel efficiency and reduced CO2 emissions. DEP Aircraft of the future have demands for Energy Storage Systems with large counts of cells put in series and parallel to achieve needed voltage and energy levels. The X57 Maxwell Battery comprises of over 6000 cells. As the pack goes through repeated charge/discharge cycles, as well as environmental cycles, each individual cell begins to lose its capacity. Advanced high energy density chemistries (>300Wh kg) are particularly vulnerable.  Cell to cell capacity variation causes the entire pack to be limited by the weakest cell. Traditional Passive Balancing topologies are limited in their ability to address cell mismatch on the discharge cycle. Active balancing allows a dynamic measurement & control system to discharge cells at variable rates. With a more robust measurement & control architecture, Active topologies have the ability to integrate more advanced algorithms. These algorithms include predictive health monitoring, life based management, physics based cell modelling. Batteries can last longer, avoid thermal runaway, and avoid maintenance. EPS is proposing development of an active BMS concept, with associated algorithms to achieve a 40% life improvement on the X57.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
All commercial aviation applications with a lithium ion battery have the ability to benefit from this research. No deployed Li-Ion battery system in Aviation today has an active topology. This is due to the stringent FAA DO311 requirements which require designers to show that their systems can meet a 1E-9 probability requirement of failed condition occurring such as overcharge. This is achieved through redundancy and the elimination of single point failures. With charge current being transferred from cell to cell, no one has achieved a cost effective design that meets the 1e-9 requirement. If the TRL is advanced on such a topology, the economics of lithium becomes much more compelling given the much improved cycle life. Other key markets who could benefit from Research would be the Air Taxi Manufacturers. Much of their business model is based on the economic properties of the battery. Right now cell manufacturers who are achieving the energy density targets for the application are no where near the cycle life requirement to make this market viable. This technology fills a critical gap in both cycle life and certification aspects.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This project is targeted for NASA's X-planes with lithium based energy storage systems. The X57 Maxwell is the target application, however, other X-planes, as well as Space applications may re-use the research to extend pack life, and avoid unpredicted Thermal Events. Vertical Take off & Lift working groups studying air taxi transportation.

TECHNOLOGY TAXONOMY MAPPING (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.)
Diagnostics/Prognostics
Algorithms/Control Software & Systems (see also Autonomous Systems)
Distribution/Management
Sources (Renewable, Nonrenewable)
Storage


PROPOSAL NUMBER:17-2 A2.02-8755
PHASE-I CONTRACT NUMBER:NNX17CA52P
SUBTOPIC TITLE: Unmanned Aircraft Systems Technology
PROPOSAL TITLE: Developing a Certifiable UAS reliability Assessment Approach Through Algorithmic Redundancy
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Systems Technology, Inc.
13766 Hawthorne Boulevard
Hawthorne,CA 90250 -7083 (310) 679-2281
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Danowsky
bdanowsky@systemstech.com
13766 Hawthorne Blvd.
Hawthorne ,CA 90250 -7083
(310) 679-2281 Ext: 128

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Integration of Unmanned Aerial Systems (UAS) into the US National Airspace (NAS) is crucial for advancement of UAS applications in different fields like transport, surveillance, disaster management, and geospatial applications. Airworthiness certification by the Federal Aviation Administration (FAA) is a critical step towards NAS integration. To match the expected FAA safety and reliability standards for UAS certification, novel technologies are needed. Conventional manned air vehicles meet FAA standards via hardware redundancy, an option unavailable for UAS due to size, weight, and power constraints. This challenge was addressed in Phase I via the so-called algorithmically redundant approach, where multiple fault detection and isolation algorithms work in parallel to detect faults more reliably. Using FAA-approved procedures like fault tree analysis or failure modes and effects analysis, reliability of algorithmically redundant systems is computed. This approach will be extended in Phase II to include flight control system hardware and control laws in the loop, and will involve validation via flight testing. A comprehensive methodology and accompanying software toolbox will result: STI Approach for Fault Estimation and Reliability for UAS (SAFER-UAS). SAFER-UAS is an overall reliability estimation approach based on theoretical analysis, simulation runs, and flight tests, serving as a vital step toward certification.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The UAS industry is experiencing rapid growth the private sector. The low-altitude (200-500 ft.) drone industry is expected to grow rapidly in the coming years with the emergence of new autonomous UAS applications including package delivery, infrastructure inspection, and environmental and agricultural monitoring. It is well-known that Amazon is pursuing the use of UAS for package delivery and a successful demonstration of this was achieved in late 2016. At higher altitudes, emerging commercial UAS technologies include high-altitude communications relay systems for expanding internet access to remote areas. Both Google and Facebook are pursuing this technology and have purchased the companies of Titan Aerospace and Ascenta respectively. The proposed SAFER-UAS Toolbox will be beneficial for ensuring that new UAS in all of these applications will be safely integrated with less required hardware redundancy, reducing required size, weight, and power (SWaP), and increasing achievable performance bounds.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed STI Approach for Fault Estimation and Reliability for UAS (SAFER-UAS) Toolbox directly addresses three strategic thrusts in the current NASA ARMD Strategic Implementation Plan. Thrust 1: "Safe, Efficient Growth in Global Operations" is addressed by a sustained focus on reducing UAS risks to maintain acceptable safety levels for all air traffic. Thrust 5: "Real-time, System-Wide Safety Assurance" is addressed by the developed analytic technique that mitigates UAS risks toward integrated, system-wide safety assurance. Thrust 6: "Assured Autonomy for Aviation Transformation" is addressed by the innovative FDI framework that will better enable safe integration of UAS into the NAS. Additionally, NASA is addressing air traffic management for low-altitude drones by developing a system to ensure safe UAS entry into this airspace. This rapidly growing industry includes emerging UAS applications such as package delivery, infrastructure inspection, and environmental monitoring. The SAFER-UAS toolbox will benefit this system by providing safety assurance.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Diagnostics/Prognostics
Recovery (see also Autonomous Systems)
Air Transportation & Safety
Algorithms/Control Software & Systems (see also Autonomous Systems)
Condition Monitoring (see also Sensors)
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 A2.02-9133
PHASE-I CONTRACT NUMBER:NNX17CA38P
SUBTOPIC TITLE: Unmanned Aircraft Systems Technology
PROPOSAL TITLE: Low-Power, ultra-Fast Deep Learning Neuromorphic Chip for Unmanned Aircraft Systems
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mentium Technologies Inc.
2208 Pacific Coast Drive
Goleta,CA 93117 -5494 (805) 617-6245
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Farnood Merrikh Bayat
farnoodmb@mentium.tech
2208 Pacific Coast Drive
Goleta ,CA 93117 -5494
(805) 708-4652

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Artificial Intelligence realized through Machine Learning algorithms seems to be the only viable solution to implement perception, enable pilot assistants and eventually full autonomy to UAS. Currently, many UAS have some kind of conventional Computer Vision (CV) helping them in obstacle avoidance or target acquisition. Interestingly though, since 2012 Deep Neural Networks (DNN) have dramatically outperformed conventional CV algorithms in those tasks and pushed Artificial Intelligence (AI) limits in a variety of other applications including, but not limited, to object recognition, video analytics, decision making and control, speech recognition, etc. Unfortunately, the computational power required for real-time DNN operation can still only be delivered by bulky, expensive, slow, heavy and energy-hungry digital systems like GPUs.

This is why Mentium  is devoted to delivering disruptive technology in the field of Machine Learning hardware accelerators, and in particular for this project, into the Deep Learning Hardware Accelerators field. Experimental data and Phase I results confirm that our hardware can deliver 100x to 1000x gain in speed and in power efficiency compared to other state-of-the-art accelerators. Our final product will be able to analyze, in real-time, big data streams coming from cameras, sensors and/or avionics and to categorize (classify) them for the purpose of decision making or object localization to achieve better navigation and collision avoidance in UAS. The same hardware processor will be deployable in the Air Traffic Systems, for real-time data analysis and decision-making. All with more than 10x reduction in cost and power consumption. This distruptive technology is based on an analog-computational core, exploiting the memory devices to carry out the computation at a physical level. Analog computation is inherently faster and more efficient than the digital one, while the in-memory computation removes the data transfer bottleneck.

 

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our final product will be attractive both for the private sector and the federal market as well.
As for the private sector, the Outcome if this SBIR project can be directly injected into the commercial UAV market, both for consumer and for executive applications.
Nevertheless, it is important to consider that with very few modifications our hardware accelerator could be used in:
- Industry intelligence (through visual, audio and sensors inputs)
- Cybersecurity
- Enterprises Big Data analytics
- Security cameras
- Automotive

Moreover, number of other federal agencies could be interested in our product, here is a list of the majors:
- EPA, Environmental Protection Agencies
- USDA, Department of Agriculture
- DHS, Department of Homeland Security
- DoD, Department of Defense
- NOAA, National Oceanic and Atmospheric Administration
- DoE, Department of Energy
- DoT, Department of Transportation

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We can easily envision our Deep Learning Accelerator deployed in the following NASA's Candidate Mission Products from Thrust 6 Roadmap:
- Autonomy-Enabled UAS for Earth Science
- Autonomy-Enabled Air Traffic Management
- Autonomy-Enhanced Vehicle Safety
- Inflight Vehicle Performance optimization
- Complex Decision-Making UAS

We want also emphasize that the final applications scope is wider than the Aeronautics Directorate, since the same architecture can be optimized for radioactive environments and deployed in space.

TECHNOLOGY TAXONOMY MAPPING (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.)
Recovery (see also Autonomous Systems)
Avionics (see also Control and Monitoring)
Autonomous Control (see also Control & Monitoring)
Intelligence
Man-Machine Interaction
Perception/Vision
Algorithms/Control Software & Systems (see also Autonomous Systems)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Image Analysis
Data Processing


PROPOSAL NUMBER:17-2 A3.01-8685
PHASE-I CONTRACT NUMBER:NNX17CA17P
SUBTOPIC TITLE: Advanced Air Traffic Management Systems Concepts
PROPOSAL TITLE: Collective Inference Based Data Analytics System for Post Operations Analysis Phase II
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ATAC
2770 De La Cruz Boulevard
Santa Clara,CA 95050 -2624 (408) 736-2822
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Bertino
jlb@atac.com
2770 De La Cruz Blvd
Santa Clara ,CA 95050 -2624
(408) 736-2822 Ext: 252

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This SBIR research provides a significant improvement over current-day post operations analysis (POA) with significant commercialization potential. In Phase I, ATAC developed a machine learning based aviation POA decision support tool (DST), which improves the state of the art of today’s airline, airport and FAA POA processes by providing automated, results-oriented POA outcomes. We provided a proof-of-concept for this POA DST by demonstrating how the Phase I prototype allows airline, airport and FAA personnel at the Charlotte Douglas International Airport (CLT) to perform faster, more efficient and results-oriented post analysis of individual departure banks to obtain actionable operational insights. Encouraged by our promising proof-of-concept demonstrations in Phase I, we propose to carry forward this research in Phase II of our SBIR project towards the eventual goal of developing a commercial licensable Cloud-based POA Platform that can be accessed by NASA, FAA, airline, airport or other commercial systems or personnel in a “Platform-As-A-Service” (PAAS) mode. This proposed capability provides a one-stop platform for gate-to-gate, complete POA including aviation data acquisition, storage, analytics, and root cause diagnosis, in a post-analysis mode as well as a real-time, continuous operations monitoring mode. The proposed continuous operations monitoring mode accelerates operations analysis work related to NASA’s ATD-2 project. The proposed second airspace focused use case supports multiple NASA research programs, including ATD-2's CLT to Northeast corridor (NEC) departure flow operations analysis, IDM NEC enroute constraints analysis, ATD-3 weather-efficient routing analysis and System Wide Safety anomaly detection. Moreover, by providing the ability to perform results-oriented POA on diverse operations (UAM, IDO), the SBIR enables the future NAS to rapidly learn from operational inefficiencies, and improve new traffic management and operations paradigms.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The main commercial application for the proposed technology is as a DST to be used by operational and/or analytical personnel at airlines, ANSPs, or airports, (or by aviation consultants) for analyzing root causes for observed operational efficiencies or irregularities at the end of a day of operations at key airports and airspaces. The CIDAS-P collective inference engine will enable staff to differentiate the impacts of factors under their control versus not under their control, to assist in improved operational decision-making around operational procedures, and technology and resource investments. Airline uses include better analysis of irregular operations responses, improved analysis of airline network-wide flight scheduling and management, fleet mix choices, gate turnaround, gate pushback, and non-movement area operations, diversions and cancellations, and competitive airline performance. In the case of airports, uses include the analysis of the impact of airport construction schedules, departure metering operations, and general management of gate turnaround, gate pushback and non-movement area operations. In addition, specific ANSP-focused applications include: (1) a Trajectory-based Operations (TBO) benefits analysis and monitoring capability, (2) an operational analysis tool focused on measuring the impact of ATM DSTs for departure metering, weather rerouting, and arrival metering, (3) NAS weather impact analysis tool, and (4) a post-operations TFM evaluation system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The CIDAS-P technology has application across multiple NASA projects. CIDAS-P's automated, results-oriented post operations analysis (POA) complements ongoing ATD-2 CLT operations analysis efforts. Phase II continuous ops monitoring and NEC surface-airspace ops analysis capabilities support development of ATD-2's Strategic Scheduling component, and accelerates progress towards the next phase of ATD-2. CIDAS-P collective inference analysis on weather-driven en route rerouting scenarios can accelerate evaluation and continuous improvement of ATD-3 rerouting technologies. ATM-X's IDM research will benefit by leveraging CIDAS-P as a reliable, results-oriented method for evaluating the effectiveness of enroute TBFM-TFMS coordination strategies. CIDAS-P's airline ops analysis use case supports NASA Airline Operations Research Group (AORG) in its objective of infusing NASA-funded technologies into airline tools. CIDAS-P can also significantly improve System Wide Safety (SWS) project's anomaly detection algorithms, by providing reliable, automated collective inference based guidance on whether the identified safety alerts are false positives or missed safety alerts. Research into future diverse operations (UAM, IDO) also stands to benefit by CIDAS-P enabled continuous operations improvement guidance. Working software prototypes and collective inference algorithms can be incorporated into NASA software analysis platforms such as DASH, SMART-NAS testbed, FACT, or FACET.

TECHNOLOGY TAXONOMY MAPPING (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.)
Air Transportation & Safety
Analytical Methods
Algorithms/Control Software & Systems (see also Autonomous Systems)
Sequencing & Scheduling
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Computer System Architectures
Data Fusion
Data Modeling (see also Testing & Evaluation)
Data Processing


PROPOSAL NUMBER:17-2 A3.01-9556
PHASE-I CONTRACT NUMBER:NNX17CL95P
SUBTOPIC TITLE: Advanced Air Traffic Management Systems Concepts
PROPOSAL TITLE: Turbulence Awareness for Strategic Aircraft Re-Routing (TASAR-R)
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The Innovation Laboratory, Inc.
2360 SW Chelmsford Avenue
Portland,OR 97201 -2265 (503) 242-1761
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jimmy Krozel
Jimmy.Krozel@gmail.com
2360 SW Chelmsford Ave.
Portland ,OR 97201 -2265
(503) 242-1761

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 1
End: 2

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

We develop a system composed of two displays, one for the Flight Deck (FD) and one for the Airline Operational Control (AOC) dispatcher.  The FD and AOC displays form a shared situational awareness of the different forms of turbulence hazards that are ahead of the aircraft.   A wide range of turbulence measurement, sensing, and forecasting systems are available, and we determined the most appropriate for aviation weather hazards originating from convective induced turbulence, mountain wave turbulence, and clear air turbulence.  The FD and AOC displays are used to exchange candidate flight plan amendments that can mitigate the turbulence weather hazards ahead of the aircraft, meeting the additional requirements known to the FD or the AOC.  Agreement from both the FD and AOC is required to thereafter file the flight plan amendement with the air traffic service provider.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
PASSUR Aerospace will partner with us on the Phase II effort in order to demonstrate the FD PED integrated with the AOC dispatcher workstation. In particular, we design the Phase II system to integrate with the PASSUR Web Tracker flight monitoring system to create a shared situational awareness and coordinated mitigation strategy.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The supporting sources of data, data transformations (including polygonalization), integration into EFB and PED displays for the FD, display features, and coordination of mitigation strategies has direct application into the NASA Traffic Aware Strategic Aircrew Requests (TASAR) Traffic Aware Planner (TAP) software system. The SBIR software will also be useful in Human in the Loop experiments at NASA.

TECHNOLOGY TAXONOMY MAPPING (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.)
Air Transportation & Safety
Navigation & Guidance
Condition Monitoring (see also Sensors)


PROPOSAL NUMBER:17-2 A3.02-8684
PHASE-I CONTRACT NUMBER:NNX17CA18P
SUBTOPIC TITLE: Autonomy of the National Airspace Systems (NAS)
PROPOSAL TITLE: NAS Element Closure Planner
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ATAC
2770 De La Cruz Boulevard
Santa Clara,CA 95050 -2624 (408) 736-2822
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Keller
wjk@atac.com
2770 De La Cruz Blvd
Santa Clara ,CA 95050 -2624
(408) 736-2822 Ext: 602

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

We propose a NAS Element Closure Planner, wherein the tool may be used to plan airspace closures and/or combined airport surface and airspace closures in advance, in addition to the exclusive airport surface closures. The proposed technology applies concepts from statistical modeling and machine learning to reliably predict likely future evolution of airport traffic as well as the evolution of other influencing factors such as runway capacity over time. A machine learning tool will drive multiple what-if analysis simulations, each with a slightly modified “initial condition” which may be defined by flight simulation start times (i.e., gate pushback times) as well as allocated taxi routes. Multiple simulations, each driven by one set of initial conditions will be run for each closure time-window option being investigated. Thereby, for each closure time-window option, we will obtain not just one but a distribution of performance metrics, which is a more realistic estimate of likely performance as opposed to a single point value. This ability to reliably predict future performance and the uncertainty associated with it, is a significant step up from the predictive analytics that are available today to airport airside operations staff. The technology would also be applied to determine the multiple futures of closing airspace for any variety of common reasons that would include a commercial space launch use case.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Direct FAA-related post Phase II applications for NECP include: (1) an analysis tool focused on the assessment of airport construction impacts, (2) a Trajectory-Based Operations (TBO) benefits analysis tool, (3) a platform to support collaborative airline-ANSP decision making around adverse weather based airspace closures, (4) a UAS airspace impact analysis tool, and (5) a Commercial Space Launch impact analysis tool set. ATAC is in active discussions with potential FAA customers in the FAA NextGen and Air Traffic Organization (ATO) on related support projects. We plan to leverage these contacts to showcase NECP's novel collaborative decision making and analytical capabilities and promote the FAA's adoption of NECP for the above applications. In addition, airlines are often adversely impacted by airport movement area closures and/or airspace closures and the changing nature of the NAS. Integration of increasing numbers of UAS as well as Commercial Space Launches increase the imperative of developing novel and efficient ways of dealing with these disruptions. NECP provides the airlines and/or airports with a reliable data-driven approach to collaboratively plan, analyze, predict, notify, and execute such closures. Each organization can also tailor its NECP platform to additionally provide metrics that measure impact on their own corporate, network-wide operations or business objectives, and then help drive agreement on the solution(s) that best fit stakeholder goals.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NECP, by extending its planning domain to cover closures of airspace regions, provides a capability that will be beneficial to the new NASA programs that address the management of new types of air traffic (e.g., UASs, Commercial Space Operations (CSO), Urban Air Mobility (UAM) operations). Gaining predictive insight to unregulated airspace and relationships to currently regulated airspace that a UAS/CSO/UAM vehicle routing may transit is not currently afforded by any platform. NECP is relevant to the NASA ATM Technology Demonstration-2 (ATD-2) subproject in which NASA plans to address current-day surface traffic management shortfalls by demonstrating Integrated Arrival, Departure, Surface (IADS) scheduling technologies and transitioning them for field-implementation. NASA's ATD-2 technologies are expected to become critical parts of the FAA's NextGen Terminal Flight Data Manager (TFDM) capability, deploying surface traffic management solutions at NAS Air Traffic Control Towers (ATCTs). At winter weather impacted airports, the deployed TFDM/ATD-2 technologies will benefit from our proposed NECP DST to improve decision-making during runway closures. NASA's AORG is gaining a better understanding of winter storm effects on NAS operations (especially airports) and developing knowledge and tools to reduce cancelations and delays. Our innovation has been included within the FACT program and supports these capabilities by enabling improved decision-making during runway closures.

TECHNOLOGY TAXONOMY MAPPING (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.)
Air Transportation & Safety
Analytical Methods
Algorithms/Control Software & Systems (see also Autonomous Systems)
Sequencing & Scheduling
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Computer System Architectures
Data Fusion
Data Modeling (see also Testing & Evaluation)
Data Processing


PROPOSAL NUMBER:17-2 A3.02-9829
PHASE-I CONTRACT NUMBER:NNX17CL38P
SUBTOPIC TITLE: Autonomy of the National Airspace Systems (NAS)
PROPOSAL TITLE: Predictor of Airport Runway Capacity (PARC)
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Architecture Technology Corporation
9971 Valley View Road
Eden Prairie,MN 55344 -3586 (952) 829-5864
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sebastian Timar
stimar@atcorp.com
910 Campisi Way, Suite 2D
Campbell ,CA 95008 -2337
(408) 819-9200 Ext: 105

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The Predictor of Airport Runway Capacity (PARC) is a decision support tool for air traffic managers to estimate the near-term capacity of the individual runways of an airport for traffic planning and control. To estimate runway capacity, PARC analyzes historical data describing an airport’s traffic movements, operating conditions, operating procedures, and geospatial data to determine the time intervals between successive aircraft using an airport’s runway and variables that influence it. Variables may include facility, aircraft, flight plan and weather conditions. Second, PARC uses the data to construct Bayesian Network (BN) statistical models of the joint probability of inter-aircraft time spacing and the variables for each airport’s runway. Third, PARC performs Monte-Carlo simulations of the traffic planned to use each runway, sampling the BN models to estimate the spacing of successive takeoff, landing and taxi crossing aircraft, to obtain a distribution of possible runway capacities. Fourth, PARC selects a a target runway capacity from the distribution for airport traffic management. The advantages of PARC are adapting to the characteristics of the airport and accounting for the anticipated operating conditions to provide accurate estimates of runway capacity. Phase I demonstrates processing of FAA System Wide Information Management (SWIM) traceable data sources for modeling for 1-year of data for Atlanta-Hartsfield International Airport (KATL). Phase I uses the data to constructs BN models of inter-aircraft time spacing and to validate the models. Phase I demonstrates the greater accuracy of the BN models in representing and predicting inter-aircraft time spacing than a simpler single-event probability model. Phase I demonstrates sampling of the BN models for different airport, aircraft and flight plan conditions to obtain inter-aircraft spacing values to be used in Monte-Carlo simulations for capacity prediction.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
PARC could be a decision support tool for FAA Airport Tower Controllers to plan airport runway configurations and utilizations (e.g., dedicated versus shared, arrival-departure capacity allocations for shared runways). PARC could be a decision support tool for FAA Air Route Traffic Control Centers (ARTCCs) and the Air Traffic Control System Command Center (ATCSCC) to estimate the arrival capacities of US airports for anticipated operating conditions for demand-capacity balancing. PARC could be a tool for FAA Airport Tower Controllers to compare in real-time spacing measured from airport surveillance and infrastructure data to modeled spacing and alert of anomalies. PARC could be used by the airport authority, airline or airlines, or a third party to manage surface traffic in the non-movement area of the airport including planning and control of movement area exits and entries, gate assignments, departure reservoirs. PARC could be implemented as an analysis tool for airport consulting agencies to use in airport master planning. Specifically, PARC would be used to estimate the airport runway capacities for numerous operating conditions and compare the capacities to anticipated traffic to determine the need for modifications to, or addition of, runways to increase capacity. PARC could be used to compute and compare the effective and theoretical capacities of an airport?s configurations for efficiency assessment and traffic management.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
PARC could be used by the NASA Airspace Technology Demonstration-2 (ATD-2) traffic scheduling to compare the throughput implied by scheduled runway operations to runway capacity as per operating conditions. Specifically, if tactical runway schedules are constructed to meet minimum statutory spacing requirements, PARC could assess whether the resulting schedules comply with appropriate or typical spacing buffers. PARC could be used in other ATD-2 decision support and real-time control tools to support planning and management of airport runway configuration; allocation of runway capacity to arrivals, departures and crossing runway traffic; and/or metering of airport traffic for macroscopic Traffic Flow Management (TFM) or finer-grained Time-Based Flow Management (TBFM) applications. Specifically, PARC could estimate airport runway capacities for runway configuration planning, traffic metering and management, and demand-capacity balancing. PARC could be used in the ATD-2 system to assess in-trail separations of aircraft at the runway (measured from surveillance data) and alert controllers to occurrences of excessively small spacing values of low-probability, indicating a shift in the operating characteristics to be addressed. PARC could be used to estimate airport runway and airport-wide arrival and departure capacity values for modeling and simulation of traffic under different operating conditions for concept and technology research and development activities.

TECHNOLOGY TAXONOMY MAPPING (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.)
Autonomous Control (see also Control & Monitoring)
Man-Machine Interaction
Command & Control
Process Monitoring & Control
Characterization
Software Tools (Analysis, Design)
Data Fusion
Data Modeling (see also Testing & Evaluation)
Data Processing
Transport/Traffic Control


PROPOSAL NUMBER:17-2 A3.03-8309
PHASE-I CONTRACT NUMBER:NNX17CA48P
SUBTOPIC TITLE: Future Aviation Systems Safety
PROPOSAL TITLE: Detecting Anomalies by Fusing Voice and Operations Data
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Robust Analytics
2053 Liza Way
Gambrills,MD 21054 -2007 (410) 980-3667
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Peter Kostiuk
peter.kostiuk@robust-analytics.com
2053 Liza Way
Gambrills ,MD 21054 -2007
(410) 980-3667

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Robust Analytics team will add real-time speech-to-text (STT) monitoring of controller-pilot radio communications to the risk state analytical framework previously demonstrated by Robust Analytics. The combination of our successful Phase I application of STT to ATC communications with the risk state analysis data fusion and analytical framework will provide a real-time risk and safety margin monitoring capability for the NAS.

Adding voice communications monitoring remains crucial for achieving NASA’s system-wide safety monitoring goals. Voice is still the main source of ATC-pilot communications and a large body of airspace situational awareness and operationally-related information is contained therein that never makes it effectively back into broader National Airspace Systems (NAS) use. Our innovation provides access to that information, in real-time, and with the built-in analytics to use that information to identify anomalies and provide alerts. When combined with the other factors included in our risk state assessment framework, our innovation would have identified recent crashes such as Asiana 214 and UPS 1354 as high risk flights, before the events occurred.

Robust Analytics offers a vision for NAS-wide, real-time safety monitoring based on analyzing controller-pilot voice communications for anomalies and clearance deviations, and combining that insight with information from other data sources (flight plans, position reports, weather, infrastructure status, and traffic density) through advanced analytics with cloud computing for a scalable, reliable 24/7 solution.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In the near term, we envision our innovation used by FAA facility shift supervisors to provide insight into potential risks. After additional validation, our innovation can provide alerts to controllers for flights deviating from clearance instructions.
Preliminary discussions with airline decision support tool providers suggest interest in a version of ILSA that would operate in the AOC to provide real-time and prognostic support to dispatchers. The concept is to provide dispatchers with current and predicted information on airspace and aircraft risk status. This information, combined with data on crew and aircraft assignments from AOC information systems, can alert the dispatcher that, for example, a crew operating at the end of a long flight may be entering a region of medium or high risk. The value of this combined information is indicated by the two most aircraft rashes that occurred when the crews were flying non-normal times (0600 hours or at the end of a long trans-Pacific flight) with the ILS out, and in the UPS case with degraded weather.
Operators and controllers report on recurring congestion in subsectors that cause inefficient deviations from planned routes. These inefficiencies do not typically get reported to the ATSCC and thus do not get de-conflicted in the planning process. Both the FAA and airlines would benefit from our system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Our ILSA innovation offers a direct contribution to meeting NASA's strategic objective for real-time safety assurance. We provide a robust, extensible approach to achieve the technical challenge for terminal area safety margin monitoring. With speech-to-text capability, we add another tool to identify operational anomalies in real-time, and a continuous monitoring system that generates a new source of data for NASA safety analyses. Our risk state analytical framework offers the SWS Project a platform for testing and deploying new anomaly detection algorithms that will be developed with the new voice transcription database we will generate.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Air Transportation & Safety
Data Processing


PROPOSAL NUMBER:17-2 A3.03-8665
PHASE-I CONTRACT NUMBER:NNX17CL65P
SUBTOPIC TITLE: Future Aviation Systems Safety
PROPOSAL TITLE: HATIS: Human Autonomy Teaming Interface System for UTM Risks Management
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Human Automation Teaming Solutions, Inc.
20944 Sherman Way, Suite 211
Canoga Park,CA 91303 -3643 (818) 912-6166
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Walter Johnson
walt.johnson@hatssolutions.com
20944 Sherman Way, Suite 211
Canoga Park ,CA 91303 -3643
(818) 912-6166

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

UTM is a key NASA initiative, and one of UTM’s key thrusts is to ensure safe usage of UAS. Technologies which can be used for real-time risk assessment of UAS flights are being developed by UTM Safety researchers, but there is currently no user interface to connect these technologies with the UTM managers and/or UAS operators. We propose to develop a human autonomy teaming interface system (HATIS) composed of specialized tools, multimodal interfaces, and human autonomy teaming software, which will permit human operators and UTM/UAS automation to collaborate for real-time risk management and mitigation (RMM). In Phase I, we collaborated with NASA to identify hazard categories and UTM RMM roles and automation capabilities; developed high-level system requirements and a system architecture along with three test cases; demonstrated a proof-of-concept with interactive mockup interfaces; and validated HATIS potential as a product for key market segments, including NASA labs conducting research in human autonomy teaming (HAT), landfills conducting  real-time environmental monitoring and reporting, and UAS manufacturers. In Phase II, we will spiral the development in HATIS in two builds: 1) HATIS1, which includes both building basic interfaces that allow the operator to visualize risks and collaborate with the automation to manage risks, and conducting the first integrated test and evaluation with usability and software; and 2) HATIS2 which includes extending HATIS to include level-of-automation management, play-based control, voice interaction, and conducting the second integrated test and evaluation with usability, software, and interoperability. We will implement a comprehensive risk mitigation plan that involves creating emulators of UTM RM algorithms and testing with these emulators if direct testing with RM algorithms is infeasible, and incorporating NASA input in preliminary and critical design reviews throughout each build.    

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
HATIS associated support services will fulfill needs of several organizations. The first group will be landfills that could use a network of drones for real time environmental monitoring and reporting. The second group will be companies that build UAS (e.g., Northrop Grumman, Aerovironment, General Atomics, Boeing) and manufacture UAS avionics systems (e.g., Honeywell, L3). As these organizations develop new technologies and new concepts of operations, they will need software such as HATIS integrated into their ground control station in order to rapidly conduct risk-evaluations of their ConOps. The third group is made up of DoD labs researching and developing human machine teaming applications (e.g., the Air Force's Autonomous Wingman, the Army's Air Mission Commander, and the Navy's Autonomous Swarmboats). HATIS will facilitate research on important topics such as trust, transparency, and function allocation between human and automation. The fourth group are: a) companies that have developed UAS technologies or systems for package delivery or emergency response applications (Google, Amazon); and b) cargo companies that may use UAS to transport cargo (UPS, FedEx). These companies will need to conceive, design, build, and test specific UAS, GCSs and ConOps to expand their business operations and markets. As with small UAS manufacturers, these organizations will also provide a market for actual multi-UAS GCSs. And again, HATS Inc. will be able to fill this need.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications of HATIS span four NASA directorates. In the ARMD, HATIS can provide programs such as UTM, UAS-in-the-NAS, and SMART-NAS with an interface system that allows the operator to team with the UTM automation to evaluate (via live virtual constructive distributed environments) and manage risks associated with flying UAS in terminal and congested airspace. In the HEOMD, HATIS can be integrated into human-system interaction subsystems that enable crew and ground controllers to better supervise robots in space exploration mission. Such integration would enhance the management of risks associated robots working remotely in space. In the STMD, HATIS can be augmented with human-swarm interaction interfaces for controlling a multi-agent system as an ensemble. Such augmentation would enable the operator to visualize the risks and work collaboratively with the swarm automation to manage the risks associated with the swarm operations. In the SMD, HATIS dynamic function allocation capability and play-based control can be a valuable asset for astronauts to use augmented reality systems to carry out procedures through various sensory modalities, reduce dependency for ground support, enhance situational awareness, and reduce cognitive overload while performing complex tasks.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Diagnostics/Prognostics
Recovery (see also Autonomous Systems)
Air Transportation & Safety
Autonomous Control (see also Control & Monitoring)
Man-Machine Interaction
Recovery (see also Vehicle Health Management)
Robotics (see also Control & Monitoring; Sensors)
Command & Control
Models & Simulations (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 A3.03-9117
PHASE-I CONTRACT NUMBER:NNX17CL96P
SUBTOPIC TITLE: Future Aviation Systems Safety
PROPOSAL TITLE: Turbulence Awareness via Real-Time Data Mining
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The Innovation Laboratory, Inc.
2360 Southwest Chelmsford Avenue
Portland,OR 97201 -2265 (503) 242-1761
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jimmy Krozel
Jimmy.Krozel@gmail.com
2360 SW Chelmsford Ave.
Portland ,OR 97201 -2265
(503) 242-1761

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Automatic Dependent Surveillance - Broadcast (ADS-B) has been mandated by the FAA for all aircraft that fly in Class A airspace in year 2020 and beyond.  ADS-B will be the foundation of surveillance, and in this SBIR effort, we exploit the fact thta ADS-B data can also provide evidence of aircraft flying through known sources of aviation turbulence. Phase I R&D showed that moderate or greater levels of turbulence can be identified by analyzing in real-time certain key features observable from ADS-B data.  Mountain wave turbulence, clear air turbulence, and convective induced turbulence events can all be identified from the data mining approach that we have developed.  Analysis results can be performed in near real time and in an automated fashion, and can trigger safety alerts on AOC dispatcher displays or can be used to build better turbulence forecasts and nowcasts.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
To complete the commercialization of this SBIR technology, The Innovation Laboratory, Inc and PASSUR Aerospace are partnering on the development and deployment of this SBIR technology into existing PASSUR product lines, including an existing network of ADS-B sensors as well as airline dispatcher workstation displays.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
For a decade, NASA has researched how to incorporate weather hazards into Air Traffic Management (ATM) Decision Support Tools (DSTs) and how to establish a shared situational awareness of such hazards with ATM, the Flight Deck (FD), and airline dispatchers. This SBIR effort will have infusion in NASA ATM research, human in the loop experiments, FD displays, and tactical flight planning systems. With ADS-B as the foundation of surveillance for 2020 and beyond, this technology is a natural fit into the foundational research being performed in shared traffic and situational awareness.

TECHNOLOGY TAXONOMY MAPPING (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.)
Air Transportation & Safety
Analytical Methods
Condition Monitoring (see also Sensors)
Data Acquisition (see also Sensors)


PROPOSAL NUMBER:17-2 H1.01-9111
PHASE-I CONTRACT NUMBER:NNX17CC81P
SUBTOPIC TITLE: Mars Atmosphere Acquisition, Separation, and Conditioning for ISRU
PROPOSAL TITLE: ISRU CO2 Recovery
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TDA Research, Inc.
12345 West 52nd Avenue
Wheat Ridge,CO 80033 -1916 (303) 422-7819
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gokhan Alptekin
krhodus@tda.com
12345 West 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)

Human exploration of Mars and unmanned sample return missions can benefit greatly from the resources available on Mars.  The first major step of any Mars in-situ propellant production system is the acquisition of carbon dioxide and its compression for further processing. 

 

TDA Research Inc. proposes to develop a compact, lightweight, advanced sorbent-based compressor to recover high-pressure, high purity CO2 from the Martian atmosphere. The system eliminates the need for a mechanical pump, increasing the reliability with relatively low power consumption. TDA’s system uses a new, high capacity sorbent that selectively adsorbs CO2 at 0.1 psia and regenerates by temperature swing, producing a continuous, high purity CO2 flow at pressure (> 15 psia). 

In the Phase I work, we successfully completed bench-scale proof-of-concept demonstrations, elevating the TRL to 3. In Phase II, we will further optimize the sorbent and scale-up its production using advanced manufacturing techniques such as continuous microwave synthesis.  We will carry out multiple adsorption/desorption cycles to demonstrate the sorbent's cycle life.  Finally, we will design and fabricate a sub-scale prototype to fully demonstrate the technology under simulated Martian atmospheres (TRL-5); this unit will be sent to NASA for further testing and evaluation.

POTENTIAL NASA COMMERCIAL 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- and natural gas-fired power plants. If regulations are put in place this market could develop in to billions of dollar. It is also applicable to CO2 removal from biogas, natural gas, and the water-gas-shift reaction in hydrogen manufacturing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The main attraction of our research to NASA is its ability to provide a lightweight, compact and energy efficient adsorbent based solid-state CO2 compressor system to collect and pressurize CO2 from the Martian atmosphere. The sorbent developed will also find application as a CO2 control system for commercial space craft cabin air revitalization and space suit.

TECHNOLOGY TAXONOMY MAPPING (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.)
Resource Extraction
In Situ Manufacturing


PROPOSAL NUMBER:17-2 H1.01-9317
PHASE-I CONTRACT NUMBER:NNX17CP22P
SUBTOPIC TITLE: Mars Atmosphere Acquisition, Separation, and Conditioning for ISRU
PROPOSAL TITLE: High Capacity Multi-Stage Scroll Compressor for Mars Atmosphere Acquisition
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Air Squared, Inc.
510 Burbank Street
Broomfield,CO 80020 -1604 (513) 200-3787
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Wilson
j.wilson@airsquared.com
510 Burbank St.
Broomfield ,CO 80020 -1604
(303) 466-2669

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposed innovation supports technologies for In Situ Resource Utilization (ISRU) processes by collecting and pressurizing gasses from the Mars atmosphere for eventual oxygen production by use of Solid Oxide Electrolysis (SOXE). There are several ways to capture and pressurize CO2, including freezing at cryogenic temperatures, mechanical compression, and absorption. Completed studies on each approach, have generally favored cryogenic temperature and mechanical compression solutions. Recently, mechanical compression has gained momentum through the Mars Oxygen ISRU Experiment (MOXIE), which utilizes an Air Squared compressor for mechanical compression of CO2. If this approach is pursued further for a larger system, there are still several questions concerning reliability over 10,000 hours of autonomous operation in Mars environment and scalability. Air Squared plans on addressing these issues as part of Phase II.


The proposed innovation is a Martian Atmosphere Scroll Compressor (MASC). Dealing with the low pressures of the Martian atmosphere, the MASC functions like a vacuum pump utilizing Air Squared scroll compressor technology. During Phase I, Air Squared tested several orbiting and spinning scroll prototypes on CO2 at a wide range of discharge pressures and superior efficiency was demonstrated with lower discharge pressures. Parallel efforts by NASA-JPL on MOXIE, showed no performance degradation of the SOXE at reduced pressures down to 4.4 PSIA. Additionally, reducing the cathode pressure provides more margin against starting to electrolyze CO. For this reason, Air Squared has decided to focus exclusively on collection-only in an attempt to concentrate efforts on a lightweight and efficient MASC, supporting oxygen generation. The following proposed Phase II work will further develop both a spinning and orbiting scroll MASC for providing 2.7 kg/hr of CO2 at discharge pressures between 4.4 and 15 PSIA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Where size, weight, and power are at a premium, the MASC excels, making it a perfect fit for military and commercial aerospace markets. The MASC could replace state of the art air compressors in On-Board Oxygen Generation Systems (OBOGS) which recycles cabin atmosphere in military aircraft, eliminating the need for heavy and tightly temperature controlled liquid oxygen tanks, thereby extending mission lengths and increasing pilot performance. Air Squared has an existing partnership with Cobham Manufacturing to produce scroll air compressors in their OBOGSs and once testing is completed, the MASC would be a next-generation upgrade for military aircraft. A spinning scroll compressor design, like the MASC, would minimize space and weight needs while maintaining versatile compatibility with several different military aircraft.

Integrated as an air compressor for aviation potable water systems, the MASC could provide more efficient, lighter, and smaller solution to the commercial air transportation industry. The MASC could reach a market already established in Air Squared?s partnership with Airbus to retrofit their current potable water system. The adaptive MASC would solve previous reliability issues through its less complex spinning scroll design. If successful, the spinning scroll MASC will provide a pathway for tailoring the technology to the additional compressor and vacuum pump applications in the commercial aerospace industry.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
To meet NASA?s ambitious goal of human exploration of Mars, the MASC provides in-situ resource utilization for the production of oxygen and fuel derived from the CO2 rich Martian atmosphere. Designed to minimize size, weight, and power requirements without compromising efficiency, the MASC is applicable to NASA?s many atmospheric collection and monitoring demands. Engineered for the collection of CO2 for the Mar Rover 2020 mission, the MASC is a next-generation evolution of Air Squared?s successful MOXIE scroll compressor, re-imagined for human exploration of space. Scaled up, the MASC would apply to storage and utilization of CO2 on future Mars missions to supply the raw materials for oxygen and fuel production. Scaled down, the MASC could be integrated onboard NASA?s crewed spacecraft to collect and analyze atmospheric particulate to monitor the safety of the astronauts on board. Additionally, the MASC could fulfill the atmospheric monitoring and safety needs on board the ISS by collecting CO2 and other toxins and regulating the breathable environment. Via a low power, compact, and reliable design, the MASC could reduce space transit fuel costs for Mars exploration crews by supplying them with oxygen and fuel for the journey back home.

TECHNOLOGY TAXONOMY MAPPING (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.)
Machines/Mechanical Subsystems
Pressure & Vacuum Systems


PROPOSAL NUMBER:17-2 H2.01-8820
PHASE-I CONTRACT NUMBER:NNX17CK06P
SUBTOPIC TITLE: Lunar Resources
PROPOSAL TITLE: Cuberover for Lunar Science and Exploration
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Astrobotic Technology, Inc.
2515 Liberty Avenue
Pittsburgh,PA 15222 -4613 (412) 682-3282
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Horchler
andrew.horchler@astrobotic.com
2515 Liberty Avenue
Pittsburgh ,PA 15222 -4613
(216) 272-3882

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

CubeRover is a robust miniaturized rover for built for lunar science and exploration. With its 2-kg mass, the robot would be the smallest (and likely the least costly) planetary rover ever deployed. CubeRover’s mobility, power and sensing enable 0.5 km traverses, or greater, even over challenging lunar terrain. The rover is based on a highly-integrated single board computer (rover-on-a-board) with reliable flight software, has integrated lander stowage and deployment capability, and uses WiFi for teleoperation and shared computation between rover and lander. The system incorporates a flexible thermal design and includes mass and power allocation for small science instruments, opening up a range of novel applications, landing sites, and mission concepts. Finally, the design offers an approach toward standardization and commercialization of CubeRover parts and designs.

This proposal describes a detailed plan for the development, testing, and delivery of flight hardware by the end of the contract in 2020. Phase II work will mature the Phase I design and retire risks in pursuit of developing and delivering a flight-ready CubeRover. The proposed program consists of five technical objectives that address the key challenges of small size and mass, the harsh lunar environment, and broad applicability and flexibility for future missions and payloads. Work will mature subsystems to develop the final flight configuration to environmental specifications, build flight hardware, and perform qualification and acceptance testing. The key artifacts that will result include: a flight-qualified version of the single board computer, several prototype rovers for testing, and a flight-qualified CubeRover that can survive the trip to the Moon and perform its mission.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Astrobotic intends to commercialize CubeRover to allow entrepreneurs to develop tools and components for the platform. The hope is that the release of a standard will lead to increased development interest and investment in affordable, compatible parts for CubeRovers in the same way that CubeSats drove industry to centralize around common standards and components. The goal, long term, is that these rovers are well suited to technology demonstrations and a range of commercial endeavors on the lunar surface, including lunar volatiles prospecting, habitat building, monitoring and repair, and the establishment of local infrastructure (such as communication relay).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
CubeRover is designed for robustness and could be infused into any NASA mission to the Moon. To date, the team has identified six Lunar SKGs that could be studied using CubeRover and small, relevant scientific instruments with a clear path to flight.

Due to its relatively low deployment and development cost, CubeRovers will be excellent platforms for technology demonstration missions. Specific technologies that might be tested include rover batteries that could withstand high temperatures, space computing, novel materials or sensors, motors, power systems, or dust mitigating technologies. CubeRover will allow developers an affordable route through which to increase the Technology Readiness Level of their technology, and lower a barrier to technology development (and, while these technologies will be demonstrated on CubeRovers, the components that are validated and developed are likely to be relevant to rovers of all sizes).
Additionally, small rovers will allow engineers, entrepreneurs, and scientists to test novel, exciting, and high-risk concepts of operations. CubeRovers will be the first to demonstrate recharging from a centralized power source in a regolith environment, repair of surface assets, and establish a local communication infrastructure network. Demonstrating these concepts will be critical to enabling the establishment of long-term habitats on the Moon, but they are neither relevant nor economically feasible for investigation with a larger rover.

TECHNOLOGY TAXONOMY MAPPING (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.)
Hardware-in-the-Loop Testing
Lifetime Testing
Robotics (see also Control & Monitoring; Sensors)
Telemetry/Tracking (Cooperative/Noncooperative; see also Planetary Navigation, Tracking, & Telemetry)
Teleoperation
Mission Training


PROPOSAL NUMBER:17-2 H3.02-9612
PHASE-I CONTRACT NUMBER:NNX17CJ20P
SUBTOPIC TITLE: Environmental Monitoring for Spacecraft Cabins
PROPOSAL TITLE: Micro-Electro-Analytical Sensor for Sensitive, Selective and Rapid Monitoring of Hydrazine in the Presence of Ammonia
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)
Maksudul Alam
Maksudul.alam-1@innosense.us
2531 West 237th Street, Suite 127
Torrance ,CA 90505 -5245
(310) 530-2011

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Hydrazine, a volatile and flammable colorless liquid, is classified as a carcinogen by the US Environmental Protection Agency. It can cause chromosome aberrations negatively affecting the lungs, liver, spleen, thyroid gland, and central nervous system. NASA’s existing hydrazine measurement technology is sensitive, selective and reliable, but it takes 15 minutes to collect and analyze a sample. For future missions beyond Low Earth Orbit, NASA will need a measurement system that responds within 30 seconds without any performance limitations such as lack of specificity and maintenance challenges. To fulfill NASA needs, InnoSense LLC (ISL) will continue developing a space-worthy micro-electro-analytical sensor for rapid monitoring of hydrazine (Micro-Zin™) in the presence of ammonia in spacecraft cabin atmosphere (SCA) for long-term performance without maintenance. In Phase I, ISL developed a compact Micro-Zin working model and demonstrated its performance detecting hydrazine with high sensitivity and selectivity over ammonia, fast response time (T90 >30 seconds), reversibility, cyclability and reproducibility under NASA-required SCA conditions, meeting or exceeding performance targets. In Phase II, ISL will focus on optimization and scale-up of Micro-Zin following fine-tuning of performance and analyzing life expectancy by rigorous testing. Complex modeling, package design, and construction of a Micro-Zin prototype for SCA-level testing are also planned. At the end of Phase II, a compact, battery-operated, handheld Micro-Zin prototype will be delivered to NASA for further evaluation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Micro-Zin will find applications in the commercial space industry (including Lockheed Martin Company, UTC Aerospace Systems, SpaceX, Blue Origin and Orbital ATK), missile defense, the toxic chemical process control industries, environmental/EPA regulatory compliance and biomedical sensor areas. Micro-Zin is an adaptable platform and it can be modified to address point-of care diagnostics. A modification of the sensing element will allow development of highly sensitive and selective biosensors for monitoring disease biomarkers, making the medical market the largest transition opportunity. This market demands high performance, low life-cycle cost and low-power consumption. The global nanomedicine market was $212B in 2015 and could reach $1.3T by 2025.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Micro-Zin is designed for rapid monitoring of hydrazine for measurements of spacecraft cabin atmosphere to identify and minimize the risks to crew health during exploration-class missions beyond low-Earth orbit (LEO). Micro-Zin will offer sensitive, selective and reliable detection of hydrazine with quick response time (T90 ≤30 seconds) in the presence of confounding background ammonia gas (30X or more than hydrazine levels) in spacecraft cabin atmosphere. Micro-Zin will be compact (device volume ~480 cubic centimeters) and lightweight to comply with mass and volume constraints. One or more of these miniature Micro-Zins can be placed within the crew cabin, thereby supporting crew health and well-being for future space missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Chemical/Environmental (see also Biological Health/Life Support)
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Space Transportation & Safety
Autonomous Control (see also Control & Monitoring)
Health Monitoring & Sensing (see also Sensors)


PROPOSAL NUMBER:17-2 H3.03-9217
PHASE-I CONTRACT NUMBER:NNX17CJ31P
SUBTOPIC TITLE: Environmental Control and Life Support
PROPOSAL TITLE: Solid State Oxygen Concentrator and Compressor
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sustainable Innovations, LLC
111 Roberts Street, Suite J
East Hartford,CT 06108 -3653 (860) 652-9690
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Trent Molter
trent.molter@sustainableinnov.com
111 Roberts Street, Suite J
East Hartford ,CT 06108 -3653
(860) 652-9690

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Sustainable Innovations has developed a novel solid state technology for gas separation and is applying it for the first time to meet a critical life support function: to develop an oxygen concentration module that minimize the hardware mass, volume, and power footprint while still performing at the required NASA capabilities. The Sustainable Innovations Oxygen Concentration Module is an extension of our proven H2 concentration, generation and compression technology that we are currently developing for NASA applications, including several configurations specifically designed for operation in Zero Gravity. This cell hardware has been demonstrated in mock zero and negative gravity on the bench-top and is currently being scaled for greater throughput applications.

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Other applications of oxygen capture and compression technology include military, commercial aviation and medical uses. Military - The U.S. Department of Defense may be interested in the development of this technology for military operations as an aircraft on board oxygen generation system, capable of providing breathing oxygen for the crew. Commercial Aircraft- Sustainable Innovations' Solid State Oxygen Concentrator has the potential to become a cost efficient platform for the onboard generation of oxygen in commercial aircraft. The system will be capable of recycling breathing oxygen from the on board atmosphere and providing supplemental oxygen for passengers during emergency descent. Medical Oxygen-Current medical oxygen markets are moving to become less reliant on bulky, stationary oxygen concentrator systems. Sustainable Innovations' Solid State Oxygen Concentrator will serve as a low cost, efficient, and portable oxygen generation system for use in medical practices and private homes

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Sustainable Innovations Solid State Oxygen Concentrator and Compressor will concentrate the oxygen within the cabin environment and provide the required concentration of oxygen to the crew members. Sustainable Innovations' electrochemical cell technology will separate pure oxygen from dilute, mixed gas streams. In addition, the Solid State Oxygen Concentrator and Compressor system has the potential to replenish the secondary oxygen pack (SOP) used by astronauts during extravehicular activity (EVAs) should the primary and backup systems fail. The SOP only contains 1.2 kilograms of oxygen, enough to sustain an astronaut for approximately thirty minutes. By replenishing the SOP with recycled oxygen, Sustainable Innovations'electrochemical cell design could give astronauts on EVAs additional time to reach the airlock of their orbiter.​

TECHNOLOGY TAXONOMY MAPPING (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.)
Essential Life Resources (Oxygen, Water, Nutrients)
Medical
Protective Clothing/Space Suits/Breathing Apparatus


PROPOSAL NUMBER:17-2 H3.03-9928
PHASE-I CONTRACT NUMBER:80NSSC17P0061
SUBTOPIC TITLE: Environmental Control and Life Support
PROPOSAL TITLE: Regenerable Carbon Filter
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)
John Holtsnider
Holtsnider@urcmail.net
P.O. Box 609
Myrtle Creek ,OR 97457 -0102
(541) 863-2663

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A Regenerable Carbon Filter (RCF) is proposed for the removal of carbonaceous particulate matter produced in Environmental Control and Life Support (ECLS) processes. Successful development of this technology will result in a device that effectively collects ultrafine carbon particles in a high density, high storage capacity volume which is subsequently regenerated in-situ using self-cleaning techniques. Various reactors considered for use in air revitalization in NASA's exploration life support closed habitat mission concepts result in the generation of solid carbon compounds as byproducts. These include the Carbon Formation Reactor (CFR) within a Bosch-type carbon dioxide reduction system and, what the proposed RCF technology specifically addresses, the methane Plasma Pyrolysis Assembly (PPA) within a Sabatier-type carbon dioxide reduction system. Capture and oxidation of this carbon material in a manner that eliminates crew handling while maximizing equipment operating capacity and lifetime is of paramount importance within manned space habitats that rely upon these processes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Gas filtration is an important step in many industrial processes and as such the proposed RCF technology may find application in such instances where low residual carbon is produced as a problematic byproduct requiring removal. In addition, completely analogous to NASA's application, is the employment of an RCF aboard commercial crewed space platforms.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The NASA application will be as Flight Hardware for deployment in support of future manned missions. Regenerable filtration of carbonaceous particulates from gas steams produced within closed habitation ECLS system hardware is needed to maximize equipment operating capacities and extend mission timelines. Ideally the fully developed technology will be acquired as Flight Hardware by NASA, resulting in enhanced capability during crewed deep space exploration.

TECHNOLOGY TAXONOMY MAPPING (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.)
Essential Life Resources (Oxygen, Water, Nutrients)


PROPOSAL NUMBER:17-2 H3.04-9315
PHASE-I CONTRACT NUMBER:NNX17CJ15P
SUBTOPIC TITLE: Logistics Reduction
PROPOSAL TITLE: Vapor Compression Refrigeration System for Cold Storage on Spacecrafts
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Air Squared, Inc.
510 Burbank Street
Broomfield,CO 80020 -1604 (513) 466-2669
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kunal Bansal
k.bansal@airsquared.com
510 Burbank Street
Broomfield ,CO 80020 -1604
(303) 466-2669

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA is looking for solutions for its long-term or distance food storage and transport applications. Achieving high thermal efficiencies and reliability while maintaining volumetric and mass efficiency has been the key challenge with these kinds of refrigeration/freezing systems in a microgravity environment. Previous state of the art refrigerator/freezer systems such as the ISS RFR, use thermoelectric thermal control with very low overall system COP of around 0.36 (in freezer mode).

Alternatively, terrestrial cold food storage systems utilize much more efficient vapor compression thermal control systems, making the systems lighter and more compact. Currently, these systems do not have provisions to fulfill the load and reliability requirements of space applications and are also not designed for microgravity operation. An example would be Kelvinator KCCF220QW chest freezer. This freezer can maintain temperatures as low as 26͒C at COPs of around 2.2 to 2.4.

Air Squared is proposing the development of a Zero-gravity Vapor Compression Refrigerator (ZVCR). The ZVCR is an oil-free, scroll driven, vapor compression food storage system that is thermally efficient, lightweight and reliable. Similar to conventional systems, the ZVCR will include four major components: compressor, condenser, expansion device and evaporator. But, instead of a heavy and oil lubricated working fluid compressor, it will use an advanced oil-free orbiting type scroll compressor and expander developed by Air Squared. Its oil-free design will remove system’s operational reliance on gravity while keeping the design compact & lightweight at higher efficiencies. For expansion work recovery, a scroll expander based on the same technology as the compressor will be used to further improve the system’s performance. Custom heat exchangers will be designed for efficient operation in microgravity while considering the size, weight and reliability requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
With a compact duet scroll compressor and expander design, the reliable and efficient ZVCR is poised to impact the aerospace and aviation thermal control market. The oil-free nature of the proposed ZVCR reduces the need for oil separation and componentry within thermal systems that demand reduced size and weight in low and zero gravity environments. Implemented on board military aircraft, the ZVCR would provide excellent waste heat rejection and thermal systems control of precise atmospheric temperatures and cabin pressurization. Due to the efficient vapor compression refrigeration, the ZVCR could increase storage life, capacity, and low temperature cooling as an active container system for aviation cold transportation of food and medical supplies. The ZVCR would not rely on dry ice for refrigeration, allowing additional logistical flexibility in the event of delayed flight schedules. Reliable and efficient oil-free cooling and heating systems have substantial potential for both terrestrial and aerospace applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Via an innovated compact scroll technology, the ZVCR transports the benefits of earth-based refrigeration and thermal control into space for long-term human exploration. Installed on ISS resupply modules, the improved COP, minimized space and weight and maximized reliability designed into the ZVCR would allow for more food and supplies to be stored on NASA missions. The reduced weight and increase payload afforded by the ZVCR would decrease fuel costs and increase mission durations for potential Mars exploration.

In addition to the ZVCR space refrigeration applications, Air Squared can easily modify the system to meet a diverse set of NASA?s efficient thermal control needs. As a waste heat rejection pump, the ZVCR could provide precise thermal control for spacecraft operating at high ambient temperature locations. A larger ZVCR could efficiently control the livable environment and crew accommodations as an environmental control unit for spacecraft or stations. Regardless of electronic, cabin, or food storage thermal management, a compact, lightweight reliable, and efficient ZVCR could increase the efficiency of NASA operations.

TECHNOLOGY TAXONOMY MAPPING (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.)
Active Systems
Food (Preservation, Packaging, Preparation)


PROPOSAL NUMBER:17-2 H4.01-8870
PHASE-I CONTRACT NUMBER:NNX17CJ30P
SUBTOPIC TITLE: Damage Tolerant Lightweight Pressure Structures
PROPOSAL TITLE: Impact-Resistant, Damage-Tolerant Composites with STF Energy Absorbing Layers
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
STF Technologies, LLC
58 Darien Road
Newark,DE 19711 -2024 (716) 799-5935
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Dombrowski
rddombrowski@stf-technologies.com
58 Darien Road
Newark ,DE 19711 -2024
(716) 799-5935

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

We propose an innovative hybrid composite material containing shear thickening fluid (STF) Energy Absorbing Layers (SEALs) that provides superior impact protection and novel, self-healing functionality to prevent leakage after impact.  The proposed innovation directly addresses the need for thin, lightweight, impact-resistant composite materials that can be fabricated in complex geometries for next-generation space suits.  The proposed Phase II research leverages successful Phase I R&D and extensive composite materials and space suit expertise of our partners to advance commercialization and TRL of impact-resistant, damage-tolerant SEAL-composites innovation to produce a prototype suit component suitable for system-level integration and testing.  In Phase I it was shown that the SEAL-composites provide significantly improved impact properties and weight savings vs. leading conventional composite materials from the Z-2 prototype. Futhermore, SEAL-composites impart self-healing functionality to mitigate air leakage if damaged. The Phase II objectives and work plan follow a logical sequence to test and downselect improved SEAL-composite materials, to develop and validate a computational model and conduct model-based design optimization, to develop high-fidelity test methods, to refine the manufacturing process to make aerospace-grade SEAL-composites, and to deliver a validated suit prototype component made from SEAL-composites.  Further, we will leverage synergistic environmental protection garment (EPG) research being conducted at STF Technologies and the University of Delaware to perform system-level development and optimization of the SEAL-composites combined with emerging, state-of-the-art EPGs.  Overall, the proposed Phase II will produce a validated SEAL-composite prototype suit component meeting the needs for improved impact-resistance and damage-tolerance to offer superior astronaut protection in a wide range of future Martian and Lunar surface EVA scenarios.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The growing market for carbon fiber and fiberglass composites represents a substantial market opportunity for STF composite materials offering improved impact resistance and damage tolerance. Improvement of out-of-plane impact resistance can potentially improve the durability and utility of composite materials in a wide variety of applications and industries including: 1. Automotive - an all composite B-pillar was recently demonstrated by researchers at UD CCM under a collaboration with BMW. Carbon fiber composites are also seeing increased demand in automotive due to the desire for increased fuel economy and growing demand for electric vehicles. 2. Personal Protective Equipment (PPE), including composite armor and shielding for first responders 3. Storage tanks for water, chemical process, oil and gas industries 4. Aerospace 5. Consumer sporting goods - skis, snowboards, surfboards, bicycle frames, tennis rackets, hockey and lacrosse sticks, helmets, and protective equipment 6. Power generation-increasing demand for wind turbine blades is major driver of growth in the fiberglass and carbon fiber reinforced composite market. Composite materials with damage tolerance and tunable damping properties have applications in large- and small-scale generation infrastructure. 7. Construction and building materials - building cladding, decking 8. Marine

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary target market for the proposed SEAL-composites innovation is in the composite portions of advanced xEMU and mEMU suits for future surface exploration missions. Specifically, the hybrid materials and design of the SEAL-composites provide significant increases in impact-resistance and damage-tolerance as compared to conventional composite materials. Phase I results found that the SEAL-composites tolerate 50% more impact energy without sustaining damage resulting in leakage and were 11% lighter than monolithic designs using the materials developed in the prior Z-2 prototype project. The improved durability and self-healing functionality at reduced weight of the SEAL-composites is useful for increasing the reliability of other composite structures and applications including storage tanks, habitats, or surface exploration vehicle components.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Nanomaterials
Smart/Multifunctional Materials
Textiles
Destructive Testing
Nondestructive Evaluation (NDE; NDT)
Protective Clothing/Space Suits/Breathing Apparatus
Characterization
Models & Simulations (see also Testing & Evaluation)
Processing Methods


PROPOSAL NUMBER:17-2 H4.01-9146
PHASE-I CONTRACT NUMBER:NNX17CJ17P
SUBTOPIC TITLE: Damage Tolerant Lightweight Pressure Structures
PROPOSAL TITLE: Impact Resistant Composite Structures for Space Suit Applications
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Composites Automation, LLC
9 Adelaide Court
Newark,DE 19702 -2068 (302) 584-4184
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Roger Crane
crane@compositesautomationllc.com
9, Adelaide Court
Newark ,DE 19702 -2068
(410) 562-2163

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Composites Automation (CA) proposes to collaborate with the University of Delaware Center for Composite Materials (UD-CCM) and our industry transition partner ILC Dover, to develop innovative material and structure concepts for next generation Space Suit hard composite components. The SBIR goals are develop material systems that survive an impact of 300 J at <0.125” thickness and <1.7 g/cc density with no leaks. Phase I demonstrated a material solution that met these requirements and the ability to balance impact and structural performance with composite design. Phase II will study additional material choices, develop and optimize composite architectures, and demonstrate impact, structure and joint/interface performance. A complete material specification including material composition, process methods and properties will be developed for the optimized solution(s) for use in product design. Phase II will culminate in the design, analysis and manufacture of a full-scale Hatch, based on NASA requirements, with the optimized composite material solutions. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Damage tolerant composite structures are used in many applications, including aerospace, automotive and marine composites, and military platforms. Post-impact mechanical performance drives composite design in these applications, such as Compression after Impact or Open-hole Tension/Compression. Mechanical fastening and joining is also common in many of these applications and resistance to damage propagation at fastener holes promotes long-term durability. Concepts/strategies that increase durability, and post-impact performance while retaining lightweight characteristics are of wide-ranging interest in the composites industry. The proposed full-component Hatch demonstrator will address all these challenges and serve as an technology maturation example for all these markets.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Increasing damage tolerance of lightweight composite structures to impact loads while maintaining leak resistance under pressure is a key performance metric for space suit hard composite components. Aerospace and satellite structures are also driven by damage tolerant design criteria and proposed concepts may enable higher design allowables and lighter weight solutions. Proposed goals will improve performance 4X the current Z2 composite design and enable lighterweight and more robust and leak resistant composite component designs.
NASA has recently developed the Z2 space suit but has interest in improving the robustness required for exploration of a planetary surface. The desired improvements will allow for reduced maintenance and provide simple and robust interfaces with the portable life support system. This can potentially also be used for the International Space Station Extravehicular Mobility Unit.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Smart/Multifunctional Materials
Pressure & Vacuum Systems
Structures
Air Transportation & Safety
Tools/EVA Tools
Protective Clothing/Space Suits/Breathing Apparatus


PROPOSAL NUMBER:17-2 H5.02-9590
PHASE-I CONTRACT NUMBER:NNX17CL34P
SUBTOPIC TITLE: Hot Structure Entry Control Surface Technology
PROPOSAL TITLE: Novel, Functionally Graded PIP Coating System for Hot Structures
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Allcomp, Inc.
209 Puente
La Puente,CA 91746 -2304 (626) 369-1273
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Wei Shih
wei.shih@allcomp.net
209 Puente Avenue
City of Industry ,CA 91746 -2304
(626) 369-1273

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA future missions place stringent requirements on high temperature and light-weight materials.This proposal addresses some of the most challenging materials issues with respect to Hot Structures, very high temperature, up to 4500 degrees F, applications.

The very successful NASA led X-43A hypersonic flight proved the ability to use state of the art (SOTA) 2D C-C with oxidation coating system. However, current material systems can only offer limited temperature capability (<3000 °F) and mostly for single use application.  

In Phase I, two innovative technologies, undercoat and FGM multi-layer coats, were developed and screened. They were further integrated into two SOTA C-C composites. Oxidation protected C-C samples were torch tested at 3500 F/ 30 minutes, at 4200 F/ 2 minutes up to 10 cycles, and at 3000 F/cool/ 4000 F cycles showing very promising results.  The combined effects of the undercoat and FGM spray coats provide repeatable performance by creating a glass forming, conforming and adherent external coating to protect the C-C from being oxidized.

The overall objective of the proposed P-II is to further develop and optimize a robust, tailorable, and affordable oxidation protection system for C-C TPS and C-C hot structure by integrating our undercoat and FGM multi-layer spray coat technologies into at least two grades C-C composites (T300 and P30 2D C-C) meeting higher temperature performance up to 4500 F and multi-use applications. 

Work plan includes 12 tasks over 24 month grouped into 5 categories.

Once further optimized and validated under Phase II, these technologies can easily be integrated into SOTA C-C using current manufacturing facilities. The resulting oxidation protected C-C could be tailorable, affordable, and easily scaled up for large components or structure required in future NASA, DoD and commercial space applications.

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This proposal addresses some of the most challenging materials issues with respect to Hot Structures, very high temperature, up to 4000 degrees F, applications. The very successful, record breaking, NASA led X-43A hypersonic flight proved the ability to use state of the art (SOTA) material/coating system for short duration, single mission, and very high temperature applications.

However, current material systems can only offer limited temperature capability (<3000 ?F) and mostly for single use application at higher temperature. The development and validation of a family of robust oxidation resistant C-C composites that are high temperature capable, multi-use, reliable, scale-up able, and affordable will enable non-NASA designers to implement hot structure solutions in lieu of parasitic passive insulation system resulting in significant weight reduction in future non-NASA applications.

Several DoD organizations are currently actively pursuing hypersonic vehicles for both advanced missile systems, as well as sophisticated surveillance vehicles, where high performance oxidation resistant C-C are required for Aeroshell, leading edge, and flow path duct of the scramjet.

High performance upper stage C-C extension nozzles, capable of operating up to 4000 F and multi-use, are also sought by both DoD and many commercial space companies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This proposal addresses some of the most challenging materials issues with respect to Hot Structures, very high temperature, up to 4500 degrees F, applications. The very successful, record breaking, NASA led X-43A hypersonic flight proved the ability to use state of the art (SOTA) material/coating system.

However, current material systems can only offer limited temperature capability (<3000 ?F) and mostly for single use application. The development and validation of a family of robust oxidation resistant C-C composites that are high temperature capable and multi-use will enable NASA designers to implement hot structure solutions in lieu of heavy parasitic passive insulation system in future NASA Space Exploration vehicles and other missions,

The primary focus of Phase II effort is to provide new TPS solutions for NASA Space Exploration vehicles, including but not limited to hot structure, control surface/ leading edge, and upper stage extension nozzle, where a new generation of oxidation resistant C-C capable for higher temperature up to 4500 F and also for multi-use, well beyond the Space Shuttle C-C technology using SiC (via pack cementation) & glass sealant, is required.

In addition, this technology would also have applicability in future hypersonic applications. Specifically NASA future goals to use scramjet engine technology where the unique Phase II technology would be highly applicable to leading edges, fins, etc.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Composites
Processing Methods


PROPOSAL NUMBER:17-2 H6.01-9055
PHASE-I CONTRACT NUMBER:NNX17CA31P
SUBTOPIC TITLE: Integrated System Health Management for Sustainable Habitats
PROPOSAL TITLE: Operation-Aware ISHM for Environmental Control and Life Support in Deep Space Habitants
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Global Technology Connection, Inc.
2839 Paces Ferry Road, Suite 1160
Atlanta,GA 30339 -6224 (770) 803-3001
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ash Thakker
athakker@globaltechinc.com
2839 Paces Ferry Road, Suite 1160
Atlanta ,GA 30339 -6224
(770) 803-3001

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A life support systems’ reliability and survivability are critical to NASA especially in long-term space exploration missions. The Health Management of life support systems consists of several components among which power, water recovery, and biomass processing systems etc. which are of primary importance. Due to the crew’s critical dependence on such a complex system, the health management of life support systems becomes crucial to NASA’s mission success rates. In Phase I, we focus on the WRS system for proof-of-concept of ACM system. In Phase II, the work will be expanded to full scale LSS, including WRS, oxygen, food generation, waste processing, air revitalization, biomass production, etc. This will yield a system model which involves mechanical, electrical, hydraulic, chemical and biological components. We will also leverage existing models, such as BioSim, HabNet, V-HAB . With the LSS model, we will fully mature and develop the ACM system, which integrates data driven modeling, sensor/component failure isolation, hierarchical ACM system, and dynamic case-based reasoning. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Among other agencies, DoD, US Air Force, US Navy, and commercial aviation (e.g., SpaceX, Bieglow Space) are the most likely potential customers for the resulting technologies.
In addition, smart home applications or intelligent hospital and patient-care systems can be of secondary application space.
This technology would also be useful for disaster planning, e.g. Federal Emergency Management Agency, fire planning, and urban design. Applications such as air traffic control, missile guidance system, space, and range instrument radar systems, etc. also will be pursued by GTC commercialization team. From a commercial perspective, emergency response services, where remote users must quickly share information and collaborate to save lives, a means to instrument that network to assess efficiency and operation would be attractive. The technology developed under this SBIR will also be interest to any organization working on design for resilience (Terminals, highway planning, drug distribution, supply chain planning) interested in validating the effectiveness of different solutions with a focus on quick and effective decisions. Our intent is to pursue an aggressive productization and commercialization strategy to bring the technology into market place.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed effort has significant range of applications across various NASA multi-disciplinary engineering centers. Quantifying ISHM/FM in terms of standard and recognized metrics has been proven in practice in the Space Launch System, managed by Marshall Space Flight Center. Likewise, other immediate applications of this technology can be used in the operations and launch facilities at NASA's Kennedy Space Center. Other potential applications include Glenn Research Center, Ames Research Center, and Jet Propulsion Laboratory. NASA must address the long communication delays between Mars and Earth, as well as increasingly more complex systems associated with resilient autonomous spaceflight systems. These systems should be automated, monitored and diagnosed by mission control like any other near-earth mission. The proposed capability will add to the existing portfolio of PHM/SHM by addressing the need for an integrated system capable of considering the mission requirements and potentials for advancement of science in a case-by-case basis.
NASA would highly benefit from proposed systems by:
1. Concurrently predicting failures before they disrupt the mission or habitant's safety.
2. Reducing false positives of such prediction and enabling a human-interaction with an intelligent reasoning engine
3. Identifying the remaining useful capability of the system.

TECHNOLOGY TAXONOMY MAPPING (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.)
Diagnostics/Prognostics
Recovery (see also Autonomous Systems)
Space Transportation & Safety
Autonomous Control (see also Control & Monitoring)
Health Monitoring & Sensing (see also Sensors)
Condition Monitoring (see also Sensors)
Process Monitoring & Control
Models & Simulations (see also Testing & Evaluation)
Data Fusion
Data Modeling (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 H6.01-9516
PHASE-I CONTRACT NUMBER:NNX17CA47P
SUBTOPIC TITLE: Integrated System Health Management for Sustainable Habitats
PROPOSAL TITLE: Flexible Integrated System Health Management for Sustainable Habitats using TEAMS
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Qualtech Systems, Inc.
100 Corporate Place, Suite 220
Rocky Hill,CT 06067 -1803 (860) 257-8014
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Deepak Haste
deepak@teamqsi.com
100 Corporate Place, Suite 220
Rocky Hill ,CT 06067 -1803
(860) 761-9351

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

QSI proposes to field a "Flexible" ISHM Solution for Sustainable Habitats utilizing the TEAMS Toolset and concomitant model-based and data-driven diagnostic/prognostic reasoning technologies to enable the habitat crew and ground support personnel to obtain crucial alerts that affect the operation of critical habitat subsystems. Automated health assessment, crew alerts and future degradation estimates will be generated to facilitate corrective actions in the face of off-nominal and failure conditions. The ISHM solution would reduce the cognitive load on the crew given the abundance of information that has to be reasoned upon in a timely fashion. This will be critical for improving mission and system safety. The solution will utilize habitat's real-time system health assessment, anomaly and failure detection, machine learning and active learning techniques to provide clear and concise decision support to improve situational awareness and perform proactive corrective actions. The solution provides the ability to report and incorporate previously undiscovered anomalies through a visually intuitive active learning interface. QSI's Hybrid modeling concept leverages domain information from various knowledge sources such as SysML, VISIO, etc. to augment its data-driven models with system-level interdependencies, which provide critical insight into the system when new anomalies need to be identified by the human-in-the-loop. Additionally, the TEAMS framework will enable integration of third-party Machine Learning modules to leverage best-in-class anomaly detection techniques for an integrated solution. These technologies would reduce the cost and risk of habitat operations, across all its phases: development, flight unit production, launch, and operations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The application of habitats in government, industrial, and commercial applications makes them an obvious commercialization target for this technology. We envisage the proposed technology to be of significant interest inside DoD's Forward Operating Bases (FOBs), FAA, US Air Force, US Navy, and commercial space vendors (e.g., Boeing, SpaceX). The development of the various interacting technology components for health-monitoring enabled anomaly/failure and degradation detection can be easily directed towards mission assurance and will be of direct interest to large-scale military systems (systems of systems) such as NORAD, Space Command ground segments, the Navy shipboard platforms and Submarine Commands. In addition, offshore platform industry, greenhouse industry, bio-domes, nuclear shelters, and extreme weather research stations are potential targets as well. Other examples of use of this technology include manufacturing, transportation (air transport, self-driving vehicles, and electric cars), energy (smart grids), space (on-orbit inspection and repair, mining), agriculture, healthcare (prosthetics, rehabilitation, surgery), marine environments, education (inspiring science, technology, engineering and mathematics education), public safety (emergency response, hazardous material handling, bomb disposal), and consumer products (household robots). This solution can also be marketed to commercial habitat operators and maintainers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed ISHM solution, aimed at improving the reliability and performance of sustainable habitats through the use of diagnostic and prognostic failure and anomaly detection techniques, active learning and trending capabilities, will allow NASA to better plan and execute future Science Missions. The technology can be leveraged to facilitate endurance in complex systems, such as NASA's long-duration missions in space science and exploration. It is envisioned that the technology will also be ready to be operated as part of NASA's next generation Mission Control Technology allowing NASA to utilize the continuous health assessment and mission satisfiability information from the tool for improved mission execution while improving safety, mission success probability and the overall operational uptime of the habitat platform. This technology can also be applied to NASA's Earth based green initiatives such as the Sustainable Habitat. The Grey Water Recycling System (GWRS) at the Sustainability-Base at NASA, ARC could be an ideal insertion point for the ISHM solution. Various other systems, besides the GWRS, are also ideal candidates for the application of the ISHM technology, including the Hot Water Pump System; HVAC: Heating and cooling system; Air Life Support System; Photo-voltaic arrays; Facility Equipment and Environmental sensors: temperature sensors, humidity sensors, differential pressure sensors, airflow sensors, carbon dioxide monitors, oxygen monitors, etc.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Diagnostics/Prognostics
Air Transportation & Safety
Analytical Methods
Health Monitoring & Sensing (see also Sensors)
Condition Monitoring (see also Sensors)
Models & Simulations (see also Testing & Evaluation)
Data Acquisition (see also Sensors)
Data Processing
Knowledge Management


PROPOSAL NUMBER:17-2 H6.03-9503
PHASE-I CONTRACT NUMBER:NNX17CA51P
SUBTOPIC TITLE: Spacecraft Autonomous Agent Cognitive Architectures for Human Exploration
PROPOSAL TITLE: User Cognitive Modeling to Enhance Task Execution
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Stottler Henke Associates, Inc.
1650 South Amphlett Boulevard, Suite 300
San Mateo,CA 94402 -2516 (650) 931-2700
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Emilio Remolina
remolina@stottlerhenke.com
1650 South Amphlett Blvd., Suite 300
San Mateo ,CA 94402 -2516
(650) 931-2700 Ext: 2709

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Procedures are commonly used by organizations to specify, document, and disseminate prescribed methods for performing tasks efficiently and effectively. However, even well-trained personnel can make errors when carrying out procedures. The risk of these errors increases when task loads are too low or too high, when multi-tasking or switching between tasks, when interrupted, when complex team coordination or handovers are required, and/or during stressful situations. In these situations, users can become fatigued or complacent, or they can lose situation awareness due to overloaded working memory, automaticity, loss of vigilance, cognitive tunneling, ineffective information scanning, or susceptibility to confirmation and other biases. When these cognitive states occur, users are prone to committing errors such as wrong steps, skipped steps, mode errors, completion errors, default errors, and perseveration.

The goal of this project is to develop an intelligent assistant that monitors users, such as crewmembers performing procedural tasks, maintains estimates of the crewmembers' cognitive states (including situation awareness and affective state), identifies situations where the user is at risk of making errors, and selects appropriate interventions that reduce the likelihood of errors. Depending upon the situation and the cognitive state of the user, the assistant will select an intervention that increases user awareness of important situational elements that the user may be missing; and by changing the level of automation, the assistant will reduce user workload.

The assistant's modular architecture facilitates plugging in of different data models and algorithms required to monitor user performance, assess situation awareness and cognitive states, identify states that might lead to errors, and intervene to prevent those errors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This technology can be used to reduce the risk of errors in other domains that employ guided or memorized procedures, especially when errors are costly. In addition to NASA applications, other domains where loss of situation awareness or affective state might lead to error include aviation (air traffic control, pilot operations), medicine (nursing), nuclear plant operations, and, in general, monitoring, operating, maintaining, and repairing complex systems and processes.

The technologies here proposed can also be used to enhance safety in the automotive industry and in the DoD-wide use of autonomous unmanned vehicles (UVs). Operating UVs will require intelligent adaptive interfaces to support new operator workload requirements as they change from many operators controlling one UV to one operator controlling many UVs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology resulting from this research will monitor user actions and physiological data and estimate the user cognitive state to detect increased risk of specific types of errors. In order to lower these risks, it will execute appropriate interventions such as changing the level of automation and/or the content and presentation of information. This capability will provide the greatest benefits when stress, tight deadlines, high task loads, multi-tasking, task-switching, complex team coordination, and handovers increase the risk of error.

Candidate NASA applications include ISS flight crew operations, mission control operations, and the Orion Multi-Purpose Crew Vehicle (MPCV). In the case of near-Earth and deep space missions like MPCV, crews will need to be able to operate more autonomously with complex and sophisticated flight systems. Our technology will complement procedure tools and technologies planned for MPCV such as the presentation of procedures using tools like the MPCV eProc Viewer and augmented reality mobile glasses. This technology will also increase the ability for crew members to oversee the operation of teams of robots during lunar and Martian missions and, in the nearer term, during analog experiments on Earth.

TECHNOLOGY TAXONOMY MAPPING (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.)
Intelligence
Man-Machine Interaction
Algorithms/Control Software & Systems (see also Autonomous Systems)


PROPOSAL NUMBER:17-2 H7.02-8696
PHASE-I CONTRACT NUMBER:NNX17CM34P
SUBTOPIC TITLE: In-Space Manufacturing of Precision Parts
PROPOSAL TITLE: The Vulcan Advanced Hybrid Manufacturing System
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Made in Space, Inc.
427 North Tatnall Street, #56666
Wilmington,DE 19801 -2230 (209) 736-7768
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Snyder
snyder@madeinspace.us
8226 Philips Hwy
Jacksonville ,FL 32256 -1240
(419) 271-0602

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Building on previously funded work by NASA and DARPA, its internal research and development projects, and manufacturing activities occurring on the International Space Station (ISS), Made In Space, Inc. (MIS) is developing the VULCAN system to address NASA’s requirement to produce high-strength, high-precision polymer and metallic components on-orbit with comparable quality to commercially-available, terrestrial machined and inspected parts. Such capability enables the in-situ manufacturing of critical parts for human and robotic spaceflight and without dependence on terrestrial resupply. MIS combines spaceflight-proven microgravity process controls and payload support systems, such as environmental and thermal controls, with a modular manufacturing and post processing system that generates a net shape final product. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Department of Defense has a demonstrated need for advanced manufacturing capabilities in locations and on forward-deployed platforms without regular logistical support or available resources for traditional fabrication and finishing technologies. Perhaps the foremost example is the US Navy submarine fleet. While aircraft carriers are commonly referred to as ?cities at sea? because of their size and on-board industrial capacity, the nation?s attack and ballistic missile submarines deploy for months at a time and must function as entirely self-contained units with no physical connection to the outside world. Submarines on patrol duty may only surface during departure from base and upon return.
When away from home port, there are only two submarine tenders in the entire US Navy, one each for the Atlantic and Pacific fleets, which limits underway replenishment opportunities. These 23,000-ton ships carry physical plants comparable to a small city and are often retasked for mobile fleet support activities, exacerbating the need for an in-situ solution. Much like spacecraft, submarines also have limited volume and environmental constraints on their operations.
A tactical version of the VULCAN device gives the DoD a modular, common manufacturing system deployable on mobile platforms, such as submarines, destroyers, transport aircraft, and trucks, and in fixed locations with limited external support, such as Forward Operating Bases and advance airfields.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The VULCAN technology is primarily intended for sustaining human spaceflight operations, first on the ISS and, later, on long-duration missions to the Moon, Mars, or other destinations in the Solar System. MIS has built industry alliances with such companies as Boeing, Lockheed Martin, Orbital ATK, Sierra Nevada Corporation, and Bigelow Aerospace to evaluate the optimal concept of operations for in-space manufacturing as an enabling technology for the NextSTEP Cislunar Habitat. MIS is also working with UTC Aerospace Systems and Paragon to develop ECLSS design principles for repair and replenishment by in-space manufacturing.
Robotic expeditionary missions can also employ the VULCAN technology for autonomous repairs while building the infrastructure preceding human habitation. Local robots may retrieve and install VULCAN-generated parts automatically or via teleoperation. Such capability may be necessary to ensure continuity of operations without direct human intervention and enable human crews to focus on mission objectives.

TECHNOLOGY TAXONOMY MAPPING (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.)
Prototyping
In Situ Manufacturing
Processing Methods


PROPOSAL NUMBER:17-2 H7.02-9767
PHASE-I CONTRACT NUMBER:NNX17CM63P
SUBTOPIC TITLE: In-Space Manufacturing of Precision Parts
PROPOSAL TITLE: ISS Multi-Material Fabrication Laboratory Using Ultrasonic Additive Manufacturing Technology
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ultratech Machinery
297 Ascot Parkway
Cuyahoga Falls,OH 44223 -4422 (330) 929-5544
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Hagarty
bhagarty@utmachinery.com
297 Ascot Parkway
Cuyahoga Falls ,OH 44223 -4422
(330) 564-8845

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The goal of this program is to demonstrate the use of Ultrasonic Additive Manufacturing (UAM) solid state metal 3D printing to provide in-space, on-demand manufacturing capabilities to support the unique challenges of long-duration human spaceflight. Previous and ongoing work in NASA SBIR programs has demonstrated the ability to 3D print quality metal parts using UAM. The goal of this Phase I program is to demonstrate the feasibility to reduce the size and power consumption of current UAM machine technology to 3D print aerospace grade aluminums for In-Space manufacturing. In fact, for the UAM process, operation in a micro-gravity environment contributes to power reduction goals expressed in recent NASA documents (NASA, 2016).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Other applications of this technology could be in defense and on the spot fixes for novel parts in addition to research ventures and commercial space structure programs. This project could enable the high-performance, technology-leading nature of the organizations and their missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA applications include use on the ISS in addition to any research and development on UAM and metallic consolidation.

TECHNOLOGY TAXONOMY MAPPING (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.)
Joining (Adhesion, Welding)
Heat Exchange
Manufacturing Methods
Prototyping
In Situ Manufacturing


PROPOSAL NUMBER:17-2 H8.01-8809
PHASE-I CONTRACT NUMBER:NNX17CA37P
SUBTOPIC TITLE: ISS Utilization and Microgravity Research
PROPOSAL TITLE: Industrial Crystallization Facility for Nonlinear Optical Materials
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Made in Space, Inc.
427 North Tatnall Street, #56666
Wilmington,DE 19801 -2230 (209) 736-7768
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Snyder
snyder@madeinspace.us
82266 Philips Hwy Suite 102
Jacksonville ,FL 32256 -1240
(419) 271-0602

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Made In Space, Inc. (MIS) proposes the development, to a critical design level, of an Industrial Crystal Facility (ICF) for microgravity product manufacturing and applied research. The ICF is focused on advanced materials engineering, rather than biomedical research, and expands utilization of the ISS into new product areas not previously investigated. Intended applications include nonlinear optical single crystals and other relatively large material formulations, such as bulk single-crystal thin films and high temperature optical fiber. This is a critical next step in the development of Low Earth Orbit as an economic development zone. ICF uses the International Space Station (ISS) National Lab as a proving ground and utilizes the same value proposition as the forthcoming Made In Space Fiber (MIS Fiber) demonstration of manufacturing a product in space with economically-significant intrinsic value on the ground.

Semiorganic nonlinear optical (NLO) crystals generated from low temperature solution methods have only emerged in the past decade of academic research as an alternative to industry standards, such as lithium niobate, for improved performance and easier integration into opto-electronic devices. Lithium niobate single crystals must be manufactured by the Czochralski process, at temperatures in excess of 1260°C, which makes it energy-intensive to produce. Even with doping, lithium niobate products are typically limited to operate below 200°C or require active thermal control to limit photorefractive damage that distorts photon transmission. Microgravity production holds the potential for room-temperature production of NLO materials for high-energy applications with size and quality undiminished by the effects of sedimentation and convection. A new facility is needed to explore the feasibility of microgravity-enabled industrial crystals as a new product market for Low Earth Orbit.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
CMOS image sensors go into new automotive-safety systems, medical equipment, video security and surveillance networks, human-recognition user interfaces, and other embedded image collection devices. The growth in laser transmitter demand is driven by ever-increasing Internet traffic, cloud services, and the expected dramatic leap in network load from billions of Internet of Things connections. This sub-market is particularly complimentary to the Made In Space program for ZBLAN optical fiber production. ZBLAN optical fiber manufactured in microgravity has both a lower attenuation rate and a wider transmission window than traditional silica fiber. While fiber produced on-orbit can be used to increase the efficiency of existing fiber networks, it can also support higher-output transmitters that utilize microgravity-grown nonlinear optical crystals to exceed the material limits of silica fiber.One high impact application that NLO crystals are ideally suited to is the efficient production of UV light by second harmonic generation (SHG). A high efficiency conversion could potentially take incoherent light and produce UV from a low energy source such as an LED. Several inorganic NLO materials have transparency in the UV range including BPO4, which has a lower range of 130 nm. This would be a game changing system for medical and industrial UV applications such as lithography and machining.Another important application is efficient measurement of terahertz wave sensors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In the civil sector, including NASA, photonic device applications include laser range finding, photonic gyroscopes, spectroscopy, and optical communications. For example, the upcoming Laser Communications Relay Demonstration on the ISS, called ILLUMA, relies on a first-of-its-kind integrated photonics circuit to transmit and encode data at orders of magnitude higher rates than traditional digital systems. Future integrated photonics circuits can be lithographically printed on large single optical crystals, much as integrated microelectronic circuits are lithographically printed on semiconductor crystals today.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Nanomaterials
Organics/Biomaterials/Hybrids
Materials & Structures (including Optoelectronics)
Waveguides/Optical Fiber (see also Optics)
Processing Methods


PROPOSAL NUMBER:17-2 H8.01-9770
PHASE-I CONTRACT NUMBER:NNX17CA55P
SUBTOPIC TITLE: ISS Utilization and Microgravity Research
PROPOSAL TITLE: Rodent Centrifuge Facility Quad Locker for ISS Life and Microgravity Science Research
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)
Rachel Ormsby
rormsby@techshot.com
7200 Highway 150
Greenville ,IN 47124 -9515
(812) 728-8122

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

According to the decadal report titled, Life and Physical Sciences Research for a New Era of Space Exploration, a Report, "...the AHB Panel would be remiss if it did not strongly recommend an animal centrifuge capable of accommodating rats/mice at variable gravity levels." Furthermore, the panel stated, “...research on animal models will be constrained without the ability to manipulate the gravity variable as a factor modulating the fundamental processes underlying organ system homeostasis.” In response, Techshot has proposed to develop an innovative Rodent Centrifuge Facility (RCF-QL) that utilizes four locker locations (Quad Locker) in the EXPRESS Rack for life science research. The counter-balanced centrifuge is designed to provide a facility to allow rats and mice to live and be observed in simulated gravity between 0-1 g for up to 90 days. This streamlined design is more cost efficient and provides up to five cages. Each cage can accommodate at least six 30 gram mice, three 200 gram rats, or two 400 gram rats per cage. Each individual cage has adlib food and water, controllable lighting, and video monitoring. The habitat is temperature controlled with constant airflow throughout the cages. Air flow entraps waste in a filter that also treats the waste for bacteria and odor. Additional air filters will remove odors and ammonium from the animal enclosure. The subsystems design will minimize crew time. Each subsystem requiring change-out during the 90 day experiment will be designed to be simple and intuitive in operations. The RCF-QL will be the only facility capable of providing group housing for rats and mice, with a medium diameter centrifuge (20 in., 0.508 m) and a large rotating cage volume (up to 850 in3, 13,929 cm3 for the cage). All hardware cage features are designed to utilize the NIH animal care and use standards.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Techshot sees tremendous potential commercial applications for the Rodent Centrifuge Facility - Quad Locker (RCF-QL) in biotechnology and pharmaceutical companies where life science research holds promise for cell replacement therapies for bioregenerative diseases. Techshot already has been in talks with pharmaceutical companies such as Novartis and Eli Lilly regarding long-term rodent research aboard the ISS. In addition, the company has a long standing relationship with the CASIS, with which it has been working to identify and facilitate industry users of ISS and Techshot spaceflight hardware technologies. The company also already has conducted multiple recent face-to-face discussions with Robert Bigelow of Bigelow Aerospace and Christian Maender of Axiom Space regarding deploying research systems such as the Techshot RCF-QL aboard their respective private commercial orbiting vehicles. Techshot also will commercialize the RCF-QL by incorporating it into the company's spaceflight service catalog it markets to other federal agencies such as NIH, NSF, and DoD.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Rodent Centrifuge Facility - Quad Locker (RCF-QL) offers the largest diameter centrifuge research tool flown on ISS. The RCF-QL is a unique and powerful instrument for novel life and microgravity science research. Techshot's initial targeted application of the proposed innovation is an offering of both the equipment and services associated with flight hardware and integration activities, which are highly desired by NASA-funded scientists. The RCF-QL will enhance NASA's position in exploration research by allowing rodent experiments at Moon or Mars gravity - a long-standing interest of NASA's intramural and extramural gravitational physiology users. Its large cage geometry will allow the investigation of a variety of systems, biological and physical, with larger allowed volume than any other ISS centrifugal research device. And it can provide 1-g control conditions for experiments in stationary hardware such as animal and plant habitats. The RCF-QL will have the additional advantage that Techshot is uniquely qualified to provide these space flight services, just as the company has done for PI's on a variety of flight experiments for the nearly 30 years, including, for example, the Techshot rodent Bone Densitometer, and its artificial-gravity payloads such as the Avian Development Facility and the Multi-use Variable-g Platform.

TECHNOLOGY TAXONOMY MAPPING (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.)
Machines/Mechanical Subsystems
Biological (see also Biological Health/Life Support)
Biophysical Utilization
Medical
Physiological/Psychological Countermeasures


PROPOSAL NUMBER:17-2 H9.01-8624
PHASE-I CONTRACT NUMBER:NNX17CP40P
SUBTOPIC TITLE: Long Range Optical Telecommunications
PROPOSAL TITLE: High Power (50W) WDM Space Lasercom 1.5um Fiber Laser Transmitter
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)
Doruk Engin
dengin@fibertek.com
13605 Dulles Technology Drive
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)

Fibertek proposes to develop and demonstrate a spaceflight prototype of a wideband, high power 50W, 1.5-um fiber laser transmitter, supporting high data rate wavelength-division-multiplexed (WDM) operation for space optical communication links. The fiber laser transmitter will support up to 8x WDM channels with high power conversion efficiency. The proposed 10x scaling of the average and peak power performance for such a space-qualifiable WDM 1.5-um transmitter enables >100x data-rate scaling of current space laser communication links. In Phase 1 of the program all proposed performance objectives were exceeded or achieved.  The successful outcome of Phase II will be to develop a prototype, space-qualifiable, high-efficiency, high-power (50W), 1.5-um WDM space lasercom transmitter. This advances the Technology Readiness Level (TRL) from 3 to 5.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This effort supports the need for large data volume DoD and commercial GEO inter-satellite networks and high data volume downlink and LCRD (Lunar Communication Relay Demonstrator) style relay.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
1) Supports NASA SCaN (Space Communications and Navigation Program) roadmap to enable large science data volume returns from deep space missions. NASA exploration mission to Mars, planets and asteroid belts will benefit from much higher data rates and longer ranges than the current state of the art.
2) NASA SCaN office initiatives to support large 100G + core GEO networks.
3) Space laser communication transmitter for ISS/LEO/GEO platforms, similar to NASA technology demonstrator missions
4) High-data rate, multi-channel laser transmitters, as an adjunct high-volume data link for Earth Science missions, such as for hyper-spectral imaging, JPSS (Joint Polar Satellite System), Landsat, and radar/lidar missions where large data volumes are needed.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fiber (see also Communications, Networking & Signal Transport; Photonics)
Filtering
Gratings
Lasers (Communication)
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Multiplexers/Demultiplexers
Transmitters/Receivers
Waveguides/Optical Fiber (see also Optics)
Models & Simulations (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 H9.01-8838
PHASE-I CONTRACT NUMBER:NNX17CG41P
SUBTOPIC TITLE: Long Range Optical Telecommunications
PROPOSAL TITLE: Geiger-Mode SiGe Receiver for Long-Range Optical Communications
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Freedom Photonics, LLC
41 Aero Camino
Goleta,CA 93117 -3104 (805) 967-4900
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Daniel Renner
drenner@freedomphotonics.com
41 Aero Camino
Goleta ,CA 93117 -3104
(805) 967-4900 Ext: 7008

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The objective of this program is to develop, demonstrate and implement a 1550-nm sensitive photon-counting detector array with monolithically integrated time-tagging electronics, suitable for free-space optical communications, where high data volume returns from space missions are critical, such as in the Lunar Laser Communication Demonstration (LLCD) and other future NASA missions. Conventional photon counting detector arrays are implemented in either Silicon (Si) or Mercury Cadmium Telluride (HgCdTe), negating detection at 1550 nm in the case of Si or incurring high cost and complexity for HgCdTe. In this program, Freedom Photonics will partner with the University of Nevada Las Vegas (UNLV) and Arizona State University (ASU) to develop a novel Geiger-mode Avalanche Photodiode (APD) arrayreceiver for photon counting applications with sensitivity for wavelengths in the range from 1000 nm to 1600 nm, which utilizes standard CMOS processing for electronics, coupled with selective growth of APDs in the SiGeSn materials system, resulting in a low-cost, high-sensitivity, high-speed and radiation hard receiver for long-range optical communications. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential applications for the FSO high sensitivity photodetector include:
- Space communications
- Aircraft-to-aircraft and aircraft-to-ground communications
- Communication links for internet-by-balloon or internet-by-drone as currently being developed by Google and Facebook
- Building-to-building connectivity, where the improved detector sensitivity would improve performance under some adverse weather conditions

Customers for these products include:
Other Government
o Department of Defense
o Department of Agriculture
o Department of Homeland Security
o Department of Energy
Non-Government Commercial
o Companies developing aerial internet distribution such as Google and Facebook
o Space exploration companies such as SpaceX and Orbital ATK
o FSO link manufacturing companies such as fSona and Lightpointe

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In this program, Freedom Photonics proposes to develop a photon-counting detector array, sensitive in the 1550 nm wavelength range, suitable for Free-Space-Optical (FSO) communications where high data rates from space missions are critical, such as the Lunar Laser Communication Demonstration (LLCD). The proposed photodetector array is akin to the well known Silicon Photomultiplier (SiPM) but using the SiGeSn ternary alloy, rather than just Si, to extend the detection wavelength range to 1550 nm. To our knowledge, no such solid state "photomultiplier" device exists currently for detection at 1550 nm. This SiGeSn Semiconductor Photomultiplier (SPM) will be epitaxially grown on a CMOS wafer, so that it will include monolithically integrated time tagging electronics for a significant reduction in Size, Weight and Power (SWaP), compared to current state-of-the-art lasercom receivers.
Potential NASA customers for these products include:
o Space Technology Directorate
o Science Directorate
o Human Exploration and Operations Directorate
o Deep Space Optical Communications (DSOC)
o Laser Communications Relay Demonstration (LCRD)
o Space Network (SN)
o Near Earth Network (NEN)
o Lunar Laser Communication Demonstration (LLCD)
o International Space Station
o New Horizons: Pluto and Beyond

TECHNOLOGY TAXONOMY MAPPING (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.)
Telescope Arrays
Detectors (see also Sensors)
Materials & Structures (including Optoelectronics)
Optical
Optical/Photonic (see also Photonics)
Infrared
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Transmitters/Receivers
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Image Capture (Stills/Motion)


PROPOSAL NUMBER:17-2 H9.03-8954
PHASE-I CONTRACT NUMBER:NNX17CG38P
SUBTOPIC TITLE: Flight Dynamics and Navigation Technology
PROPOSAL TITLE: CUA OpenMP Nonlinear Optimization Tool
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CU Aerospace, LLC
301 North Neil Street, Suite 502
Champaign,IL 61820 -3169 (217) 239-1703
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alexander Ghosh
ghosh@cuaerospace.com
301 North Neil Street, Suite 502
Champaign ,IL 61820 -3169
(217) 721-2875

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Nonlinear programming (NLP) allows for the solution of complex engineering problems, however, none of the currently available solvers fully capitalize on parallel computing. Many NASA trajectory design packages (OTIS, EMTG, MALTO) have already had their own code streamlined, and it is now the serial execution of existing NLP solvers that represents the largest bottleneck. It is the goal of this Phase II effort to further develop the CUA OpenMP Nonlinear Optimization Tool (COMPNOT), which will utilize shared memory systems to significantly improve the time-to-solution of NLP problems. As large-scale shared memory parallel systems, such as Intel’s Xeon Phi family, become more commercially available, COMPNOT will greatly expand the market for a parallel NLP solver, even enabling most modern desktop computers to effectively run it. Phase II will focus largely on creating a distributed/shared memory hybrid mode, enabling COMPNOT to take advantage of the shared memory nodes that comprise large distributed memory systems.  Additionally the development of hardware-specific optimization, focusing on the Intel Math Kernel Library (MKL), will be a priority. At the end of Phase II, COMPNOT can begin integration into NASA trajectory design packages, significantly reducing the time-to-solution.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Government agencies other than NASA, as well as commercial markets, would benefit from the improvements inherent in COMPNOT, especially given the widespread use of nonlinear programming techniques as a primary method for solving some of the most difficult technical computing problems. For example, in economics the product-mix with price elasticity problem can be formulated as a nonlinear program and solved with a tool like COMPNOT. Another field that depends heavily on efficient and robust NLP solvers is operations research, with the facility location problem and network optimization problems being archetypal examples of operation research challenges that may be cast as nonlinear programs. Furthermore, industries dealing with problems such as power grid design, weather prediction, and crop planting optimization could benefit from COMPNOT's speed enhancements.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA currently utilizes SNOPT, IPOPT, and WORHP software packages for astrodynamics applications such as the design of complex spacecraft trajectories and other optimal control problems, but could greatly benefit from the introduction of a parallel large-scale, nonlinear, sparse optimization solution one which does not have its speed bottlenecked by a single processor. The core NLP algorithm proposed to be used in COMPNOT has already been shown to result in a reduction in execution time, thereby reducing the optimization's turn-around time and improve communications between both designers and scientists. COMPNOT would take this effort, and refocus it to multi-core machines so that individual NASA scientists could perform advanced optimizations on a desktop. Our solver would act as a significant force multiplier for existing NASA tools such as GMAT's collocation-based low-thrust transcription and EMTG"s inner loop solver. Additionally, COMPNOT could improve run-times across all forms of problem optimizations, including trajectory design, resource management, attitude determination and control, and vehicle design.

TECHNOLOGY TAXONOMY MAPPING (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.)
Development Environments
Operating Systems
Programming Languages
Verification/Validation Tools
Navigation & Guidance
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 H9.04-8557
PHASE-I CONTRACT NUMBER:NNX17CP37P
SUBTOPIC TITLE: Advanced RF Communications
PROPOSAL TITLE: GaN MMIC Ka-Band Power Amplifier
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Custom MMIC Design Services, Inc.
300 Apollo Drive
Chelmsford,MA 01824 -3629 (978) 467-4290
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Moniz
moniz@custommmic.com
300 Apollo Drive
Chelmsford ,MA 01824 -3629
(978) 467-4290 Ext: 119

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA is seeking innovative Advanced RF Platform technologies at the physical level, specifically Ka-Band high efficiency high linearity 10 to 20 Watt solid state power amplifiers (SSPAs), to meet the needs of future space missions for communications and sensor applications. Space missions require small size, weight, and power (SWaP) among the hardware components. As a result, monolithic microwave integrated circuits (MMICs) are well suited to fill this need. In Phase I of this SBIR, Custom MMIC Design Services, Inc. (Custom MMIC) analyzed a number of commercially available Gallium Nitride (GaN) MMIC process technologies from domestic foundries based in the United States, and selected the optimum process for linear power amplifiers (PAs) - the 0.2 um GaN  process as offered by Northrop Grumman Space and Technology (NGST). Custom MMIC’s use of novel small- and large-signal linear power amplifier (PA) circuit design techniques led to circuit simulations exhibiting a large signal gain greater than 22 dB from 31.7 to 32.3 GHz, a linear output power of 13 W, input and output return losses of better than -20 dB, a PAE of 41% PAE, and an error vector magnitude (EVM) of 4.5% for 8PSK 500 MHz modulation. In addition, Custom MMIC’s use of the balanced amplifier topology allowed the simultaneous independent optimization of input/output return losses and internal PA impedances for linearity and PAE. As a result, Custom MMIC has produced a design that represents a new industry state-of-the-art benchmark for linear Ka-Band GaN MMIC PAs.  In Phase II, we will develop not only the MMIC hardware that represents this design for JPL at Ka-Band (31.8 - 32.3 GHz) but also a similar linear PA for GSFC at K-Band (25.5  - 27 GHz) and a saturated radar PA for JPL at 35 GHz.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Linear GaN PA MMICs represent a new frontier in microwave research and development, though to date few manufacturers have been able to turn such efforts into viable commercial products. Custom MMIC is one such company that has made the successful transition from design to production on a number of GaN amplifiers, and so is well suited to bring an expanded portfolio of new GaN amplifiers to the market in a timely and efficient manner. Custom MMIC will use the follow-on Phase II SBIR contract to bring a number of new 10-20 W, Ka-band high power amplifiers to the commercial space.
The 25-27 GHz GaN 5 W linear amplifier is being well received in the commercial markets. A customer has already designed it into a new product and we are transitioning to production. We are in discussions with this customer as to whether the performance can be improved. It is likely that when this SBIR program transitions to Phase II we would also target this lower frequency band for a 10 W linear variant.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The improvements and innovations achieved during the Phase I portion of this 10-20 W, KA-Band GaN MMIC PA and subsequently manufactured in a follow-on Phase II will allow us to develop other state-of-the-art, linear, high efficiency PAs for NASA at other frequency bands. Specifically, Custom MMIC can apply these Phase I results to improve the 5 W, 25 to 27 GHz Power Amplifier as previously developed for NASA Goddard, and the 5 W, 35 GHz Power Amplifier for Radar Applications as previously developed for NASA JPL, such that both amplifiers can be increased to greater than 10 W output power with better PAE. Other NASA Applications could be 1) NASA deep space missions that require high data rate Ka-Band downlinks, 2) Mass, power and volume challenged surface missions to moons, asteroids and comets (such as Europa Lander), and 3) Future NASA instruments that require Ka-Band radars (such as Mars 2020).

TECHNOLOGY TAXONOMY MAPPING (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.)
Radiometric
Sensor Nodes & Webs (see also Communications, Networking & Signal Transport)
Microwave
Ad-Hoc Networks (see also Sensors)
Amplifiers/Repeaters/Translators
Transmitters/Receivers
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)


PROPOSAL NUMBER:17-2 H9.04-9007
PHASE-I CONTRACT NUMBER:NNX17CG24P
SUBTOPIC TITLE: Advanced RF Communications
PROPOSAL TITLE: Row Column Phased Array Architecture for Low Cost, Low Profile Millimeter Wave Phased Array Antennas
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Agile RF Systems, LLC
4316 Beverly Drive
Berthoud,CO 80513 -7953 (970) 344-6556
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Philip Kelly
pkelly@agilerfsystems.com
4316 Beverly Drive
Berthoud ,CO 80513 -7953
(303) 522-0303

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

There is high demand for electronically steered antennas particularly at millimeter wavelengths. However, the cost to develop and procure this type of antenna prohibits this technology from widespread use. The proposed innovation substantially reduces the control complexity of phased arrays by reducing the control set from MxN phase controls to M+N phase controls where M and N represent the number of rows and columns in the phased array. By reducing the control complexity, not only are the phased array devices simplified, but the control distribution network is substantially reduced. This simplification ripples across the entire phased array to improve physical integration and thermal management which often cost as much as the phased array components. This is particularly important for high frequency antennas where unit cell sizes become a significant impediment to system implementation. This proposal summarizes the Phase I SBIR findings definitively demonstrating the phased array innovation feasibility and applicability to future NASA Ka band communications and sensors. This phased array technology does not rely on future advancements in device technology and controls but is realizable using proven, inherently radiation hardened MMIC device technology widely available today. A prototype demonstration is proposed that will operate from 25.25 to 27.5 GHz with 8 dBm output power at each unit cell to illustrate millimeter wave phased array capabilities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed phased array beamforming architecture is a significant breakthrough in phased array technology. By drastically reducing the uniquely addressed (and routed) commands to steer electrically large phased arrays, the overall system cost is reduced associated with phased array integration. This is often an overlooked subsystem when attempting to reduce phased array system costs. The control distribution network often impacts how the phased array is temperature controlled by adding significantly to the backside physical interconnects eliminating critical surface area for thermal controls. The proposed technology can directly improve existing large phased array systems used for radar or communications. However, the low cost potential does sacrifice exquisite performance levels typically attributed to tracking radar systems that have the ability to adaptively null jamming signals or achieve very low sidelobe levels due to unit cell controls that have been eliminated with this architecture. Nevertheless, the proposed beamforming architecture can enable phased array application to mobile communication markets where spatial diversification is required for high capacity and frequency re-use. These markets include satellite communications such as for inflight entertainment and 5G high speed microcells. Other applications include sensors for Counter UAS or missile seekers where microwave and millimeter wave offers avenues for small size.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There is a growing list of small satellite and cube satellite missions enabled by industry advances in very capable, low power and miniature digital signal processing hardware. Because the proposed phased array development is expected to result in significantly lower system costs, this phased array technology should be considered for small satellite payload and data transfer subsystems. By providing a communication solution that can be electronically steered, spacecraft attitude management is simplified allowing the payload to point at the primary target longer without interruption for data off-loading. Furthermore, by lowering antenna system costs, larger apertures can be deployed to significantly improve EIRP and G/T metrics essential for long range, high throughput capacity links. A high gain, electronically steered antenna at millimeter waves in Low Earth Orbit can reduce ground station antenna sizes enabling the deployment of small ground stations to avoid scarce resource conflicts. There is also the possibility of making the Ka band antenna compatible with K/Ka band SATCOM links to provide an additional means of transporting data or command and control messaging. The proposed phased array technology not only reduces the cost of millimeter wave phased arrays but enables significant bandwidths (20% or greater) to support commercial, military and NASA spectrum. One potential mission is replacement of gimbaled Ka band antennas on JPSS-3 & JPSS-4.

TECHNOLOGY TAXONOMY MAPPING (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.)
Electromagnetic
Antennas


PROPOSAL NUMBER:17-2 H9.05-8528
PHASE-I CONTRACT NUMBER:NNX17CC28P
SUBTOPIC TITLE: Transformational/Over-the-Horizon Communications Technology
PROPOSAL TITLE: Polarization Entangled Photon Pair Source for Space-Based Quantum Communication
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)

The overall goal of this NASA effort is to develop and deliver efficient, single-pass quantum optical waveguide sources generating high purity hyper-entangled photon pairs for use in high-rate long-distance links.  The new devices will produce hyper-entangled photon pairs with high efficiency, pure spectral properties, and low attenuation, providing the key technology required for deployment of ground-to-space links and future construction of a global quantum network.  The waveguide-based technology is compact, robust, and power efficient for deployment on space-based platforms such as the International Space Station.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Quantum-based communication is of prime interest to corporations and government agencies with high security requirements. In cases where classical schemes are not considered trustworthy, key distribution by courier is typically used. Unlike human courier networks, quantum cryptography has the ability to detect interception of the key, has greater reliability and operating costs, and is automatic and instantaneous. For long distance quantum communication to be practical, ground-to-space links are a necessity due to the current limitations of optical fiber and photon detectors in ground-to-ground links. Additionally, the path to creating entangled photon sources that are as ubiquitous as diode lasers are today has implications in whole new arenas of economic development in addition to national security.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
To provide reliably secure communications, development of practical quantum optical devices for ground-to-space quantum key distribution is a necessity. The proposed technology offers a path to provably, unconditionally secure quantum encryption meeting future NASA security requirements. A space-based implementation of the technology may also answer important questions in fundamental physics by testing the properties of quantum entanglements over much greater distances than ever before, and due to earths gravitational curvature may provide an insight to the relationship between gravity and quantum physics.

TECHNOLOGY TAXONOMY MAPPING (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.)
Emitters
Lasers (Communication)
Transmitters/Receivers
Waveguides/Optical Fiber (see also Optics)


PROPOSAL NUMBER:17-2 H10.01-9546
PHASE-I CONTRACT NUMBER:NNX17CS09P
SUBTOPIC TITLE: Advanced Propulsion Systems Ground Test Technology
PROPOSAL TITLE: An Affordable Autonomous Hydrogen Flame Detection System for Rocket Propulsion
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Innovative Imaging and Research Corporation
Building 1103, Suite 140C
Stennis Space Center,MS 39529 -0001 (228) 688-2452
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mary Pagnutti
mpagnutti@i2rcorp.com
Building 1103, Suite 140C
Stennis Space Center ,MS 39529 -0001
(228) 688-2452

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA has long used liquid hydrogen as a fuel and plans to continue using it in association with their advanced nuclear thermal propulsion technology. Hydrogen fire detection is critical for rocket propulsion safety and maintenance. A significant fire at a rocket test or launch facility could be catastrophic to infrastructure or even worse, to human life. Detection monitoring is problematic as hydrogen flames can be nearly invisible during the day. Non-imaging, Non-visible fire detection technology has limited range and can suffer from false alarms from sources outside the region of interest. Low-cost visible imagers, commonly used for wide-scale routine surveillance, have limited utility detecting hydrogen fires. Although it has been known for decades that multispectral imaging outside the visible range can be used to detect fires with low false alarm rates, the price of such systems and the lack of processing algorithms and ability to implement them in real-time has largely prohibited their use. During this project we will develop a low-cost imaging capability that fuses data collected from sensors operating in the (1) solar blind ultra-violet, (2) thermal infrared, (3) mid-wave infrared, and (4) visible spectrum, using advanced spectral, spatial and temporal processing techniques optimized to detect and generate alerts associated with hydrogen fires in real-time. This multi-sensor, multi-processing approach will enable us to automate flame detection with extremely low false alarm rates. This multisensory imaging research could also support NASA's important cool flame microgravity research occurring on the International Space Station.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Government facilities managed by the Rocket Propulsion Test Program Office, including Arnold Engineering Development Center (AEDC), Redstone Test Center (RTC), the Air Force Research Laboratory (AFRL) and the Naval Air Warfare Center (NAWC) as well as commercial facilities including SpaceX, Blue Origin, Sierra Nevada Corporation and Orbital ATK could all enhance their safety and facilitate their maintenance efforts by employing this technology to monitor hydrogen and other flames. There are several established markets and applications that incorporate significant amounts of hydrogen gas in their processes that would benefit from our flame detection technology. These markets primarily include petrochemical facilities, heat treating facilities for aerospace and automotive applications, fuel cell production facilities, food processing facilities (for hydrogenation) and potentially thermonuclear power plants. An emerging application is hydrogen fuel cell fueling station monitoring. With the advent of fuel cell powered vehicles, hydrogen fueling stations will be required along roadways as a way of refilling fuel cells. These fueling stations are required by law to include hydrogen flame sensing technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology has near term direct application for monitoring hydrogen fires within several NASA propulsion test and launch facilities. This capability will enhance the safety of these facilities and potentially facilitate required maintenance procedures. NASA rocket motor testing centers that would benefit from this include SSC, MSFC, GRCPBS and WSTF. KSC, responsible for the SLS and Orion launches that continue human spaceflight within NASA, and the Launch Services Program that provides launch operations oversight at several locations including Cape Canaveral Air Force Station and Vandenberg AFB would also realize safety and maintenance benefits from this technology. NASA is currently conducting experiments on flame interaction and extinguishment onboard the ISS. Fire burns differently in microgravity and although our technology is optimized for hydrogen flame phenomenology, it has wider potential use in NASA's cool flame research portfolio and could, for example, be used to support follow-on Saffire and FLEX experiments. FLEX experiments have shown low-frequency flicker that our temporal algorithms could exploit for terrestrial fire detection and discrimination.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fuels/Propellants
Radiometric
Ultraviolet
Visible
Infrared
Multispectral/Hyperspectral
Display
Image Analysis
Image Processing
Data Fusion


PROPOSAL NUMBER:17-2 H10.03-9438
PHASE-I CONTRACT NUMBER:NNX17CS14P
SUBTOPIC TITLE: Cryogenic Purge Gas Recovery and Reclamation
PROPOSAL TITLE: Helium and Hydrogen Mixed Gas Separator
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Reactive Innovations, LLC
2 Park Drive, Unit 4
Westford,MA 01886 -3525 (978) 692-4664
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Benjamin Slote
bslote@reactive-innovations.com
2 Park Drive, Unit 4
Westford ,MA 01886 -3525
(978) 692-4664

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This product innovation is directed toward separating hydrogen from helium gas mixtures using a micro-channel separation unit with thin walls of a palladium-silver alloy. The micro-channels are produced in a size range of 100-200 microns such that the boundary layer thickness inside is drastically reduced when mixtures of helium and hydrogen gas flow through the channels. This thin boundary layer enhances the thermal and mass transport fluxes to the channel walls increasing the separation rate.  With this micro-channel approach, the membrane surface area to volume ratio is maximized reducing the operating costs and capital costs for the unit.

The present cryogenic separation process for this helium-hydrogen gas mixture is energy intensive, and newer demonstrations using proton-exchange membrane based separation processes are difficult and costly to scale to the size needed to process this large quantity of gas. Accordingly, Reactive Innovations is developing a metal membrane based micro-channel separation unit that is readily scalable and inexpensive to produce and operate. The micro-channel separation technology maximizes the separation area per unit volume giving enhanced thermal and mass fluxes to separate hydrogen from the helium mixture.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Beyond NASA's use, helium is an important irreplaceable inert gas used in a variety of scientific and industrial fields such as oil and gas detectors, the nuclear industry, medical applications, cryogenics, and welding. However, due to the growing demand for helium, the market supply is becoming tighter and costs are increasing. Currently, cryogenic distillation and pressure-swing adsorption are the prevalent methods widely used for helium separation, especially in natural gas feedstocks. The cryogenic distillation and pressure-swing separation methods involve complicated operations and require considerable energy consumption. Thus, there is an urgent need to develop simple, low-energy, and low-cost methods for separating helium from other gases. Other potential uses for this separator unit include removing hydrogen from natural gas processing plants, and separating helium-hydrogen mixtures used in medical MRI imaging, semiconductor processing, welding, and nuclear processes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The National Aeronautics and Space Administration uses substantial quantities of helium gas to purge hydrogen from fuel lines during spacecraft launches, rocket engine testing, and other processes at NASA facilities. A typical shuttle launch used about a million cubic feet of helium where six times this amount is expected for the space launch system and multipurpose crew vehicle launches. This helium gas contaminated with hydrogen is expensive and energy intensive to purify and recover. Because of helium shortages and rising prices, cost effective recovery and reclamation of helium from hydrogen-helium gas mixtures is of great economic significance to NASA and to the nation.

TECHNOLOGY TAXONOMY MAPPING (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.)
Coatings/Surface Treatments
Fluids
Fuels/Propellants
Launch Engine/Booster
Spacecraft Main Engine
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Sources (Renewable, Nonrenewable)
Material Handing & Packaging


PROPOSAL NUMBER:17-2 H11.01-9532
PHASE-I CONTRACT NUMBER:NNX17CJ32P
SUBTOPIC TITLE: Radiation Shielding Technologies for Human Protection
PROPOSAL TITLE: RSim: A Simulation Tool Integrating Radiation Codes and CAD.
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)
Svetlana Shasharina
sveta@txcorp.com
5621 Arapahoe Ave., Ste. A
Boulder ,CO 80303 -1379
(720) 841-4301

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Tech-X will develop a standalone cross-platform application RSim.  This application will have a Graphical User Interface (GUI) for performing common radiation transport simulations.  Without the need to write code in C++ or Fortran and inputs for models, users of RSim will be able to set up the radiation environment, geometry and materials of the analyzed system, choose the analysis type (tallies), run simulations and perform visualization of the simulation results.  RSim will be use two simulation engines: Geant4 and MCNP6.  RSim will be integrated with the Computer Aided Design (CAD) by supporting CAD data import and translating it into the format understood by the underlying codes. 

In addition to providing the traditional geometry support used in these code, we will also implement the DAGMC technology under development at the University of Wisconsin-Madison that would allow us to improve simulations performance.

RSim will provide a unique innovative combination of features: (1) validated support for CAD needed for integration with CAD tools, (2) a cross-platform standalone GUI application working with two radiation codes, Geant4 and MCNP6 and (3) unified visualization of setups and simulations outputs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Radiation analysis for defense satellites (DOD)
Designers developing defense satellites faces the same challenges as designers of commercial satellites. That is, one needs to minimize radiation effects on electronics and the payload. These challenges can be directly addressed by RSim.

National Laboratories
RSim will be used in detector modeling simulations routinely performed at FNAL, ANL, SLAC, BNL, SNL and ORNL.
Some of these laboratories (SNL, for example) design and launch satellites, and Tech-X has worked on radiation modeling for one their payloads. They were particularly interested in comparing results from Geant4 to their independent studies (using ITS) and will benefit from RSim, as it will facilitate such comparisons between different Monte Carlo codes.

Radiation Therapy
Modern cancer treatment uses radiation transport simulations to help radiotherapists and clinical physicists better understand and compute radiation dose from imaging devices and design new devices. RSim will allow physicians to perform comparison between models and do this very efficiently.

Global radiation detection, monitoring and safety industry Radiation transport simulations are routinely use to design new radiation detection devices are designed and analyze their data. RSim will facilitate these activities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA Manned Exploration Missions will benefit from the proposed development, as RSim will streamline design of shielding strategies. Examples of such programs are International Space Station, Orion Spacecraft system, and NASA Commercial Crew Program.

Second area of applications with NASA is Space Radiation Detector Simulation. For example, SUDA (SUrface Dust Analyzer) is an instrument under development at the Laboratory of Atmospheric and Space Physics, CU, Boulder. SUDA is approved for the upcoming Europa mission, and Tech-X is performing Geant4-based radiation modeling for the SUDA detector (see Sec. 2.3). In fact, working on this project provided us with the motivation for RSim.

Other NASA design activities face the same challenges in their modeling. For example, we are in communication with JPL engineers, who routinely perform comparisons between different radiation models.

TECHNOLOGY TAXONOMY MAPPING (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.)
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)
Ionizing Radiation
Verification/Validation Tools
Simulation & Modeling
Isolation/Protection/Radiation Shielding (see also Mechanical Systems)


PROPOSAL NUMBER:17-2 H12.01-8754
PHASE-I CONTRACT NUMBER:NNX17CL73P
SUBTOPIC TITLE: Radioprotectors and Mitigators of Space Radiation-induced Health Risks
PROPOSAL TITLE: LGM2605 as a Mitigator of Space Radiation-Induced Vascular Damage
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
LignaMed, LLC
3711 Market Street
Philadelphia,PA 19104 -5501 (215) 206-2754
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thais Sielecki-Dzurdz
thais.sielecki@lignamed.com
3711 Market Stree, Suite 866
Philadelphia ,PA 19104 -5501
(610) 299-7482

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

LignaMed, LLC is developing LGM2605, an oral small molecule for use as a radiation mitigating agent. Here we aim to evaluate LGM2605 as a mitigator of space-radiation induced damage. NASA missions to Mars will expose astronauts to solar/galactic cosmic mixed radiation including low dose g and proton radiation, a source of harmful short and long-term health effects. Damage to the vascular network under mixed radiation types is not understood. Findings from our NASA-funded Phase I studies provided novel evidence that LGM2605 is an effective mitigator of radiation toxicity in cells exposed to mixed-field space-relevant radiation (high LET protons and gamma rays). In this application, LignaMed in collaboration with the researchers at the University of Pennsylvania will extend these initial studies to evaluate LGM2605 in an in vivo model for protection from radiation-induced i) carcinogenesis in lung, liver and all major organs (Task 1) and accelerated lethality as a secondary endpoint and ii) tissue degeneration (Task 2) by evaluating long term lung deterioration and long-term damage mixed gender adult mice. We hypothesize that mixed space radiation increases cancer risk and induces chronic, pro-inflammatory changes in tissues leading to accelerated degeneration of the cardiovascular and pulmonary system. We propose that LGM2605 will mitigate space radiation-induced carcinogenesis and tissue degeneration.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lignamed LLC is a biopharmaceutical company developing LGM-2605 as adjunct therapy to reduce side effects and improve cure rates of radiation treatment of chest cancers. The market size is $5 billion. Chest cancers are a deadly and costly disease. They include breast cancer, lung cancer, sarcomas, lymphomas and esophageal cancer. According to the American Cancer Society, more than 500,000 new chest cancer cases will be diagnosed in the United States in 2014 and they project the number to increase in the years ahead. About 50 to 60 percent of cancer patients are treated with radiation at some time during their disease. Combinations of surgery, chemotherapy and radiation treatments are the standard for modern cancer therapy. Success is often determined by the ability of patients to tolerate the most aggressive regimen. The ability to deliver effective radiation therapy is limited by toxic side effects to healthy normal lung tissues. These side effects often cause breaks in treatment or dose-limiting toxicity after treatment, and, therefore, limit the amount of radiation that can be delivered to the tumor. No current therapies are effective to protect healthy normal lung tissue from the damaging effects of radiotherapy. A significant unmet need exists for a safe radioprotection agent that will ameliorate radiation side effects to normal tissue without "protecting" the tumor. The US market opportunity is estimated at $5 billion per year.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
LignaMed, LLC is developing LGM2605, a safe oral small molecule for use as a radiation mitigating agent. Here we aim to evaluate LGM2605 as a mitigator of space-radiation induced damage. The future space explorations of NASA in the form of manned missions to Mars will expose astronauts to solar and galactic cosmic radiation (GCR), which ranges from high energy protons to high charge and energy (HZE) particles and secondary neutrons produced by galactic cosmic rays (GCR). Such a mixed radiation environment does not exist on earth and is unique to space. Thus there is a lack of data defining the biological and physiological effects during and following exposure to such mixed-field space radiation exposure. This work will help understand the effects of GCR on cell signaling and demonstrate the protective effects of LGM2605 to prevent this long-term damage. Ultimately, LGM2605 will be developed for use by astronauts during space travel.

TECHNOLOGY TAXONOMY MAPPING (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.)
Isolation/Protection/Radiation Shielding (see also Mechanical Systems)
Medical


PROPOSAL NUMBER:17-2 S1.01-8484
PHASE-I CONTRACT NUMBER:NNX17CG20P
SUBTOPIC TITLE: Lidar Remote Sensing Technologies
PROPOSAL TITLE: 1.57 Micron High Pulse Energy Single Frequency Fiber Laser
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
AdValue Photonics, Inc.
3440 E Britannia Drive, Suite 190
Tucson,AZ 85706 -5285 (520) 790-5468
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shibin Jiang
sjiang@advaluephotonics.com
3440 East Britannia Drive, Suite 190
Tucson ,AZ 85706 -5285
(520) 790-5468

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

We propose to demonstrate and build a 1.572 micron single frequency high pulse energy and high peak power fiber laser by using an innovative Er-doped gain fiber with large core diameter and high gain per unit length. 1.572 micron single frequency high energy and high peak power fiber laser is needed for accurately measuring column CO2 concentrations. In Phase II, we will optimize the doping concentrations, increase the SBS threshold, improve the slope efficiency, and demonstrate high pulse energy and high peak power fiber laser with a short piece of gain fiber. Successful demonstration of such a fiber laser will enable many new NASA and commercial applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This eye-safe high pulse energy and high peak power single frequency fiber lasers can be used to build commercial lidar for ranging and gas monitoring applications, for optical sensing, fast scanning biomedical imaging, and scientific research.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA plans to launch ASCENDS in 2023 in according to the US National Research Council?s 2007 Decadal Survey recommendation to accurately measure column CO2 concentrations using the IPDA technique. For ASCENDS mission NASA would need a pulsed singe frequency polarization maintaining (PM) laser system with >3.2mJ pulse energy, 3.2 kW peak power, repetition rate of 7.5kHz, and beam quality (M2) of <1.5. This proposed laser can be used for ASCENDS.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Ladar/Lidar)


PROPOSAL NUMBER:17-2 S1.01-8776
PHASE-I CONTRACT NUMBER:NNX17CL62P
SUBTOPIC TITLE: Lidar Remote Sensing Technologies
PROPOSAL TITLE: High Speed Frequency Locking Module for Lidar Based Remote Sensing 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)
Patrick Burns
pburns@fibertek.com
13605 Dulles Technolgy Drive
Herndon ,VA 20171 -4603
(703) 471-7671 Ext: 3609

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A basic requirement for all Differential Absorption Lidar (DIAL) systems is wavelength switching of the probe laser on and off of an absorption line of the species of interest. For most trace gas species switching accuracy on the order of 10 MHz is also required. Further complications for many DIAL systems are that the platform moves (airborne or space craft) and that the lasers are often high peak power, pulsed lasers. The combination of a moving platform, pulsed laser, and the requirement that the online and offline measurements be made in essentially the same volume implies that the online/offline switching time be less than ~ 1 ms, and many cases even shorter. To date, most lasers used in DIAL systems rely on piezo-electric (PZT) mechanisms for the cavity length changes needed for the frequency switching. Typically this limits wavelength switching speeds to a few hundred Hz. This relatively slow frequency switching prevents researchers from fully exploiting DIAL systems utilizing the high efficiency, multi-kHz lasers or the lower repetition rate, dual pulse lasers systems that are now available. In Phase I, Fibertek demonstrated a brassboard version of a high speed, non-mechanical frequency locking module that allowed shot to shot frequency switching of a 1645.5 nm Er:YAG laser at >1 kHz with a spectral purity of 1,000:1.  Our approach to the proposed locking module was an innovative synthesis of all electro-optic (EO) based switching and locking, a compact and efficient EO driver design that reduces voltage requirements by 4x over conventional designs, a novel EO voltage profile that eliminates electrochromic darkening, and a larger off-set locking capability that eliminates the requirement for an additional phase shifter in the cavity. In Phase II we will advance the TRL of the key technology components and incorporate a hardened version of the locking module into a 1645.5 nm Er:YAG laser that is being developed for a methane lidar being built at NASA Langley.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In addition to our NASA customers, Fibertek does significant lidar development work with various DoD agencies that would benefit from the proposed effort. Two specific examples are briefly described below.
1) Single-frequency blue lasers for use in underwater communications: Since the early 1970's the U.S. Navy has made major investments (>$100M) in attempts to develop single-frequency blue lidar systems for underwater communications. Fibertek has supported these development efforts and anticipates that the successful development of the proposed technology would enhance our chances of winning future business in this area.
2) Doppler Wind Lidar (DWL) systems for precision air drop: An unmet need for the Army is a compact and robust DWL system that could be used to quantify the vector wind fields in the vicinity of regions where supplies will be dropped from medium to high altitude aircraft. The technology proposed here would enhance Fibertek's ability to respond and compete in this business area.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Our proposed innovation will improve the performance of the injection-seeded, single frequency lasers that are planned for use in a number of airborne and space-based missions, including the following.
1) Aerosol/Cloud/Ecosystems (ACE): This is an expanded scope follow-on to the highly successful CALIPSO cloud and aerosol lidar mission. Multiple NASA researchers have been developing three wavelength (1064 nm, 532 nm, and 355 nm) High Spectral Resolution Lidar (HSRL) systems as candidate lidars for the ACE mission.
2) 3-D Winds: Space-based measurement of winds has been identified as a critical mission for enhancing both weather and climate modeling. 355 nm airborne demonstrators for this mission include a direct detection wind lidar that was built at GSFC and an Optical Auto-Covariance Wind Lidar (OAWL) being developed at Ball Aerospace.
3) Global Atmospheric Composition Mission (GACM): A scaled up version of the 355 nm pumped Ozone DIAL system being developed at NASA Langley is a strong contender for the GACM mission for global ozone measurements.
4) NASA Langley High Altitude Lidar Observatory (HALO): This is an ongoing lidar development program for airborne measurements of methane and water vapor. Our proposed high speed locking and switching technology is critical for achieving the desired performance for the 1 kHz, 1 m pump lasers and the optical parametric oscillators (OPOs) used to generate the 1.65 um and 1.57 um beams used to measure methane and water vapor.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Ladar/Lidar)
Lasers (Measuring/Sensing)
Chemical/Environmental (see also Biological Health/Life Support)
Optical/Photonic (see also Photonics)


PROPOSAL NUMBER:17-2 S1.01-8884
PHASE-I CONTRACT NUMBER:NNX17CS54P
SUBTOPIC TITLE: Lidar Remote Sensing Technologies
PROPOSAL TITLE: High Speed Beam Steering Components for Lidar
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)
Jay Stockley
jstockley@bnonlinear.com
450 Courtney Way, Unit 107
Lafayette ,CO 80026 -8878
(303) 604-0077

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

 Boulder Nonlinear Systems (BNS) proposes to pursue development of low size, weight, and power (SWaP) beam scanner technology for entry, descent and landing (EDL) or wind sensing Lidar NASA applications that can redirect the beam of light at 1 kHz (threshold) to 10 kHz (goal) framerates. The prototype scanner will steer to 8 spots over at least a 60o field of regard. BNS will employ their current liquid crystal polarization grating (LCPG) technology and ferroelectric liquid crystal (FLC) switches to meet scanner speed and resolution requirements.  Advantages of applying BNS’ LCPG and switch component technology specific to the space-based Lidar applications will include accuracy, reliability, and improved SWaP as well as high rate (at least 1 kHz ) scanning.  In addition, BNS will develop low SWaP dedicated drive electronics and environmentally test the scanner prototype which will be built in Phase II. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Possible commercial applications include the use of this technology for wind farms, automotive hazard avoidance and headlight steering, and remote sensing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to the Entry, Descent and Landing as well as remote wind sensing application, a low-SWaP beam control system could be used in NASA?s hazard avoidance applications (Docking, Entry, Descent and Landing). The Phase II prototype implementation will serve to demonstrate the beam scanning capability, environmental survivability, as well as optimize size, weight and power. The resultant beam control system will be transitioned to Lidar systems integrators and eventually into a commercial product.

TECHNOLOGY TAXONOMY MAPPING (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.)
Polymers
Gratings
Entry, Descent, & Landing (see also Astronautics)
Optical
Ranging/Tracking
Optical/Photonic (see also Photonics)
Positioning (Attitude Determination, Location X-Y-Z)
Infrared
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
3D Imaging


PROPOSAL NUMBER:17-2 S1.01-8897
PHASE-1 CONTRACT NUMBER:NNX17CL42P
SUBTOPIC TITLE: Lidar Remote Sensing Technologies
PROPOSAL TITLE: Autonomous Alignment Advancements for Eye-Safe Coherent Lidar

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Beyond Photonics, LLC
6205 Lookout Road, Suite B
Lafayette, CO
80026-8868
(303) 475-2088

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sammy Henderson
sammy@beyondphotonics.com
6205 Lookout Road, Ste. B
Boulder,  CO 80301-3334
(303) 396-8536

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
<p>In this Phase II effort we propose to advance the development of autonomous alignment technology allowing improved performance and reliability from coherent lidar systems and demonstrate the technologies in a working coherent lidar system.&nbsp; Eye-safe coherent lidar technology holds great promise of meeting NASA&#39;s demanding remote 3D space winds goal near term. &nbsp;Highly autonomous, long-range coherent lidar systems may however suffer significant signal loss due to environment-induced component misalignment, as well as varying receiver lag-angle alignment errors in space-based platform applications.&nbsp; Although such systems can be engineered with the required alignment stability, the overall size, mass, and cost to produce coherent lidar systems will benefit from incorporating technology into the design that allows alignment to be optimized automatically while the system is in the field.&nbsp; Autonomous space- and air-borne lidar systems will especially benefit, where maintaining peak performance is critical without regular human intervention.&nbsp; Auto-alignment technologies will result in lower-cost lidar sensors with greater autonomy and less-exotic opto-mechanics, spurring strong commercial potential due to the rapid introduction of lidar systems into the commercial marketplace for various applications.&nbsp; The technology aimed at maintaining laser and lidar alignment also has potential to correct for receiver lag angle in fast-scanning long-range lidar systems, which will facilitate faster scan rates, larger apertures, and greater area coverage rate capability.&nbsp; Beyond Photonics has a strong interest in solving these technological problems for relevant ground-based, airborne, and space-based unattended lidar systems.&nbsp; This Phase II effort will further mature auto-alignment designs exhibiting a high level of synergy between NASA&#39;s and other commercial vendors&rsquo; requirements for laser auto-alignment, transmit/receive transceiver auto-alignment, and receiver lag angle compensation.</p>

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA, commercial applications for the lower-cost, higher reliability autonomous coherent laser radar sensors that would be realized from the proposed Phase II work include, use of such systems in wind energy management and site location applications; at airports for detection of hazardous aircraft wake vortices and wind shear, increasing airport operating efficiency; hard-target sensing, identification, and imaging applications. Future very-compact and low-cost implementations of auto-alignment capability has potential for application in compact lidar systems for autonomous air and ground vehicle obstacle avoidance and navigation. Auto-alignment functionality will find many commercial and industrial research applications wherever two or more beams need to be aligned to each other, such as is often required in non-linear optics, IR spectroscopy and coherent sensing applications (e.g. FT-IR spectroscopy; OCT imaging technology), coherent lasers beam combination for power scaling, coherent communications, and single-mode fiber beam combination and management.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications for the lower-cost, higher-reliability autonomous laser and lidar alignment technology described in this Phase II proposal include current and upcoming programs like NASA LaRC's WIND-SP; the existing NASA LaRC DAWN lidar system (which currently suffers from thermally-induced environmental system misalignment that would readily be addressed by this technology with very low impact on existing architecture); and future generations of this wind measurement lidar system, particularly, space-based instruments with poor or impractical access for on-site system maintenance. The technology can be easily extended to other wavelengths (e.g. 1.55-1.6 um), which could directly benefit NASA programs aimed at atmospheric CO2 or CH4 measurement using lidar systems and other laser remote sensing efforts where long-duration unattended operation is key. Space-based applications are of particular interest.

TECHNOLOGY TAXONOMY MAPPING
Lasers (Ladar/Lidar)
Optical/Photonic (see also Photonics)
Autonomous Control (see also Control & Monitoring)
Process Monitoring & Control


PROPOSAL NUMBER:17-2 S1.01-9205
PHASE-I CONTRACT NUMBER:NNX17CL82P
SUBTOPIC TITLE: Lidar Remote Sensing Technologies
PROPOSAL TITLE: Compact Integrated DBR Laser Source for Absorption Lidar Instruments
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Photodigm, Inc.
1155 East Collins Boulevard, #200
Richardson,TX 75081 -2304 (972) 235-7584
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Annie Xiang
axiang@photodigm.com
1155 East Collins Boulevard, #200
Richardson ,TX 75081 -2304
(972) 235-7584 Ext: 2240

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Modern water vapor differential absorption lidar (WV-DIAL) uses a single frequency distributed Bragg reflector (DBR) laser diode to seed a pulsed semiconductor amplifier. To meet the demand of these advanced instruments, the development of DBR lasers at multiple wavelengths in the 700-950nm region is required. 

Current DIAL systems use free-space lasers that require bulk optics and are subject to misalignment and contamination. A compact integrated laser module is desirable for future cost-effective, rugged and fieldable systems.

Build on the design and prototype demonstration of Phase I, we propose to further the development of the compact integrated laser modules. Our approach, with the fabrication of high precision DBR laser of 935nm and 817nm wavelengths; and the package engineering of compact integration, will provide the narrow linewidth and high power laser modules for numerous Lidar applications with the advantages of reduced size, weight and power (SWaP).

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The compact integrated laser modules are the turn-key solutions for single frequency laser source at 935nm and 817nm. The narrow linewidth and high power laser modules find applications in spectroscopy, remote sensing and biometrics. Its spectral stability is desirable in resolving hyperfine structures and in providing long coherent length. Its compactness is suitable for handheld instruments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA's primary application for the compact integration laser module is the differential absorption lidar (DIAL) instrument development for an autonomous field sensor network mapping atmospheric water vapor. This application is well aligned with the Science Mission Directorate (SMD) instrument development program through the implement of smaller and more affordable DIAL transmitters and is an important step towards water vapor DIAL deployment in air and in space.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Ladar/Lidar)


PROPOSAL NUMBER:17-2 S1.02-9097
PHASE-I CONTRACT NUMBER:NNX17CG73P
SUBTOPIC TITLE: Technologies for Active Microwave Remote Sensing
PROPOSAL TITLE: Deployable Microwave Antennas for CubeSats, NanoSats, and SmallSats
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Boulder Environmental Sciences and Technology
5171 Eldorado Springs Drive, Suite A
Boulder,CO 80303 -9672 (303) 532-1198
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tristen Hohman
tristen.hohman@boulderest.com
5171 Eldorado Springs Drive, Suite A,
Boulder ,CO 80303 -9672
(303) 532-1198 Ext: 115

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The goal of this project is to develop an offset-fed paraboloidal mesh reflector antenna for operation onboard small, low cost satellites such as CubeSats, in the frequency range up to 100 GHz. The Phase II component of this goal is to fully test the performance characteristics of a prototype deployable antenna reflector, with an aperture greater than 0.5 m under controlled conditions. The mesh used in the reflector is gold plated molybdenum. The weave of the mesh will be developed early in Phase II to achieve the tight tolerances required for operation up to 100 GHz (W-Band). Characterization measurements of the currently available mesh have been completed and will be used as a baseline to quantify improvements measured from the newly developed mesh samples. Analysis of surface error contributions from faceting, thermal stresses, manufacturing tolerances, and operational forces will be performed. Micro-machining and small-scale manufacturing techniques will be refined to achieve an overall reflector surface accuracy of less than 60 micrometers (1/50 of the wavelength at 100 GHz).

The fully constructed mesh reflector antenna with feed will be measured to obtain the full gain pattern of the antenna to characterize the antenna performance and determine the overall efficiency of the mesh reflector. The deployment mechanism will also be tested and refined to ensure repeatable operation of the antenna.

The proposed antenna can be stowed within less than 1.5 U of a CubeSat. Doing so can significantly lower the cost of any satellite system requiring a high gain reflector antenna, including radars, scatterometers, radiometers, and deep space communication links. Successful completion of the Phase II goals will increase the technical readiness of the project from TRL 3, at the end of Phase I, to TRL 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Compact antennas stowable within CubeSats, NanoSats and SmallSats have a potential to open new observational capabilities to private markets. Several private companies are in or are entering into the nano/microsatellite market, with companies like Spire and PlanetLabs already operating constellations of CubeSats, and with constellations planned by OneWeb, SpaceX, Boeing, and Samsung. While these companies are not specifically focused on Earth Observations (EO), they pave the way for privatization of EO and signal a growing need for antennas such as the one proposed here.
Military agencies could also benefit from this technology, with a desire for constellations of smaller satellites due to cost reductions and the opportunity of frequent technology refesh. The proposed antenna is not limited to remote sensing applications, and could equally be applied to communication purposes, with its high stowing efficiency enabling larger apertures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Any NASA mission that requires a microwave antenna, or a microwave sensor, will benefit from the compact deployable offset parabolic reflector antenna proposed here. Such a reflector antenna can be used for active and passive microwave remote sensing, communication systems, and other applications. Apertures up to 2 m can use a similar approach, operating up to 100 GHz. A 0.55 meter aperture stows in a diameter of 55 mm, a length of 117 mm, and a mass of 0.25 kg; a 1.2 m aperture stows in a diameter of 14.4 cm, a length of 21.3 cm, and a mass of 0.6 kg; and a 2 m aperture stows in a diameter of 24 cm, a length of 35.4 cm, and a mass of approximately 1 kg.
Such compact antennas have a potential to significantly lower NASA costs for Earth observing systems and enable Solar system exploration with much more compact spacecrafts, such as CubeSats. This reduction in costs and the increased operational frequency of the proposed antenna would allow the creation of CubeSat constellations for the same cost as a single traditional satellite, such as ATMS. This has the potential to significantly increase the revisit time of a specific area for a given mission, drastically improving the utility of such applications. Several existing NASA funded programs, such as TROPICS and TEMPEST-D, could also greatly benefit from the inclusion of an antenna like the one proposed here.

TECHNOLOGY TAXONOMY MAPPING (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.)
Electromagnetic
Radiometric
Microwave
Antennas
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)


PROPOSAL NUMBER:17-2 S1.02-9250
PHASE-I CONTRACT NUMBER:NNX17CP70P
SUBTOPIC TITLE: Technologies for Active Microwave Remote Sensing
PROPOSAL TITLE: Enabling Larger Deployable Ka-Band Antenna Apertures with Novel Rib
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tendeg, LLC
686 South Taylor Avenue, Suite 108
Louisville,CO 80027 -3000 (303) 929-4466
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gregg Freebury
gregg@tendeg.com
686 South Taylor Avenue, Suite 108
Louisville ,CO 80027 -3000
(303) 929-4466

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The significance and relevance of the proposed innovation is to design and develop a novel rib that will enable 2-6m aperture parabolic reflectors and antennas for smallsats.  The rib will be rollable and allow 100: 1 compaction ratios.  It will provide deployment authority and deployed structural integrity meeting Ka-band precision requirements. Higher communication data rates, longer transmission distances, increased sensor capacity for active radar and radiometers are all directly related to larger aperture sizes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There is strong market growth in CubeSat up to smallsat size satellites in the commercial arena. Numerous communications, data transfer and Earth observation constellations are planned. Many of them would benefit from a lightweight, small packaged volume, high gain antenna. In the terrestrial market, the U.S. Military is seeking man-packable high gain antennas for forward operating Warfighters.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed innovation relative to NASA needs will be focused on small to medium aperture antennas up to Ka-band and used for Earth observing science missions (RainCube radar, radiometers), deep space communications, and any mission needing high data rate down links. The rib technology would enable larger apertures for any higher gain mission needs.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Metallics
Deployment
Machines/Mechanical Subsystems
Structures
Analytical Methods
Antennas
Command & Control
Characterization
Prototyping


PROPOSAL NUMBER:17-2 S1.02-9973
PHASE-I CONTRACT NUMBER:NNX17CP53P
SUBTOPIC TITLE: Technologies for Active Microwave Remote Sensing
PROPOSAL TITLE: Deployable Ku/Ka/W Tri-Band Cylindrical Parabolic Antenna
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MMA Design, LLC
P.O. Box 7804
Loveland,CO 80537 -0804 (970) 290-6426
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christopher Pelzmann
capelzmann@mmadesigmllc.com
2555 55th St. Suite 104
Boulder ,CO 80301 -5729
(720) 728-8491

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

MMA has proposed a technical approach creates a highly simplistic antenna architecture by taking advantage of natural mechanics of high-strain composite materials to create a 1D parabolic reflector surface. At smaller scales (1-2 m2), the architecture allows continuous reflector surfaces for ESPA-class spacecraft, while at larger scales a modular architecture is taken advantage of to produce much larger apertures without requiring comparatively large spacecraft. The effort will develop a large aperture at Ku, Ka, and W frequencies using rollable shell surfaces that combine the surface accuracy of rigid reflectors with the packaging advantages of flexible reflectors.  Developing a stowable, “morphing”, high-strain composite reflector surface with sufficient surface roughness and position knowledge for frequencies up to 94 GHz will enable large apertures with reduced stowed envelope and can dramatically reduce the hardware, instrument and mission implementation costs. Originally inspired by the shape of a beam being deflected under load, MMA is using analysis and lab testing to determine the prescribed loading configuration capable of deflecting a semi-rigid member into a parabolic curve. By using the mechanics of bending rather than molding and manufacturing to prescribe the reflector’s shape, the system provides a repeatable method of forming a parabolic surface. This architecture lends itself to a structurally simple system, providing high reliability and low complexity. Phase I efforts demonstrated through analysis and prototyping that loading conditions exist for isotropic beams to form a surface closely matching a parabola, while RF performance simulations verified the reflector’s ability to perform with minimal gain losses up to 95 GHz. The phase II effort will build upon this early development to design, build, and test a deployable tri-band antenna system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The same economic drivers that support NASA commercialization of this technology apply to non-NASA markets. The DoD, foreign countries, and commercial interests are all in need of improved, timely weather data.
The U.S. military has expressed interest in smaller, lower cost, dis-aggregated satellite system architectures that support rapid upgrades and replacements. This technology can support such efforts in precipitation measurement, hurricanes, ocean surface winds and many more weather needs with more accurate and timely data availability from low earth orbits.
Many countries suffer the negative effects of typhoons and hurricanes and actively fund low cost weather satellite missions that can be greatly enhanced by this antenna technology.
Commercial entities are also potential data consumers for such efforts as disaster relief and assessments of weather damage, agricultural impacts, etc.
As mentioned above, the wide band capability of this technology also supports a wide range of other RF applications that will also drive commercialization of this antenna/reflector technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA utilizes multi-band radar for precipitation and moisture related weather monitoring instruments. Recent missions have incorporated large, expensive antenna systems that drive large mission costs such as the Global Precipitation Measurement Mission ($1B). The availability of a relatively large aperture (2 square meters) that performs at Ku/Ka/W frequencies but can stow in a small volume (~.001 cubic meters) enables missions to be conducted on much smaller, less expensive satellite platforms (300-400 kg ESPA/ESPA Grande) that can be launched as secondary payloads on larger rockets, or utilize many of the emerging lower cost rockets for a dedicated launch. This approach supports rapid deployment of experimental missions as well a mission which utilizes multiple satellites in a constellation to provide faster revisit times and also enables instrument upgrades and rapid, low cost replacement/replenishment.
The broad frequency capabilities of this antenna technology also support commercialization into other RF applications required by NASA including communications, other applications of RF remote sensing and imaging, etc.

TECHNOLOGY TAXONOMY MAPPING (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.)
Electromagnetic
Microwave
Radio


PROPOSAL NUMBER:17-2 S1.03-8764
PHASE-I CONTRACT NUMBER:NNX17CG58P
SUBTOPIC TITLE: Technologies for Passive Microwave Remote Sensing
PROPOSAL TITLE: Low-Power Radiation Tolerant 4GHz Bandwidth 16k Channel Spectrometer ASIC
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pacific Microchip Corporation
3916 Sepulveda Boulevard, #108
Culver City,CA 90230 -4650 (310) 683-2628
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Aliaksandr Zhankevich
alex.zh@pacificmicrochip.com
3916 Sepulveda Boulevard, #108
Culver City ,CA 90230 -4650
(310) 683-2628 Ext: 20

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Spectrometers currently employed by NASA include field programmable arrays (FPGAs), analog to digital converters (ADCs) and a number of other discrete components assembled on a printed circuit board (PCB). An application specific integrated circuit (ASIC) based spectrometer offers a great reduction in weight, volume and power consumption compared to the FPGA/PCB based implementation. This proposal aims to develop a low-power (LP) poly-phase spectrometer (PPS) ASIC. The proposed ASIC aims to achieve a 4GHz bandwidth and 8192 usable frequency bins. In order to implement the required functionality and meet the specifications while consuming below 1.5W of power, the proposed ASIC will include a state-of-the-art 6-bit ADC, a demultiplexer, a poly-phase filter bank, a windowing function, a fast-Fourier-transform core, a frequency-domain data analysis block, a data readout, a digital control unit and testing features. Tolerance to at least 500Krads of total ionizing dose (TID) radiation will be achieved by implementing the ASIC using an ultra-thin gate oxide CMOS technology. Low power consumption will be achieved by employing special multiplier-less-accumulators and multiplier-less-“butterflies”. The power consumption will be further reduced by minimizing the redundant states in the poly-phase filter’s FIR and IFFT block. Additional power-saving can be achieved by switching off the ASIC’s unused blocks, and by internally dividing the clock frequency. Phase I work provided the proof of feasibility of implementing the proposed spectrometer ASIC. Phase II will result in the silicon proven ASIC’s prototypes ready for commercialization in Phase III.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In addition to its primary application in the NASA's spectrometer systems, the proposed ASIC will be targeting applications in commercial, military and other scientific exploration systems which require small size, low power, radiation hardened spectrometers. Commercial and military applications include spectrometers employed on satellites, aircraft and air balloons for remote sensing and surveillance to process the data from synthetic aperture radars, sonars, or visible light/infrared/UV image detectors. Space, airborne and ground based remote sensing instruments employed by Environmental Protection Agency (EPA) and National Oceanic and Atmospheric Administration (NOAA) require high precision spectrometers for temperature, water vapor, pollutant, ozone and other exploration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed spectrometer ASIC will greatly reduce the size, complexity, power consumption and will increase reliability of spectrometer instruments. These spectrometers are required for current and future space borne and airborne NASA's passive remote sensing instruments for exploration of the cosmic microwave background, the Earth's atmosphere and its surface. Specific missions include: A-SLMS, CAMEO, GACM, GeoSTAR, HyspIRI and GEO-CAPE. In addition, the proposed ASIC can find application in Earth based radio telescopes used for radio astronomy.

TECHNOLOGY TAXONOMY MAPPING (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.)
Microwave
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)


PROPOSAL NUMBER:17-2 S1.03-9385
PHASE-I CONTRACT NUMBER:NNX17CP60P
SUBTOPIC TITLE: Technologies for Passive Microwave Remote Sensing
PROPOSAL TITLE: Correlation Radiometer ASIC
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pacific Microchip Corporation
3916 Sepulveda Boulevard, #108
Culver City,CA 90230 -4650 (310) 683-2628
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Anton Karnitski
anton@pacificmicrochip.com
3916 Sepulveda Boulevard, #108
Culver City ,CA 90230 -4650
(310) 683-2628 Ext: 19

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposed project aims to develop an application specific integrated circuit (ASIC) for the NASA’s microwave correlation radiometers required for space and airborne Earth sensing applications. The radiometer instrumentation installed on CubeSats and SmallSats is required to have small volume, low weight and consume low power. Currently used correlating radiometers rely on analog signal processing, thus are bulky, power hungry and cannot be reprogrammed. Analog filter parameters tend to be unstable over temperature, power supply voltage, may degrade over time, and need tuning.

The proposed low-power, rad-hard ASIC will operate with microwave correlation radiometer front ends down-converting the RF to up to 10GHz IF quadrature signals. The ASIC will include digitizers, bandpass filters, cross-correlators, totalizers, serializers, an output data interface, and an I2C interface for the ASIC’s programming. Bandpass filters will split up the digitized quadrature IF input signals into bands (up to 16), will cross-correlate the signals within each band, and will ship out the resultant data in a convenient format. Instead of analog signal processing performing a strictly defined function, the ASIC will employ a digital signal processing which can be reprogrammed to adopt specific parameters of the filter block such as the number of bands, each filter’s corner frequency, bandwidth and filter’s order. A number of innovations will be introduced to the ASIC in order to combine programmability, low power consumption and radiation tolerance.

The project’s Phase I will provide the proof of feasibility of implementing the proposed ASIC. Phase II will include finishing the design, chip fabrication, testing and delivering the ADC prototypes which will be ready for commercialization in Phase III.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In addition to its primary application in the NASA's correlation radiometry systems, the proposed ASIC is targeted for other commercial and military related systems which require small size, low power, radiation hardened radiometers. Commercial applications include radiometers employed on communication, remote sensing and navigation satellites. With the increasing deployment of small size satellites, compact radiometer based positioning is essential as well as it is crucial for swarms of satellites that should maintain certain formation. Possible military applications include satellites used for communication and surveillance. Another area of application includes synthetic aperture radar receiver modules. In case of the Environmental Protection Agency (EPA) and the National Oceanic and Atmospheric Administration (NOAA), both space and ground based remote sensing instruments require high precision radiometers for temperature, water vapor, pollutant, ozone and other exploration. Radiometers used for thermal imaging in security systems is yet another application area for the proposed ASIC.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed correlation radiometer back end ASIC combining signal normalization, digitizing, programmable digital bandpass filtering and cross-correlation functions is expected to greatly reduce the size, complexity, power consumption and reliability of radiometer instruments. These radiometers are required for the current and future NASA's passive remote sensing instruments within Earth, planet and sun exploration missions. In addition, the proposed ASIC can find application in radiometers required for radio astronomy for measurements of the properties of the Cosmic Microwave Background (CMB). Distributed Spacecraft Missions (DSM) including Constellations, Formation Flying missions, or Fractionated missions using CubeSats or SmallSats require precise position synchronization between satellites which can be implemented by using correlation radiometers tracking a common radiation source.

TECHNOLOGY TAXONOMY MAPPING (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.)
Infrared
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)


PROPOSAL NUMBER:17-2 S1.04-8477
PHASE-I CONTRACT NUMBER:NNX17CG62P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: VLWIR Sensors for Detecting and Tracking Near-Earth Asteroids
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
QmagiQ
22 Cotton Road, Unit H, Suite 180
Nashua,NH 03063 -4219 (603) 821-3092
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mani Sundaram
msundaram@qmagiq.com
22 Cotton Road, Unit H, Suite 180
Nashua ,NH 03063 -4219
(603) 821-3092 Ext: 200

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

An important NASA mission is to detect, count and track near-earth asteroids for a variety of reasons including the hazards of collisions with our planet. Such asteroids are mostly dark, small and cold (~ 200K); so they are best detected in the very longwave infrared (VLWIR) wavelengths greater than ~ 12 microns where they glow brightest. To accomplish this, we developed in Phase I a record-performing focal plane array (FPA) of antimony-based strained layer superlattices (SLS) with cutoff wavelength = 13.5 microns, quantum efficiency = 30-50% in the 3.0-13.5 micron spectral band, dark current = 1/4th that of incumbent mercury cadmium telluride (MCT) per Rule07,  and operating with background-limited-performance (BLIP) at 75K with superb array uniformity, operability and image stability.  In Phase II, we propose to increase array format to 1024x1024, integrate the FPA with three spectral filters (one fire channel and two thermal channels), and package it into a compact camera.  The camera will be delivered to NASA for evaluation for missions like Landsat Data Continuity Mission - Thermal Infrared Sensor (LDCM-TIRS), where it will offer greater ground resolution in a small, lightweight, low-power package.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
1) FTIR imaging microscopy
2) Hyperspectral imaging
3) Gas imaging (e.g. for the petrochemical and power utility industries)
4) Security and surveillance (day and night)
5) Medical imaging
6) Missile defense
7) Space-based situational awareness

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
1) LANDSAT Data Continuity Mission: Thermal Infrared Sensor (LDCM-TIRS)
2) HyspIRI Multispectral: Thermal Infrared (TIR) Imager
3) Astronomy of distant dim objects (e.g. James Webb Space Telescope,
planetary missions, etc.)
4) Spectral mapping of vegetation/crops/forest-cover
5) Pollution monitoring / Atmospheric chemistry
6) Thermal mapping of landmasses/oceans

TECHNOLOGY TAXONOMY MAPPING (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.)
Detectors (see also Sensors)
Optical/Photonic (see also Photonics)
Radiometric
Thermal
Infrared
Multispectral/Hyperspectral
Materials (Insulator, Semiconductor, Substrate)
Thermal Imaging (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 S1.04-8720
PHASE-I CONTRACT NUMBER:NNX17CG57P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: Wafer level Integration on PolyStrata(R) Interposer (WIPI) Phase II (17028)
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nuvotronics, Inc.
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
contracts@nuvotronics.com
2305 Presidential Drive
Durham ,NC 27703 -8074
(800) 341-2333

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Over the course of this program, Nuvotronics will develop of a robust wafer-level chip integration technology using our proprietary PolyStrata® process to enable sub-millimeter monolithic integrated chip (IC). This new process offers a disruptive wafer level packaging, capable of monolithically integrating dis-similar semiconductor substrates such as silicon, SiGe, GaAs, GaN and InP while reducing the interconnects losses and removing the need wirebonds. Using the 8” PolyStrata process on wafer, different chips (Low Noise Amplifiers, PAs, Mixers, switches) can be monolithically integrated and interconnected using copper microfabrication process to create a IC module. To demonstrate the performance of the new wafer level packaging approach, during the Phase II, Nuvotronics will leverage the new process to fabricate a complete W-band monolithic radiometer IC. The PolyStrata IC will be surface mountable using industry standard reflow process and will not require wirebonding, high accuracy placements or expensive RF circuit board. Nuvotronics aimed in this program a revolutionizing the way mm-wave circuit are fabricated by improving the interconnection performance up to 220 GHz and significantly reducing the packaging cost.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The number of backhaul radios operating at E-band and even D-band are growing rapidly to provide a faster wireless network. Access Point-to-point and point to multi-point datalinks are expected to rapidly increase to fill the 5G network requirements and will require cost effective mm-wave hardware.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
- NASA Goddard is looking at possible insertion of this technology in measurement instruments for radiometry in a CubeSat payload. Integration of MMICs at frequency above 60GHz requires challenging processes such accurate die placement and ultra-short wirebonds to ensure repeatable performance.
- Mapping gas-tracing spectral lines to study Star formation in galactic molecular gas clouds.
- Mapping low surface brightness emission, like large-scale structure, with existing millimeter-wave interferometers to enhanced with small focal plane arrays on each telescope that would increase the field of view.
- Earth science remote sensing missions, such as the Cloud Precipitation Processes Mission (CaPPM)
- Possible: Snow and Cold Land Processes (SCLP) mission

TECHNOLOGY TAXONOMY MAPPING (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.)
Aerogels
Ceramics
Nanomaterials
Microelectromechanical Systems (MEMS) and smaller
Amplifiers/Repeaters/Translators
Antennas
Manufacturing Methods
Materials (Insulator, Semiconductor, Substrate)
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)
Processing Methods


PROPOSAL NUMBER:17-2 S1.04-8763
PHASE-I CONTRACT NUMBER:NNX17CP61P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: A Low Power Rad-Hard ADC for the KID Readout Electronics
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pacific Microchip Corporation
3916 Sepulveda Boulevard, #108
Culver City,CA 90230 -4650 (310) 683-2628
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Aliaksandr Zhankevich
alex.zh@pacificmicrochip.com
3916 Sepulveda Boulevard, #108
Culver City ,CA 90230 -4650
(310) 683-2628 Ext: 20

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposal aims to develop an analog-to-digital converter (ADC) required for the Kinetic Inductance Detector (KID) readout electronics. KIDs are developed for photometers and spectrometers for astrophysics focal planes, and earth or planetary remote sensing instruments. ADCs employed in space based KIDs are required to combine several features: radiation hardness, low power consumption, high resolution and high-sampling rate to facilitate increase in the number of the readout tones and to reduce the size of the electronics.

The proposed SAR ADC aims to achieve a 12-bit resolution and the lowest to date reported figure of merit (FOM) at the 1GSps rate. A number of innovations will be introduced to the ADC in order to combine low power consumption (below 100mW) with the signal to noise and distortion ratio (SINAD) of at least 65dB. Tolerance to at least 100Krads of total ionizing dose (TID) radiation will be achieved through application of ultra-thin gate oxide CMOS technology. A novel calibration technique for the capacitor mismatch will be introduced to improve linearity and increase the sampling rate. The proposed calibration technique introduced to the sub-ranging architecture with application of the asynchronous SAR logic will facilitate reduction of switching power.

Phase I work provided the proof of feasibility of implementing the proposed ADC. Phase II will result in the silicon proven ADC prototypes being ready for commercialization in Phase III.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The potential commercial applications for the proposed low power ADC include electronic systems employed in communication and scientific satellites, high-energy physics instruments, and medical X-ray imaging equipment. The proposed ADC can also find application in instruments and devices which require low power consumption, such as portable devices employing wireless data transmission based on WiFi, WiMAX and WiGig specifications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed ADC is primarily targeted for application in the Kinetic Inductance Detector and will meet the NASA's expectations for the radiation hardened low power ADC required for the detector's readout electronics. The ADC will also be applicable for other NASA missions since it offers a flexible solution for meeting the stringent radiation tolerance and power consumption requirements that are essential in L-band and P-band radars, an advanced synthetic aperture radar (SAR), an interferometer for surface monitoring, ice topography, hydrology, oceanography.

TECHNOLOGY TAXONOMY MAPPING (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.)
Sensor Nodes & Webs (see also Communications, Networking & Signal Transport)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)


PROPOSAL NUMBER:17-2 S1.04-9669
PHASE-I CONTRACT NUMBER:NNX17CP49P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: Tunable, High-Power Terahertz Quantum Cascade Laser Local Oscillator
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
LongWave Photonics
958 San Leandro Avenue
Mountain View,CA 94043 -1996 (617) 399-6405
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tsungyu Kao
wilt_kao@longwavephotonics.com
958 San Leandro Avenue
Mountain View ,CA 94043 -1996
(617) 399-6405

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA and NASA funded missions/instruments such as Aura/MLS (Microwave Limb Sounder), SOFIA/GREAT and STO/STO-2 have demonstrated the need for local oscillator (LO) sources between 30 and 300 um (1 and 10 THz). For observations >2 THz, technologically mature microwave sources typically have microwatt power levels which are insufficient to act as LOs for a heterodyne receivers. LongWave Photonics is proposing to develop a high power, frequency tunable, phase/frequency-locked, single mode, External Cavity THz quantum cascade laser (ECT-QCL) system with >2 mW average power output and a clear path to increase the power to >10 mW. The system includes a THz QC gain chip based on SISP or metal-metal waveguide with an integrated horn or lens structure to reduce facet reflectivity. Frequency selective external feedback will be tunable over 100's of GHz, with center frequencies ranging from 2 to 5 THz. The gain chip will be packaged in a high-reliability Stirling cycle cooler with all external component integrated under the same enclosure.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Initial applications for this technology are mainly research markets for low-pressure gas spectroscopy. The narrow line width and the ability to provide real-time frequency information and frequency tunability of THz radiation also has great appeal. Another potential application is to replace THz gas laser used for THz detector power calibration. Long-term applications include industrial uses for trace gas detection. For industrial applications, the use of high-reliability, compact Stirling cycle coolers would greatly increase the usability of these QCL devices, which have traditionally required liquid nitrogen cooling or larger cryocooling systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA applications include the use of the QCL as an LO for >2 THz receivers for future missions. Here the narrow linewidth (<100 kHz) of the QCLs can be used to resolve Doppler-limited low-pressure gasses (~MHz linewidth). The external cavity QCL LO will be a frequency tunable, compact replacement for any gas-laser LO. The resulting source will be a compact, reliable, table-top sized THz high power with narrow linewidth . It will be an easy-to-use platform for NASA researchers to study the performance of other key components in the receiver such as Schottky or HEB mixers. THz QC gain chip can also be used as the power amplifier providing gain for solid-state frequency multiplier or as the low noise preamplifier in the heterodyne receiver to reduce overall noise temperature.

TECHNOLOGY TAXONOMY MAPPING (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.)
Detectors (see also Sensors)
Lasers (Measuring/Sensing)
Chemical/Environmental (see also Biological Health/Life Support)
Electromagnetic
Optical/Photonic (see also Photonics)
Radiometric
Terahertz (Sub-millimeter)
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)


PROPOSAL NUMBER:17-2 S1.05-8877
PHASE-I CONTRACT NUMBER:NNX17CL77P
SUBTOPIC TITLE: Detector Technologies for UV, X-Ray, Gamma-Ray and Cosmic-Ray Instruments
PROPOSAL TITLE: Design and Development of High Gain AlGaN Avalanche Photodiode Arrays
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Magnolia Optical Technologies, Inc.
52 B Cummings Park, #314
Woburn,MA 01801 -2123 (781) 503-1200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ashok Sood
aksood@magnoliaoptical.com
52 B Cummings Park, Suite 314
Woburn ,MA 01801 -2123
(617) 429-7113

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Future NASA earth science systems and missions, specifically those involving high resolution Lidar measurements, will benefit from the development of large-area, high gain AlGaN ultraviolet avalanche photodiodes (UV-APD) arrays operating at room temperature at the 355 nm wavelength. The high quality GaN/AlGaN UV-APD detector arrays are epitaxially grown using an optimized metal organic chemical vapor deposition (MOCVD) technique. The use of lattice-matched bulk GaN substrates provides low dark/leakage current by minimizing defects from the substrate, while alternately AlN substrates can be used to provide backside-illuminated, high fill factor UV-APD devices. In addition to low dark current noise, the solid-state UV-APD devices demonstrate high quantum efficiencies with very high avalanche gains (>10^5). For the Phase II SBIR effort, we shall model, design, develop, and demonstrate the AlGaN UV-APD array technology for implementation in future NASA missions. We will work with NASA for modelling UV-APD arrays for performance improvements in NASA Earth Science systems. Magnolia will collaborate with Prof. Russ Dupuis of Georgia Tech, an expert in III-N material growth and device technology, for MOCVD growth, fabrication, and characterization of the UV-APD array devices. This will entail the enhancement of surface passivation techniques for further performance improvements, developing high quality, low resistivity n- and p-type contacts, as well as incorporating antireflection coatings. It is expected based on measurement data that these devices can perform in Geiger-mode at ~355 nm with high single-photon detection efficiencies for operation in photon-starved environments. Based in part on results attained from the Phase I effort, the AlGaN-based UV-APD technology can meet and/or exceed system requirements in applications such as high resolution Lidar to benefit NASA systems for advancing future missions

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
UV Detectors and Sensors are useful in a wide variety of industrial, military, and scientific applications where detection of UV radiation plays a key role. Most of these applications for UV detection and/or measurement require high performance UV-APD detector arrays and sensor systems. Ultraviolet APD arrays with high gain can capture unique target signatures, which provide critical information for applications that include machine vision, threat warning, and chemical and biological applications for detection of surface residues and biological agents. Within the Defense applications of interest are UV sensing devices to identify chemical/biological threats to war-fighters, early missile threat warning systems, and jet flame/engine monitoring. This market is segmented into four broad sectors: industrial, consumer electronics, automotive, and medical. A number of these commercial applications can directly benefit from the performance capabilities and features of the AlGaN UV-APD detector technology. Such applications include UV sensors in automobiles for improved safety, stability, and performance; detection of arcing and corona discharge in power-lines and industrial monitoring of UV radiation. In addition, the commercial UV sensor market is projected to grow substantially over the next 10 years.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Future NASA missions will require high gain UVAPD large area detector arrays.The NASA earth science application for the AlGaN UV-APD arrays. operating at the 355 nm UV band is of interest for high resolution Lidar systems. To resolve extremely weak/distant signals in such applications, detector arrays with large areas and very high gains are required. The objective of the Proposed NASA Phase II SBIR is to model, design, and develop the necessary technology for high performance GaN/AlGaN UV-APDs that can be implemented in future NASA missions. The technology developed under the proposed Phase II SBIR Program can also be applied to other NASA measurement instruments. The implementation of the technology can benefit situations requiring replacement aging and/or proprietary technologies with compact, less costly solid-state solutions. As part of the Phase II SBIR effort, we will work with NASA Program Manager towards application of the UV-APDs for other NASA programs and missions. The AlGaN-based UV-APDs allow band gap engineering for fine-tuning of the operating wavelength to UV band of interest. The solid-state UV-APDs devices are also radiation hardened and offer high chemical and thermal stability, making them well-suited for harsh operating conditions and environments such as in space-based applications. Such applications could include ozone/pollutant monitoring, and measurement of UV signatures

TECHNOLOGY TAXONOMY MAPPING (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.)
Smart/Multifunctional Materials
Detectors (see also Sensors)
Lasers (Ladar/Lidar)
Materials & Structures (including Optoelectronics)
Optical/Photonic (see also Photonics)
Ultraviolet
Materials (Insulator, Semiconductor, Substrate)
Characterization
Models & Simulations (see also Testing & Evaluation)
Prototyping


PROPOSAL NUMBER:17-2 S1.06-9292
PHASE-I CONTRACT NUMBER:NNX17CG66P
SUBTOPIC TITLE: Particles and Field Sensors and Instrument Enabling Technologies
PROPOSAL TITLE: Simplified High-Performance Roll Out Composite Magnetometer Boom
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ROCCOR, LLC
2602 Clover Basin Drive, Suite D
Longmont,CO 80503 -7555 (720) 200-0068
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dana Turse
dana.turse@roccor.com
2602 Clover Basin Drive, Suite D
Longmont ,CO 80503 -7555
(303) 908-7649

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

In response to NASA’s need for compact, low-cost deployable magnetometer booms for CubeSats, Roccor proposes to develop a Simple High-performance Roll-Out Composite (SHROC™) Magnetometer Boom.  The boom is capable of motor-less self-deployment and lock-out through a unique combination of bi-stable composite laminate design and features that increase torsional rigidity and deployed precision at the end of deployment.  The boom can be built to diameters ranging between 1.6 cm (5/8 in) and 2.5 cm (1 in) and fully deployed lengths ranging from 0.5 m to 10 m while being packaged in less than ½-U volume.  A launch-retention mechanism is provided to lock the tip-mounted instrument package for launch.  For deployment, this launch retention mechanism is released and the strain energy stored within the high-strain composite boom drives the deployment with predictable and nearly constant motive force.

During Phase II Roccor will address the key engineering development risks, mature the system design to a CDR level of development, and validate performance objectives through a series of ground-based qualification tests on engineering development units.  Overall, the anticipated outcome of the program is development and proto-flight validation of a SHROC™ Boom system for a wide range of future Heliophysics missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
*Deployable RF apertures for communication satellites (e.g., MILSTAR)
*CubeSat-class high-power solar arrays for commercial constellation missions
*Portable and man-packable deployable antennas for military ground troops

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
*Deployable magnetometers for Heliophysics research
*Deployable E-field sensors and Langmuir probes for Heliophysics research
*Deployable mono-pole and di-pole antennas for CubeSats
*High-gain mesh deployable antennas for constellation missions
*CubeSat-class high-power solar arrays for constellation missions

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Polymers
Actuators & Motors
Structures
Electromagnetic
Radiometric
Simulation & Modeling
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Characterization
Prototyping


PROPOSAL NUMBER:17-2 S1.08-8940
PHASE-I CONTRACT NUMBER:NNX17CA50P
SUBTOPIC TITLE: Surface & Sub-surface Measurement Systems
PROPOSAL TITLE: Compact CO2 Instrumentation for Small Aerial Platforms
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)
Anthony Gomez
algomez@swsciences.com
1570 Pacheco Street, Suite E-11
Santa Fe ,NM 87505 -3993
(505) 984-1322

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Over the past decade, the importance of understanding the sources and sinks of carbon dioxide and other
greenhouse gases has been recognized. A variety of research studies funded by NASA, DOE and NOAA to
measure the fluxes of CO2 from average conditions have been performed. In particular, flux measurements of CO2 in the boundary layer are critical toward understanding the carbon budget for this important greenhouse gas. The World Meteorological Organization has met its goal of 0.1 ppm CO2 accuracy for land based field sensors with gas chromatography and nondispersive infrared instruments. However, these instruments are poorly suited for small aerial platforms because of their high power requirements, large size and/or weight specifications. This proposal directly addresses NASA's need for high accuracy, small aerial platform, CO2 instrumentation for their Sierra and Dragon Eye UAVs, other unmanned aircraft such as launched and tethered balloons, and remote, unattended ground platforms where low power, compactness and self calibration are important. This instruments fits in with NASA's Technology Roadmap for satellite validation under the ASCENDS program and the OCO2 mission, as well as independent high resolution, nonintegrated CO2 profiles.

To address this instrumentation need, Southwest Sciences has  developed a compact (< 1 L), low power (< 2 watts), light weight (<1kg) diode laser based instrument to measure dry air corrected CO2 concentrations.  Phase I was successfully completed. We achieved the Phase III targets in Phase I with a drift accuracy of <1 ppm at >1 hr and short term precision of 0.2 ppm at 1 second under static conditions. Over a 300 torr pressure range, 12°C temperature range, and 1.6% water addition, the system  successfully measured within a standard deviationof 0.7, 0.8 and 0.4 ppm respectively of the actual concentration. The source of deviation was well characterized in Phase I and can be further reduced in Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A direct commercial application of this project is the sale of research and environmental monitoring instrumentation to academic researchers, government agencies for large research and monitoring programs, and commercial entities for regulatory compliance applications. Although this proposal initially targeted UAVs and can be extended to manned aircraft, it can be further adapted as a rack mount and even as a hand held ultra portable instrument. Broader commercial application areas for this sensor include gas leak sensing for pipeline and carbon sequestration sites, fire detectors for commercial and private aircraft, combustor feedback control sensors, and process control sensors for energy and chemical production industries.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High accuracy, dry air corrected CO2 instruments for UAVs and manned aircraft would bridge the gap between current land based and satellite platforms. NASA would have new tools for making high accuracy mixing ratio measurements where manned airborne observations are risky (i.e. North Slope of Alaska) or for manned flights to replace current commercial instruments that are not meeting NASA's requirements with respect to speed, precision, and/or accuracy.

TECHNOLOGY TAXONOMY MAPPING (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.)
Chemical/Environmental (see also Biological Health/Life Support)
Infrared
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Analytical Methods


PROPOSAL NUMBER:17-2 S1.09-9255
PHASE-I CONTRACT NUMBER:NNX17CG23P
SUBTOPIC TITLE: Cryogenic Systems for Sensors and Detectors
PROPOSAL TITLE: Cryomechanical Preconcentration System for Trace Gas Analysis
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aerodyne Research, Inc.
45 Manning Road
Billerica,MA 01821 -3976 (978) 663-9500
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Lerner
blerner@aerodyne.com
45 Manning Road
Billerica ,MA 01821 -3976
(978) 932-0220

Estimated Technology Readiness Level (TRL) at beginning and end of contract:
Begin: 5
End: 9

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Advanced cryogenic cooling systems are required to enable the high levels of sensitivity and precision needed for the measurements of trace atmospheric gases and isotopes that are used to evaluate anthropogenic impacts on the atmosphere and assess compliance with international regulations. This SBIR Phase II project will commercialize a robust cryogen-free pre-concentrator based on a Stirling cryocooler and a novel sample trap design. This system was successfully demonstrated in Phase I to have better thermal performance with lower maintenance than current pre-concentration systems used in NASA programs. The new sample traps are backward compatible with the existing cryogenic system to provide continued support for research groups using pre-concentrators with less advanced cooling. In Phase II, alternative sample traps will be developed to expand the utility of the pre-concentrator to a broader set of atmospheric trace gases, and to enhance the sensitivity of optical-based isotopic measurements. Selective and sensitive detection of greenhouse gases and ozone depleting substances will be further enhanced by coupling the pre-concentrator, via a gas chromatograph, to the high resolution time-of-flight mass spectrometer system evaluated in Phase I. In Phase II, improvements in the data acquisition and analysis software of this combined system will enable rapid automated analysis for field and laboratory measurements while providing new chemically-resolved information that was previously unavailable. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Atmospheric research and climate change programs sponsored by other federal agencies, such as the National Science Foundation (NSF), the National Oceanic and Atmospheric Administration (NOAA), the Environmental Protection Agency (EPA) and the Department of Energy (DOE), as well as a wide range of international collaborators, will benefit from the technology developed by this project.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA is the head US agency for monitoring ozone depleting substances, and plays a leading role in US Global Climate Change Research Program (USGCRP). The system developed in this SBIR project will provide a significant advancement in capability for measuring ozone depleting substances and greenhouse gases. It will be a desirable upgrade to the stations in the NASA-sponsored Advanced Atmospheric Gases Experiment (AGAGE) and will provide new technology for other NASA-sponsored atmospheric research programs.

TECHNOLOGY TAXONOMY MAPPING (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.)
Chemical/Environmental (see also Biological Health/Life Support)
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)


PROPOSAL NUMBER:17-2 S1.09-9725
PHASE-I CONTRACT NUMBER:NNX17CG34P
SUBTOPIC TITLE: Cryogenic Systems for Sensors and Detectors
PROPOSAL TITLE: Low Cost Cryocooler Control Electronics for Small Space Platforms
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, LLC
16 Great Hollow Road
Hanover,NH 03755 -3116 (603) 643-3800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bruce Pilvelait
brp@creare.com
16 Great Hollow Road
Hanover ,NH 03755 -3116
(603) 640-2316

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Many of NASA’s future space science missions will utilize small spacecraft, and many of these missions will require cryocoolers for cooling detectors, sensors, shields, and telescopes.  For Class C and D missions, the cryocooler technical requirements for performance, size, and mass, coupled with the programmatic requirements for minimal cost and development time, are extremely challenging.  Flight‑ready cryocoolers and associated control electronics developed for traditional satellites do not meet these technical, cost, or schedule requirements for future small space platforms.  Creare proposes to develop a low cost cryocooler control electronics package that leverages technologies and capabilities previously demonstrated on prior programs.  During Phase I, we developed a set of requirements, designed low cost electronics to meet these requirements, and verified production cost is low enough to compete with commercial off-the-shelf solutions.  During Phase II, we will continue to work closely with our partners to fabricate and qualify protoflight electronics with representative cryocoolers.  Successful completion of this program will enable advanced sensor systems for cost constrained space-borne science, surveillance, and reconnaissance missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed cryocooler control electronics are ideal for small, cost-constrained satellite missions. Military space applications include space based surveillance for Operationally Responsive Space missions and unmanned aerial vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The successful completion of this program will provide mission planners with high performance and low cost cryocooler control electronics that are compatible with miniature cryocoolers suitable for a variety of small platform missions. Primary emphasis will be on achieving low cost, small size, and high performance for cost constrained, small space platform missions. The primary NASA application will be for cooling detectors, instruments and sensors for planetary and earth science missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Cryogenic/Fluid Systems


PROPOSAL NUMBER:17-2 S1.10-8423
PHASE-I CONTRACT NUMBER:NNX17CG26P
SUBTOPIC TITLE: Atomic Interferometry
PROPOSAL TITLE: Cold Atom Laser Module (CALM)
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
AOSense, Inc.
415 Oakmead Pkwy
Sunnyvale,CA 94085 -4709 (408) 735-9500
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Josh Zirbel
jzirbel@aosense.com
415 Oakmead Pkwy
Sunnyvale ,CA 94085 -4709
(408) 735-9500

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Precision Navigation and Timing (PNT) is a critical resource for government and commercial aerospace. Given the high launch cost and shift toward smaller payloads, reducing the size, weight, and power (SWaP) of space-based navigation systems is a critical need. Atom-interferometric inertial sensors have demonstrated superior performance over conventional inertial devices owing to the intrinsic stability of atomic systems. Central to making cold atom sensors practical is their ability to reliably operate for extended periods without user intervention. Current laser diodes, which are at the heart of atomic sensors, suffer from power degradation and mode hops on timescales incompatible with long term deployment. Because these properties are inherent to the diodes, it is prudent to circumvent these problems with diagnostic protocols aimed at early detection and action. Diodes close to mode hopping can be temporarily taken offline to tune away the mode hop via current and temperature. Diodes with degraded power can be taken offline entirely in favor of a healthy diode. This approach will provide a robust, wavelength-agnostic technique to deliver reliable, long-lived laser sources at atom sensor-relevant wavelengths. AOSense proposes to develop a cold atom laser module (CALM) capable of supporting a broad range of atomic sensors. Development of the CALM laser module will result in a ruggedized and reliable laser source capable of autonomously driving an atom-based sensor within the space environment. Such an effort would enable space-based applications for atomic sensors such as IMUs, clocks, and magnetometers, opening up significant market opportunities in the defense and commercial sectors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Robust frequency stabilized lasers will also benefit the development of atomic sensors for non-NASA applications. Atom interferometric sensors can be configured as accelerometers, gyroscopes, gravity sensors, magnetometers or precision time keeping devices and therefore can be applied to a wide range of military platforms in addition to commercial applications. Precision navigation systems based on atom interferometric inertial sensors have the potential to provide precision positioning in environments where GPS signals are not available. Atomic gravimeters and gravity gradient sensors can be used for geophysical exploration and homeland security applications. Cold atom based frequency standards will ultimately replace the current generation of commercial cesium beam clocks that are widely used for timekeeping in a variety of systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Frequency stabilized lasers are at the heart of atomic sensors and their robust operation will be required for any future NASA mission that relies upon an atomic sensor. Atom interferometric sensors can be configured as accelerometers, gyroscopes, gravity sensors, magnetometers or precision time keeping devices. In each case they are best-in-class sensors and have the potential to enable new missions and applications of interest to NASA. Atom interferometers configured for gravity sensing can be used to map the earth's gravity gradient from orbit or to characterize the mass distribution of an asteroid for redirect missions. Atomic magnetometers offer the potential for improved remote sensing of magnetic fields and magnetic field gradients and could be used for precise characterization and monitoring of magnetic fields from orbit. Gyroscopes and accelerometers based on atom interferometry can provide orders of magnitude increases in inertial sensitivity which could lead to dramatic improvements in navigation and guidance systems. Ultra-precise atomic based gravity sensors and optical clocks could provide new methods for detection of gravity waves and tests of general relativity. Finally, robust frequency stabilized lasers are useful for non-atomic applications such as LiDAR and coherent laser communications.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Measuring/Sensing)
Inertial


PROPOSAL NUMBER:17-2 S1.11-8294
PHASE-I CONTRACT NUMBER:NNX17CG64P
SUBTOPIC TITLE: In Situ Instruments/Technologies for Ocean Worlds Life Detection
PROPOSAL TITLE: Compact UV Laser
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)
Bhabana Pati
pati@qpeak.com
135 South Road
Bedford ,MA 01730 -2307
(781) 275-9535

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

To advance the in-situ instrument technologies and components focused on the detection of evidence of life, Q-Peak proposes to develop a UV laser with very low Size-Weight-and-Power that can be used for laser-desorption-mass-spectroscopy (LDMS) to detect bio-signatures. A miniature LDMS, has been developed for the Mars-Organic-Molecule-Analyzer (MOMA) instrument at NASA-GSFC for the ExoMars mission, expected to launch in 2020. The MOMA instrument has a UV laser that is at least three times bigger in size compared to the Q-Peak laser. The MOMA instrument can be used in future missions to Titan and Europa to study the tholins and icy water. For mission like Europa-lander a radiation hardened instrument is needed and in this program Q-Peak will make the suitable laser. The laser will have a modular form factor to produce 1064-nm as the fundamental wavelength and then frequency-upconvert in two stages; second-harmonic-generation to produce 532 nm and fourth-harmonic-generation 266-nm using the appropriate nonlinear crystals.  When the laser is set to produce 532-nm, it is suitable to perform Raman-spectroscopy as a complementary analysis of organic molecules. When set to produce 1064-nm, it is suitable for laser-induced-breakdown-spectroscopy which is another technique to perform compositional analysis of organic/inorganic samples.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
An ultra-compact UV laser nominally operating at 262 nm can be used in advanced research and development and industrial manufacturing such as micro-material processing for the manufacturing of printed circuit boards and electronics. UV lasers are used in biotechnology and medical markets for sterilization and disinfection of devices. UV lasers are used in cosmetic dentistry mainly to facilitate chemical bonding and bleaching of organic enamels and other procedures. Atomic and molecular spectroscopy and chemical dynamics are additional experimental uses for UV lasers. With the removal of a nonlinear crystal, this laser can operate at a 532 nm which is suitable for treatment of glaucoma. Argon Laser Trabeculoplasty and Selective Laser Trabeculoplasty use green lasers for glaucoma treatment. They are used to open up the drainage angle of the eye, allowing easier flow of fluid and relieving pressure in the eye.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA applications are in the search of life in the extra-terrestrial by detecting organic/inorganic molecules by means of LDMS, LIBS, LIF, Raman spectroscopy. With slight variation when operated at high PRF such as 10-30 kHz the laser can be used for lidar, terrain mapping and autonomous rendezvous of satellite. When integrated into a mico mass spectrometer the instrument can be used for air monitoring and breath analysis for future human habitation in space.

TECHNOLOGY TAXONOMY MAPPING (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.)
Minerals
Lasers (Machining/Materials Processing)
Lasers (Measuring/Sensing)
Ultraviolet
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Characterization
Prototyping


PROPOSAL NUMBER:17-2 S1.11-8595
PHASE-I CONTRACT NUMBER:NNX17CP48P
SUBTOPIC TITLE: In Situ Instruments/Technologies for Ocean Worlds Life Detection
PROPOSAL TITLE: WOLFEChip: Wholly-Integrated Optofluidic Laser-Induced Fluorescence Electrophoresis Chip
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Leiden Measurement Technology
1230 Mountain View Alviso Road, Suite A
Sunnyvale,CA 94089 -9408 (650) 605-3046
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nathan Bramall
N.Bramall@LeidenTechnology.com
1230 Mountain View Alviso Road, Suite A
Sunnyvale ,CA 94089 -9408
(510) 301-8980

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

In this Small Business Innovative Research (SBIR) effort, Leiden Measurement Technology LLC (LMT) proposes to design and build the Wholly-integrated Optofluidic Laser-induced Fluorescence Electrophoresis Chip (WOLFEChip) System, a microchip capillary electrophoresis (MCE) system using a miniaturized optofluidic approach for packaging all critical optical elements necessary for laser-induced fluorescence (LIF) on-chip. WOLFEChip uses cutting-edge laser micromachining to fabricate fully-three-dimensional optical elements that focus excitation laser light into a MCE microchannel to excite fluorescence. The fluorescence emission is collected using custom-designed high-numerical aperture collection optics immune to misalignment of the chip up to 1-mm. This improves on current and past implementations of MCE-LIF by (1) greatly miniaturizing the optical elements which comprise a significant amount of space in MCE-LIF systems; (2) making the entire LIF optical system monolithic and immune to misalignment which greatly enhances the vibration-resistance of the entire system; (3) making the system immune to operator-to-operator variations caused by the periodic need to carefully align traditional MCE-LIF systems; and (4) greatly reducing measured stray light and thereby potentially increasing the signal-to-noise ratio (SNR) of the MCE-LIF system by employing right-angle excitation/emission optical geometries and through the use of high-quality fluorescence-free fused silica. LMT will deliver a complete MCE-LIF system featuring a refined WOLFEChip design created in Phase I.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
WOLFECHip technology allows MCE-LIF systems to be ruggedized and maintained by less-skilled personnel and so has many uses outside of NASA. Due to its sensitivity, specificity, portability (both in terms of mass and ruggedness), and flexibility it can be used in many different situations including (1) environmental research of terrestrial and marine waters (e.g., detecting important biomarkers or nutrient sources); (2) process control and monitoring of closed water systems (e.g., Naval shipboard water monitoring, water treatment centers); (3) pharmaceutical research; (4) monitoring and identification of organic pollution in water, soils, and sediments (e.g., pesticides, fuels, drugs); (5) the detection of biological and chemical weapons. Advantages of WOLFEChip over existing electrophoresis technologies are its portability (enabled by its size and its rugged optofluidic implementation of LIF), resolution (MCE-LIF is inherently higher-resolution than CE due to the injected plug size), and operator-to-operator invariance (other MCE-LIF systems require an operator to manually align optics into a MCE chip, leading to LIF efficiencies varying based on the skill of the operator; WOLFEChip uses integrated optics to avoid this). In Phase III, LMT will seek to establish commercial relationships with vendors of MCE-LIF systems for marketing commercial-implementations of WOLFEChip to environmental scientists, water-quality monitoring authorities, and the United States Navy.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
WOLFECHip is especially well-suited for detecting life on Ocean Worlds in the solar system (e.g., Europa, Titan, Enceladus) as well as other smaller bodies (e.g., asteroids, comets) and rocky planets (e.g., Mars). For the detection of life, an unambiguous, highly-sensitive, definitive approach is required and MCE-LIF is an ideal technique for detecting life by measuring the relative abundance and chirality of amino acids and other important biomarkers. Key benefits of MCE-LIF for space exploration include: (1) its levels of detection are orders-of-magnitude lower than more traditional high-TRL gas chromatography approaches; (2) the technique uses minute volumes of reagents; (3) the instrumentation inherently requires very little power and mass; and (4) MCE-LIF is highly-suitable for dealing with liquid samples. WOLFEChip will be a great stride towards further miniaturizing and ruggedizing MCE-LIF hardware for upcoming mission opportunities by fully integrating the critical LIF optics on-chip thereby reducing mass, size, and the need for mechanical stability/alignment of external optical systems to micro-scale features.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lenses
Biological (see also Biological Health/Life Support)
Biological Signature (i.e., Signs Of Life)
Chemical/Environmental (see also Biological Health/Life Support)
Optical/Photonic (see also Photonics)
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Analytical Methods
Prototyping


PROPOSAL NUMBER:17-2 S1.11-9800
PHASE-I CONTRACT NUMBER:NNX17CA21P
SUBTOPIC TITLE: In Situ Instruments/Technologies for Ocean Worlds Life Detection
PROPOSAL TITLE: Electro-Kinetic Ice Gun for Frozen Ice Plume Simulations
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Connecticut Analytical Corporation
696 Amity Road
Bethany,CT 06524 -3006 (203) 393-9666
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joseph Bango
jbango@ctanalytical.com
696 Amity Road
Bethany ,CT 06524 -3006
(203) 393-9666 Ext: 21

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This proposal evolved as a result of a conversation with a NASA scientist regarding plans for a mission to one of several icy moons in the solar system to seek signs of life based on observed water plume emissions. In preparation for such a mission, spacecraft will have to pass through clouds of ice particulates, which will pose challanges in organic species collection, and possible damage to instruments. Accordingly, there is a need for simulating the production of hyper velocity ice in the size range of 50nm through 2 microns. The NASA Ames Vertical Gun Range was designed to propell solid projectiles for studying the effects of meteorite impacts on celestial bodies and potential micro-meteoroid damage to spacecraft. “At the far end of the barrel, a gunpowder explosion is used to compress hydrogen gas to as much as 1 million times atmospheric pressure, firing a projectile pellet at speeds between 7,000 and 15,000 mph”. This approach is not suitable for ice particles, so we have developed a novel ice gun using electrosprays that can achieve a hyper velocity net result without damage to the sample grain.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications might include possible micro cleaning applications like particulate bombardment on silicon chips or other surfaces in vacuum. Of greater potential use, is a new application for ambient pathogen air sampling, ionization, sorting, and characterization to yield near real-time infectious disease analysis.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In order for NASA to probe plumes that produce ice particulates, a source for creating high speed particles is required to see whether a spacecraft can pass through and collect samples without denaturing the trace organics sought that may indicate the presence of life. Our system offers a means to create a bolt-on "ice-gun" source for any NASA facility, allowing studies on water fountain emissions, but for the simulation of comet tail media, organic molecule production from hyper-velocity impacts, and for re-entry simulation research.

TECHNOLOGY TAXONOMY MAPPING (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.)
Aerogels
Nanomaterials
Nonspecified
Organics/Biomaterials/Hybrids
Entry, Descent, & Landing (see also Astronautics)
Aerodynamics
Analytical Instruments (Solid, Liquid, Gas, Plasma, Energy; see also Sensors)
Analytical Methods
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)


PROPOSAL NUMBER:17-2 S2.01-9655
PHASE-I CONTRACT NUMBER:NNX17CP52P
SUBTOPIC TITLE: Proximity Glare Suppression for Astronomical Coronagraphy
PROPOSAL TITLE: Next-Generation Deformable Mirrors for Astronomical Coronagraphy by Utilizing PMN-PT Single Crystal Stack Actuators in integration with Driver ASIC
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microscale, Inc.
800 West Cummings Park, Suite 3350
Woburn,MA 01801 -6377 (781) 995-2245
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
xingtao wu
xwu@microscaleinc.com
800 West Cummings Park, Suite 3350
Woburn ,MA 01801 -6377
(339) 927-1996

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This SBIR Phase II project aims to develop innovative manufacturing methods for batch fabrication of single crystal PMN-PT stack actuator deformable mirrors (DM) at low cost of up to one order of magnitude reduction to those offered by the state-of-the-art manufacturing techniques. The methods, being applicable to produce high-performance deformable mirrors with a large variety of pixel densities and actuator counts, are also proposed to seamlessly integrate the DM manufacturing process with a novel large-scale driver ASIC, hence an enhancement of the proposed batch manufacturing process by reliably packaging DMs with high yield, zero failure pixel, and with high optical qualities, and on top of these offering the demanded high-resolution mirror surface control. Low payload, high performance, low cost, and low power, are the four keys that can lead a DM to successful implementation into NASA's high-performance systems. For lab testing, concept inspiration, and concept validation, the AO communities need high-performance but low-cost DMs to study wide variety of AO concepts on a tight budget and in a timely fashion; on the other hand, once an AO concept is approved, a space-based adaptive optics system will additionally demand low payload and low power dissipation for space-based deployment. The proposed DM manufacturing and ASIC integration  aims to develop DMs to meet the two staged needs through one joint DM-ASIC development program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include laser beam shaping, ophthalmology and other microscope applications. In particular, for the Department of Defense, if needed, the prototype adaptive optical systems based on the Phase II results can be applied to military seekers, FLIRs, optical communications, and other adaptive optics systems for military operations. For optical computing, the VLSI circuit could be combined with piston-only micromirror structure for a phase-only spatial light modulator. Commercial markets for these systems also include retinal imaging, supernormal human vision, and amateur telescopes. The research is also expected to lead to a family of compact, low-cost, high performance spatial light modulators for direct retinal display, head mount display, and large-screen projection display applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In general, future high-performance systems for: (1) correction of aberrations in large-aperture, space-deployed optical interferometers and telescopes, (2) high-resolution imaging and communication through atmospheric turbulence, (3) laser beam steering, and (4) optical path alignment, (5) propagation of directed laser energy through atmospheric turbulence, will require deformable mirror (DM) wavefront correctors with several hundred to millions of elements. More specifically, NASA missions and instruments that would benefit from the proposed DM manufacturing/packaging technology are WFIRST (near future), Visible Nulling Coronagraph (VNC), single aperture far-infrared observatory (SAFIR), Extrasolar Planetary Imaging Coronagraph (EPIC), and the Terrestrial Planet Finder (TPF). Other NASA projects that would benefit from the proposed TTP mirror technology include the Submillimeter Probe of the Evolutionary Cosmic Structure (SPECS), the Stellar Imager (SI) and the Earth Atmospheric Solar occultation Imager (EASI).

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Smart/Multifunctional Materials
Actuators & Motors
Microelectromechanical Systems (MEMS) and smaller
Adaptive Optics
Lasers (Communication)
Visible
Infrared
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)
Processing Methods


PROPOSAL NUMBER:17-2 S2.01-9865
PHASE-I CONTRACT NUMBER:NNX17CP76P
SUBTOPIC TITLE: Proximity Glare Suppression for Astronomical Coronagraphy
PROPOSAL TITLE: Technology Development for High-Actuator-Count MEMS DM 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)
Steven Cornelissen
sac@bostonmicromachines.com
30 Spinelli Place
Cambridge ,MA 02138 -1070
(617) 868-4178 Ext: 207

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Boston Micromachines Corporation proposes high-precision deformable mirror (DM) systems with one hundred actuators across the active aperture, corresponding to almost eight thousand actuators in the device’s circular aperture, using an innovative new approach for packaging and integration. The proposed work focuses on a technology gap that NASA has identified as critical for space-based exoplanet imaging: production techniques for small-stroke, high-reliability, high-precision deformable mirror systems. The main objective in this Phase II project is to substantially increase the state-of-the-art for the number of actuators in a compact MEMS DM system using microelectromechanical systems (MEMS) production processes and employing a multiple-layer approach to integrating routing line layers in the device. MEMS DMs will be bonded to custom manufactured printed circuit boards using conductive epoxy bonds and flip-chip alignment based on a new stencil printing process demonstrated in the Phase I project. The proposed work includes testing and evaluation of surface topography of DMs before and after bonding and assessment of actuator yield and reliability.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High-actuator-count deformable mirrors have a few commercial applications. The following applications apply to products produced by Boston Micromachines (BMC) that will benefit from increased actuator count and reduced cost.
Space surveillance: BMC has success developing arrays up to 4096 elements for astronomy which can be used for space-based systems. These programs are funded by Department of Defense administrations with classified agendas.
Optical communication: Lasercomm systems would benefit from this new architecture for long-range, secure communication. Also, fiber optic communications can take advantage of our devices in an optical switching capacity.
Microscopy: The capabilities of many non-adaptive optics-enabled microscopy modalities' devices have reached their limits. Increasing actuator count and reducing cost of fabrication will enable users to purchase higher-resolution equipment at a lower cost for use in detecting disease. Modalities affected include two-photon excitation fluorescence (TPEF), second- and/or third-harmonic generation (SHG/THG), and 4Pi microscopy, coherent anti-stokes Raman spectroscopy (CARS) and super-resolution localization microscopy techniques.
Pulse-Shaping: Laser science strives to create a better shaped pulse for applications such as laser marking and machining, and material ablation and characterization. The use of a higher-actuator count array for these purposes will enable new science and more refined techniques.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High-actuator-count deformable mirrors have a few astronomical NASA commercial applications. The following applications apply to all Boston Micromachines (BMC) mirrors that will benefit from new manufacturing processes developed for this program and from subsequent reduced cost.
Astronomy: Post applications in this category can be broken into two categories: space telescopes and ground-based telescopes. In the case of space telescopes, there are a number of missions/mission concepts that require the wavefront control provided by the proposed high actuator count deformable mirrors. These include the Large UV/Optical/Infrared Surveyor (LUVOIR) and Habitable Exoplanet Imaging Mission (HabEx) telescopes. For ground-based telescopes, BMC has already had success developing arrays up to 4096 actuators for the Gemini Planet Imager and multiple smaller devices for high contrast imaging testbeds at Nanjing University, Space Telescope Science Institute, and University of Nice. BMC can achieve similar results for larger arrays for other new and existing installations such as the planned Extremely Large Telescopes (Thirty Meter Telescope (TMT), European Extremely Large Telescope (E-ELT) and the Giant Magellan Telescope (GMT)).

TECHNOLOGY TAXONOMY MAPPING (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.)
Microelectromechanical Systems (MEMS) and smaller
Adaptive Optics
Mirrors
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)


PROPOSAL NUMBER:17-2 S2.01-9936
PHASE-I CONTRACT NUMBER:NNX17CP62P
SUBTOPIC TITLE: Proximity Glare Suppression for Astronomical Coronagraphy
PROPOSAL TITLE: Polymer Coating-Based Contaminant Control/Elimination for Exo-S Starshade Probe
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Photonic Cleaning Technologies, LLC
1895 Short Lane
Platteville,WI 53818 -8977 (608) 770-0565
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Hamilton
hamiltonj@photoniccleaning.com
1895 Short Lane
Platteville ,WI 53818 -8977
(608) 770-0565

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Our First Contact Polymer (FCP) is an easy-to-apply, residue-less, peelable strip coat that protects and cleans optics, detectors, and other sensitive surfaces, restoring them to a pristine condition. Using FCP is as simple as spraying or brushing it on a surface of interest, allowing it to dry for 15 minutes, and stripping off the rugged coating when desired. Multiple measurements, including at NASA’s Goddard Space Flight Center, show that FCP cleans better than any existing method, including the complicated, expensive, and hazardous CO2 snow, leaving no detectible residue. FCP is used to clean telescope optics at the Keck Observatory, GTC in the Canary Islands, Vandenberg Airforce Base, etc. The polymer was used by LIGO to clean the optics that enabled its breakthrough discovery of gravitational waves, and enables the THAAD missile interceptor by protecting and cleaning its optics. FCP was even used at the Smithsonian Institute to clean irreplaceable gems such as the Hope Diamond, demonstrating potential uses far beyond optics. Our technology is a crosscutting solution enabling the demanding cleanliness requirements of the Exo-S Starshade probe’s occulter, reducing the duration and cost of meeting Planetary Protection requirements without damaging sensitive components, and providing cleanroom-level cleanliness without the cleanroom, including for semiconductor manufacturing. Since our Red FCP exhibits anomalously high adhesion to certain metals and the amorphous metallic glass of Starshade petal edges, we developed in Phase I a variant with lower adhesion to metals. While the resulting adhesion was too low to be optimal, it demonstrated the adhesion tunability of our product. In Phase II, we produce 18 variants, identifying the lowest-cost one that provides optimal adhesion to protect, clean, and minimize the contribution of peeling to a mission’s alignment error budget. We also develop Standard Operation Procedures and training for application and removal.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Post-SBIR commercialization will focus on photonics markets and markets where surface sterility is of interest. These include medical & scientific research, pharmaceutical & food productions, or any manufacturing currently using clean rooms to maintain sterility. Surface radiation contamination removal would interest government & commercial operators within the nuclear/defense industries.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Our surface-specific stripcoatings will provide superior cleaning & protection from recontamination. In Phase I , we began developing a truly enabling, crosscutting technology that fills needs for multiple NASA missions, successfully developing the ability to prepare space-ready, contamination-free surfaces at unprecedented levels. Our strippable, surface-tunable, and residue-less polymer solutions can be a critical and key enabling technology required to meet mission objectives. For example, the LIGO experiment used our FCP to clean the optics that enabled its breakthrough gravitational-wave discoveries. As in LIGO, the contamination control requirements for the Starshade and the Large Interferometer Space Antenna (LISA) missions are so demanding that without the performance level of our technology, we believe those missions will not launch. LISA was recently selected by the European Space Agency (ESA) for its third large Cosmic Vision mission, while Starshades are seen as a key technology for the HabEx mission, currently under study. A starshade is also under consideration in support of the Wide-Field InfraRed Survey Telescope (WFIRST) and the Large UV/Optical/IR (LUVOIR) Surveyor. Potential future applications include creating/maintaining sterile & biological contamination-free surfaces enhancing NASA's Planetary Protection Mission, and nanotube doped, ESD controlled films for CCD and IRFPA sensor cleaning.

TECHNOLOGY TAXONOMY MAPPING (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.)
Coatings/Surface Treatments
Polymers
Adaptive Optics
Detectors (see also Sensors)
Lasers (Weapons)
Optical
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)


PROPOSAL NUMBER:17-2 S2.02-8520
PHASE-I CONTRACT NUMBER:NNX17CP71P
SUBTOPIC TITLE: Precision Deployable Optical Structures and Metrology
PROPOSAL TITLE: Redundant StarShade Truss Deployment Motor/Cable Assembly
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tendeg, LLC
686 South Taylor Avenue, Suite 108
Louisville,CO 80027 -3000 (303) 929-4466
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Stienmier
david.s@tendeg.com
686 South Taylor Avenue, Suite 108
Louisville ,CO 80027 -3000
(720) 273-7873

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The proposed innovations are as follows: 1) A fully redundant electrical and mechanical motor/cable deployment assembly 2) A redundant motor/cable deployment assembly that is integrated and deploys a perimeter truss for a starshade 3) A truss strut mechanism that allows petal and truss deployment and provides a stiff and repeatable support 4) A truss node light seal the suppressess all sun and starlight through a truss node with articulatinig truss elements and inner disk and petal interfaces. The significance and relevance of the proposed innovations is to meet the technical challenges of deploying a large scale perimeter truss (10-30m diameter) for a starshade. The STDT's "Exo-S Final Report" identified an open issue to "Mature perimeter truss technology readiness." This is part of a defined starshade technology gap S-5 that is titled "Demonstrate inner disk deployment with optical shield." In the NASA JPL starshade design the petals are placed into their precise position by the deploying truss and truss strut. The truss also deploys the spiral wrapped inner disk and at the end tensions the precision spokes. If the truss was not able to fully deploy or meet the on-orbit load (deployment and deployed) and positioning requirements then the mission would fail. Obviously the truss deployment mechanism needs to be a robust and reliable system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Large scale deployable perimeter trusses could also be used for large solar arrays for SEP applications or planetary surface operations that would need a robust architecture that can withstand high accelerations. In addition, the technology developed through this SBIR would apply to any cable driven deployment that would benefit from the reliability of a fully redundant electrical and mechanical system. Cable spoolers are used for deploying articulating booms, trusses, thermal blankets, solar arrays as well as deploying and controlling guys and stays.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Technology developed during this SBIR program will be directly applied to any NASA telescope program involved with exoplanet discovery and
characterization that needs an external occulter, or Starshade. NASA has identified a potential rendezvous mission with WFIRST/AFTA because it
is a large astrophysics telescope capable of supporting direct imaging with a starshade. Beyond starshades, the technology developed through this SBIR would apply to any cable driven deployment that would benefit from the reliability of a fully redundant electrical and mechanical system. Cable spoolers are used for deploying articulating booms, trusses, thermal blankets, solar arrays as well as deploying and controlling guys and stays.

TECHNOLOGY TAXONOMY MAPPING (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.)
Actuators & Motors
Deployment
Structures
Hardware-in-the-Loop Testing
Simulation & Modeling
Autonomous Control (see also Control & Monitoring)
Command & Control


PROPOSAL NUMBER:17-2 S2.03-9674
PHASE-I CONTRACT NUMBER:NNX17CM27P
SUBTOPIC TITLE: Advanced Optical Systems and Fabrication/Testing/Control Technologies for EUV/Optical and IR Telescope
PROPOSAL TITLE: Additive Manufactured Very Light Weight Diamond Turned Aspheric Mirror
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Dallas Optical Systems, Inc.
1790 Connie Lane
Rockwall,TX 75032 -6708 (972) 564-1156
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Casstevens
c0029156@netportusa.com
1790 Connie Lane
Rockwall ,TX 75032 -6708
(972) 564-1156

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The innovation proposed is a method for the fabrication of a very low cost, very light weight large aperture
Al10SiMg aluminum alloy mirror by the combination of three manufacturing processes. 1. Additively
manufactured mirror substrates as demonstrated in previous Phase 1 NASA SBIR S2.03-9125 with 0.2 mm
contour accuracy. 2. Precision robotic welding of hexagonal on-axis and hexagonal off-axis segments to produce a larger mirror. 3. Large capacity diamond turning can produce any desired mirror aspheric contour
to visible tolerances on the monolithic large mirror.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Defense applications requiring mirror optical components for satellites and aerospace vehicles. Non-military
applications such as weather satellite optical mirrors and commercial telescope optics. Commercial
applications requiring light weight stiff optical components such as semiconductor manufacturing equipment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Extremely light weight medium aperture off-axis three mirror anastigmat (TMA) mirror optical components, collimator and telescope optical instruments. Extremely lightweight large off-axis mirrors for unobscured optical collimators and telescopes. On-axis hexagonal segments and off-axis hexagonal aspheric optical mirrors can be assembled to enable very large telescopes.

TECHNOLOGY TAXONOMY MAPPING (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.)
Adaptive Optics
Mirrors
Telescope Arrays
Lasers (Guidance & Tracking)
Lasers (Ladar/Lidar)
Optical
Ranging/Tracking
Infrared
Long


PROPOSAL NUMBER:17-2 S2.03-9933
PHASE-I CONTRACT NUMBER:NNX17CM29P
SUBTOPIC TITLE: Advanced Optical Systems and Fabrication/Testing/Control Technologies for EUV/Optical and IR Telescope
PROPOSAL TITLE: 3D Printed Silicon Carbide Scalable to Meter-Class Segments for Far-Infrared Surveyor
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Goodman Technologies, LLC
9551 Giddings Avenue Northeast
Albuquerque,NM 87109 -6412 (505) 400-8169
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Goodman
bgoodman@goodmantechnologies.com
9551 Giddings Avenue Northeast
ALbuquerque ,NM 87109 -6412
(505) 400-8169

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Using technology spun out from Sandia National Laboratories, Goodman Technologies LLC with our Small Business and Minority Serving Institution partner (Team GT) has demonstrated the feasibility of 3D printed and additively manufactured SiC/SiC composite and Reaction Bonded SiC for low areal cost, ultra-lightweight mirrors and structures. Our technology development roadmap shows production of the first meter-class mirror segments in time for the 2020 Decadal Survey, and an excellent solution for multiple Priority 1, 2 and 3 Technology Gaps identified in the COR 2016 and 2017 PATRs. Our meter-class 3d/AM silicon carbide segments will meet or exceed all NASA requirements for the primary mirror of a FIR Surveyor such as the Origins Space Telescope (OST), and may also provide a solution for the LUVOIR Surveyor. During Phase II we achieved an areal density of 10 kg/square meter on our first attempt at a production rate of 1.44 square meter per day for a single small printer. A cost of $60K to 3D print/AM  large segments looks readily achievable, as does an optical surface that has nanometer-scale tolerances. Our encapsulated lattice construction provides a uniform CTE throughout the part for dimensional stability, incredible specific stiffness, and the added benefit of cryo-damping. Our process will also allow for direct embedding of electronics for active structures and segments, and the potential for actively cooling with helium for unprecedented low emissivity and thermal control. Finally, the particulate paste extrusion process may be very suitable for printing mirrors in the zero gravity of space. During Phase II, we propose to optimize, mature and scale 3D printed silicon carbide mirrors and telescope structures traceable to OST and LUVOIR Surveyors through the demonstration of Pathfinder Surrogate components for a meter-class primary mirror for the NASA Gondola for High Altitude Planetary Science (GHAPS) project.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA applications of low cost, lightweight, dimensionally stable mirrors and telescopes for lasercom systems, 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 NASA and national defense missions such as airborne, shipborne and land-based lasers as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed Goodman Technologies solution is directly relevant to the NASA Technology Taxonomy and the S2.03 Advanced Optical Systems and Fabrication/Testing/Control Technologies for EUV/Optical and IR Telescope topic, and the Optical Components and Systems for potential Infrared/FAR-IR Missions subtopic, and the Large Aperture FAR-IR Surveyor Mission (e.g., Origins Space Telescope, OST, mission concept). The ultimate goal of the proposed Phase II SBIR project is to demonstrate affordable manufacturing processes for 3D printing and additively manufacturing low areal cost, ultra-lightweight mirrors and structures for future FIR (OST) and LUVOIR Surveyor missions, and then sell these products to the Government and Systems Integrators in Phase III. We have already ascertained the interest of, and received a letters of support from 7 companies and a National Laboratory. The NASA Astrophysics Division Roadmap Enduring Quests ? Daring Visions builds on the 2010 Decadal Survey and includes near-term, formative (10-20 years notional Surveyor missions) and visionary (20+ years notional Mapper missions). The Far-Infrared Surveyor (Origins Space Telescope), LUVOIR Surveyor, and HabEx, along with other smaller optical systems will require 1015 m2 of mirrors in the next 30 years. At the NASA target price of $100K/m2 this represents a marketplace totaling over $101M.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Nanomaterials
Structures
Mirrors
Telescope Arrays
Ultraviolet
Infrared
Active Systems
In Situ Manufacturing
Processing Methods


PROPOSAL NUMBER:17-2 S2.04-8407
PHASE-I CONTRACT NUMBER:NNX17CG72P
SUBTOPIC TITLE: X-Ray Mirror Systems Technology, Coating Technology for X-Ray-UV-OIR, and Free-Form Optics
PROPOSAL TITLE: Freeform Optics for Optical Payloads with Reduced Size and Weight
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Voxtel, Inc.
15985 Northwest Schendel Avenue, Suite 200
Beaverton,OR 97006 -6703 (971) 223-5646
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Harmon
paulh@voxtel-inc.com
15985 NW Schendel Avenue, Suite 200
Beaverton ,OR 97006 -6703
(971) 223-5646

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

For the purposes of supporting planned and future NASA missions and addressing an unmet NASA need for high-quality visible through shortwave-infrared telescope phase-correction optics manufactured and delivered quickly and inexpensively, Voxtel proposes a Phase II effort to develop a new class of three-dimensional freeform optics and to demonstrate the optical precision and size reduction possible for NASA satellite optical systems. The Phase I optic and ink design will be executed to improve the focus of the NASA dual freeform mirrored optical system, reduce aberrations fundamental to the design, and correct measured manufacturing process variations. Both aperture-side and field-side freeform GRIN optics will be combined in nonrotationally symmetric forms and additional freeform mirror design variables will be explored—including variations in the spacing and angular tilt of freeform mirrors—and solutions will be developed that includes polychromatic performance. Material properties will be characterized in radiation conditions expected at near-earth orbit and low-earth orbit, and new or existing nanocomposites will be developed as needed to demonstrate highly reliable operation in space radiation and harsh environment applications. Voxtel’s Phase II effort will increase the technology-readiness level from 4 to 6 by delivering to NASA a flight-capable optic produced on production-ready processes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Commercial and defense applications include ophthalmic lenses, weapon-firing control optics, optical laser-sighting systems, binoculars, borescopes, interferometers, microscopes, telescopes, camera lenses (including cell-phone camera lenses, a growing segment), solar concentrator, window anti-reflection coatings, and lensed encapsulants for LEDs and white lighting.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
These freeform gradient optical corrector plates?and related gradient-index (GRIN) optics?will be useful for small-scale satellites (known as nanosats), for multi-freeform-mirror optic paths in satellites such as the Coastal Ocean Ecosystem Dynamics Imager (COEDI), for optical subsystems for the Wide-Field Infrared Survey Telescope (WFIRST) including the operational wide-field telescope, the integral field spectrograph, and the coronagraph, and for the James Webb Space Telescope (JWST) optical simulator (OSIM) wavefront sensors.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Nanomaterials
Polymers
Smart/Multifunctional Materials
Lenses
Telescope Arrays
Electromagnetic
Optical/Photonic (see also Photonics)
Display
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)


PROPOSAL NUMBER:17-2 S3.01-9023
PHASE-I CONTRACT NUMBER:NNX17CC39P
SUBTOPIC TITLE: Power Generation and Conversion
PROPOSAL TITLE: Game-Changing Photovoltaic Flexible Blanket Solar Array Technology with Spectrolab Flexsheets
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Deployable Space Systems, Inc.
460 Ward Drive, Suite F
Santa Barbara,CA 93111 -2356 (805) 722-8090
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Spence
Brian.Spence@DeployableSpaceSystems.com
460 Ward Drive, Suite F
Santa Barbara ,CA 93111 -2356
(805) 722-8090

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Deployable Space Systems, Inc. (DSS) in collaboration with Spectrolab, Inc. has developed a modular multi-junction photovoltaic flexible blanket technology that uses innovative Spectrolab flexsheet SPM's that enable/enhance the ability to provide ultra-low cost, low mass, modularity, and high voltage operability for high power arrays to support solar electric propulsion (SEP) Human Exploration and Space Science missions.  The proposed multi-junction flexible blanket assembly with the innovative Spectrolab flexsheet SPM technology, when coupled to an optimized structural platform (such as DSS's ROSA / IMBA solar array, and/or other optimized flexible blanket solar array structures) will produce revolutionary array-system-level performance in terms of high specific power, lightweight, rapid assembly and re-configurability, compact stowage volume, reliability, unparalleled modularity, adaptability, affordability, reliable high voltage operability, adaptability to all flexible solar arrays, and rapid commercial infusion.  The proposed flexible blanket technology accommodates all space photovoltaics (PV) including standard XTJ PV and emerging IMM PV technologies.  Once successfully validated through the proposed Phase 2 program, the innovative lightweight and modular multi-junction flexible blanket technology will provide incredible performance improvements over current state-of-the-art, and will be mission-enabling for future NASA and non-NASA applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA space applications are comprised of practically all missions that require affordable high-efficiency photovoltaic power production through deployment of an ultra-lightweight, ultra-compact stowage, and highly-modular solar array. Potential non-NASA commercial and DoD applications span a broad range of high voltage/power applications that demand ultra-affordability. The technology is suitable for non-NASA LEO, MEO & GEO missions. The technology is particularly suited for missions that require game-changing performance in terms of affordability, ultra-lightweight and compact stowage volume.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA space applications are comprised of practically all Exploration, Space Science, Earth Science, Planetary Surface, and other missions that require affordable high-efficiency photovoltaic power production through of an ultra-lightweight, ultra-compact stowage, and highly-modular solar array. The technology is particularly suited for advanced spacecraft that require high power / high voltage solar array arrays that require game-changing ultra-affordability. The technology is suitable for NASA LEO, MEO & GEO, and interplanetary missions. The technology is also well suited for applications requiring scalability/modularity, operability within high radiation environments, high voltage operation, and operation in LILT and HIHT environments.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Polymers
Deployment
Lifetime Testing
Conversion
Generation
Sources (Renewable, Nonrenewable)
Prototyping
Processing Methods


PROPOSAL NUMBER:17-2 S3.01-9061
PHASE-I CONTRACT NUMBER:NNX17CC59P
SUBTOPIC TITLE: Power Generation and Conversion
PROPOSAL TITLE: Radiation Tolerant >35% Efficient Phosphide-Based Multi-Junction Solar Cells with Epitaxial Lift-Off
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MicroLink Devices, Inc.
6457 Howard Street
Niles,IL 60714 -3301 (847) 588-3001
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Drew Cardwell
dcardwell@mldevices.com
6457 Howard St
Niles ,IL 60714 -3301
(360) 790-8679

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

As the world leader in volume production of large-area epitaxial lift-off (ELO) III-V inverted metamorphic multi-junction (IMM) solar cells, MicroLink proposes to develop phosphide-based ELO-IMM four-junction (4J) and five-junction (5J) solar cells that will enhance the performance and capabilities of solar photovoltaic arrays for a variety of future NASA missions. Relative to state-of-the-art incumbent (Al)GaInP/GaInAs/Ge wafer-based 3J space solar cells, the proposed 4J and 5J solar cells have superior radiation tolerance, higher beginning-of-life (BOL) and end-of-life (EOL) efficiencies (η), lower areal mass density, higher specific power, higher operating voltage, lower cost, and inherent flexibility.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Manufacturers of commercial satellites and unmanned aerial vehicles (UAVs) are interested in MicroLink's low mass and power dense ELO solar cell technology for the potential to reduce costs while improving the efficiency compared to commercially available Ge-based cells. Attractive military and civilian applications include the ability to recharge batteries in remote locations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed phosphide-based 4J and 5J solar cells are ideally suited for high efficiency multi-junction solar cell arrays for NASA applications requiring superior radiation tolerance, higher BOL and EOL efficiencies, lower areal mass density, higher specific power, or lower cost relative to incumbent Ge-based 3J space solar cells. Potential applications include solar electric propulsion programs and missions involving extreme radiation environments. Arrays based on the proposed solar cells will be suitable for NASA missions ranging from near-Earth to deep space. Lockheed Martin, Space Systems Loral, and Boeing have shown great interest in MicroLink's work and in future applications of low mass, flexible photovoltaic module technologies that can support NASA's SEP program as a replacement for the solar cells in existing spacecraft.

TECHNOLOGY TAXONOMY MAPPING (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.)
Manufacturing Methods
Materials (Insulator, Semiconductor, Substrate)
Conversion
Generation
Sources (Renewable, Nonrenewable)
Processing Methods


PROPOSAL NUMBER:17-2 S3.02-9166
PHASE-I CONTRACT NUMBER:NNX17CM54P
SUBTOPIC TITLE: Propulsion Systems for Robotic Science Missions
PROPOSAL TITLE: Hybrid Propulsion Technology for Robotic Science Missions
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Streamline Automation, LLC
3100 Fresh Way Southwest
Huntsville,AL 35805 -6720 (256) 713-1220
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Chew
William.Chew@StreamlineAutomation.biz
3100 Fresh Way Southwest
Huntsville ,AL 35805 -6720
(256) 713-1220

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

C3 Propulsion's novel Hybrid Propulsion System (HPS) will be applied to a NASA-selected Robotic Science Mission. Phase I demonstrated the Proof-of-Principle and Phase II will design, fabricate, and demonstrate a flight-like propulsion system for that specific application. The HPS is non-toxic, stable, and has energy management (throttleable or pulse-width modulated) capabilities. In Phase I, C3 Propulsion demonstrated that its hybrid fuel formulations can withstand storage at -78ºC, with minimal effect on its physical or ballistic properties, and is expected to be able to operate in the cold temperature of Mars and outer planet moons. Its simple design decreases risk, reduces size, reduces mass, and increases reliability. It has high volume and density specific impulses and is expected to increase performance and lower costs.

In Phase II, a specific robotic science mission will be identified to determine system issues, including thrust, total impulse, weight, and volume. The selected mission will affect the design and operation of the system and will lead to a notional HPS design.  A mini-thruster, Hybrid Screening Engine (HSE), will be designed, based on the notional system, to complete the development of a baseline fuel formulation.  This formulation will be thoroughly characterized for mechanical properties, including the thermal coefficient of expansion.  A full-scale heavyweight thruster will be designed and tested at the test stand of the Propulsion Research Center (University of Alabama in Huntsville), which is being upgraded by MDA.  A preliminary HPS will be designed to determine the volume, shape, and weight of the selected propulsion system for future programs.  A DoT Hazard Classification for the baseline fuel will be obtained, which is expected to be no more hazardous than 1.4C.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
C3 Propulsion's Hybrid Propulsion Technology can be used for any missile or satellite station keeping application when more than simple ballistic trajectories are desired. Such applications would be small tactical Army and Marine missiles such as TOW, Javelin, and Hellfire, Air Force and Navy air-to-air and air-to ground missiles such as AIM-9 Sidewinder and AGM-65 Maverick, and third stage booster ACS and Divert and Attitude Control Systems for MDA ballistic missile defense applications. Civilian missile manufacturers would be interested in the ACS for their boosters and even for the smaller boost applications. Satellite manufacturers would be interested in their position and station keeping abilities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
C3 Propulsion's Hybrid Propulsion Technology systems are applicable for any NASA propulsion needs other than space launch boosters. It is non-toxic, has the ability to pulse or throttle for complex maneuvering, perform ascent operations from planets, moons, and asteroids, perform ACS and station keeping operations, is applicable to both manned and robotic missions and can operate at cold temperatures. The thrust is scalable from a few to millions of Newtons. It has high density impulse like solid propulsion systems, has the versatility of liquid propulsion systems, and is safer and more environmentally friendly than either.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fuels/Propellants
Launch Engine/Booster
Maneuvering/Stationkeeping/Attitude Control Devices
Surface Propulsion
Relative Navigation (Interception, Docking, Formation Flying; see also Control & Monitoring; Planetary Navigation, Tracking, & Telemetry)
Models & Simulations (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 S3.02-9525
PHASE-I CONTRACT NUMBER:NNX17CC41P
SUBTOPIC TITLE: Propulsion Systems for Robotic Science Missions
PROPOSAL TITLE: Cathode for Electric Space Propulsion Utilizing Iodine as Propellant
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
e beam, Inc.
21070 Southwest 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 Southwest Tile Flat Road
Beaverton ,OR 97007 -8739
(503) 628-0703

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

A hollow reservoir cathode for use in ion and Hall thrusters which uses iodine as propellant. Reservoir cathodes have unique features not found in conventional impregnated cathodes. The critical barium reduction process occurs in the reservoir, not in the matrix, and this isolates that process from iodine poisoning. Also, the barium supply is 100 times greater than is available in conventional cathodes. This allows much higher rates of barium to flow to the cathode’s surface – enough to overcome iodine poisoning. Also, metals resistant to iodine attack can be used in the cathode matrix. We propose constructing large numbers of reservoir cathodes with various compositions and activities. We propose a systematic study of these cathodes in iodine to discover the factors which provide the successful performance. We also propose a miniature reservoir cathode for use in CubeSats, where iodine's compactness is most appealing. NASA is pursuing iodine EP because of its many advantages over xenon. These include low cost and high storage density.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Busek Co. is the main non-NASA producer of iodine thrusters. We have been in communication with it to supply cathodes if this project is successful. CubeSats are the largest non-NASA market. They are the mainstay of university and private space science projects.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA's primary interest is for iodine thrusters of less than 1 KW. It is also interested in powers over 10 KW. NASA has a critical need for reliable cathodes, both for discharge and neutralization. NanoSats are the largest market with iodine supply between 1 and 10 Kg and power at about 200 watts. A 12U CubeSat sponsored by NASA Glenn Research Center will employ an iodine ion thruster. NASA Glenn and the Marshall Space Flight Center are co-sponsoring the iSat (iodine satellite) project. It, too, needs reliable cathodes. 2,000 to 2,750 small satellites are planned for this project.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fuels/Propellants
Sources (Renewable, Nonrenewable)
Prototyping


PROPOSAL NUMBER:17-2 S3.02-9837
PHASE-I CONTRACT NUMBER:NNX17CC71P
SUBTOPIC TITLE: Propulsion Systems for Robotic Science Missions
PROPOSAL TITLE: Iodine Hollow Cathode
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Plasma Controls, LLC
1180 La Eda Lane
Fort Collins,CO 80526 -4415 (970) 581-2239
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Casey Farnell
casey.farnell@plasmacontrols.com
1180 La Eda Lane
Fort Collins ,CO 80526 -4415
(970) 581-2239

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Plasma Controls, LLC will develop an iodine-compatible hollow cathode for use in Hall-effect thrusters. Materials in current state-of-the-art electron emitters, and many of the materials used in mounting hardware, are not compatible in a high-temperature iodine environment. This includes cathodes that use inserts made from porous tungsten impregnated with ceramics containing barium oxide, which can be susceptible to rapid decomposition of the ceramic by iodine, and lanthanum hexaboride-based inserts, which are subject to rapid surface decomposition by iodine. The work function of both types of inserts increases in the presence of iodine, and the temperature of the cathode increases, which further exacerbates the decomposition processes. We will use a materials science based approach to evaluate the chemical interactions between iodine and a range of potential materials at elevated temperature. We will construct and experimentally test candidate cathodes in relevant iodine environments to identify robust, safe-to-handle, chemically-stable material systems. In Phase II work, we will (1) perform long duration wear tests to demonstrate adequately long lifetime capability and (2) integrate the cathodes into iodine storage, feed, and thruster systems through industry and government partnerships.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A fully iodine compatible hollow cathode and thruster system is of great interest to commercial spaceflight satellite and cube-sat missions as a size, weight, and power and economic and enabler of smaller propulsion systems. In addition, hollow cathode electron sources are commonly used as components of ion and plasma sources in ground-based, materials processing applications. This includes ion etching of surfaces, ion-assisted film deposition, ion implantation, and chemical vapor deposition; processes which can present similarly challenging chemical environments to that of iodine. Robust and long life hollow cathodes developed through this work are anticipated to be highly commercially attractive as they would reduce maintenance expenses and process downtime. However, their attractiveness grows exponentially if they could be used in applications that were previously off limits due to the presence of highly reactive gases and plasmas. Hollow cathode technologies are also advantageous as electron sources in high-current, electron-beam melting applications and in gas/liquid/solid material analysis equipment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA aims to mature and demonstrate iodine electric propulsion technologies. Of particular interest are iodine hollow cathodes with lifetimes greater than 10,000 hours. Hollow cathodes are used in electric propulsion devices, including Hall effect and ion thrusters, to sustain discharge plasmas and neutralize ion beams, and in plasma contacting devices to neutralize spacecraft charge. Ultra-long-life, high-power, and wide-operating-current-range cathodes are needed for the Science Mission Directorate?s ambitious deep space missions, and low-power, high-efficiency cathodes for secondary payload cube-sat missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Metallics
Spacecraft Main Engine


PROPOSAL NUMBER:17-2 S3.03-8373
PHASE-I CONTRACT NUMBER:NNX17CC76P
SUBTOPIC TITLE: Power Electronics and Management, and Energy Storage
PROPOSAL TITLE: GaN-Based High Power High Frequency Wide Range LLC Resonant Converter
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SET Group, LLC
142 Schoolhouse Road
Souderton,PA 18964 -0000 (844) 738-9933
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Raul Chinga Alvarado
ralvarado@setgroup.us
142 Schoolhouse Rd
Souderton ,PA 18964 -0000
(844) 738-9933

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

SET Group will design, build and qualify a Gallium Nitride (GaN) based High Power High Frequency Wide Range LLC Resonant Converter capable of handling high power and high frequency operation. The GaN LLC Converter will operate at 1 MHz with an input voltage of 95V - 160V and output of 600V - 2kV, capable of handling up to 5 kW. Current technology utilizes silicon-based solutions for power conversion and distribution. GaN can fundamentally perform well beyond current silicon based hardware. GaN has direct benefits such as higher power density, reduced footprint, increased power capacity, and improved power efficiency. Increasing frequency of operation results in smaller components but it also creates a challenge for thermal management and magnetic component design. SET Group will develop a novel thermal management system utilizing additive manufacturing which will consolidate the housing and cooling in a single part. Similarly, SET Group will design a novel transformer that will integrate the resonant inductor, transformer, and output voltage multiplier stage into a single unit. SET Group's goal of integration is to reduce the number of parts to decrease size of unit, mass and volume. This results in higher power density, lower manufacturing costs and higher reliability. SET Group will design the GaN-LLC Converter to be used for Solar Electric Propulsion (SEP), but the outcome of this work will serve as a platform for other power conversion products utilizing GaN technology to be developed. 

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Demand for broadband internet access in remote areas, airplanes and higher data capability (i.e. 4K TV, 360o video, etc), have pushed satellite manufacturers to provide more powerful RF transponders. These transponders require higher power, increasing satellite size and launching costs, which results in more expensive satellite services for end consumers. SET Group's proposed GaN-LLC can provide satellite manufacturers a competitive edge by increasing power capabilities while reducing size, weight, and cost. In recent years, GEO satellite service providers, such as DirecTV, have been requesting more powerful satellites to handle the wider bandwidth needed to keep up with the data demand (DirecTV now offers 4K video). To meet broadband internet demand, companies have turned to LEO satellites, which due to their closer proximity to Earth, have a lower delay of signal (latency) over a GEO satellite. This is important for broadband internet given it is a two-way communication. Oneweb, a satellite manufacturer startup, will provide developing countries affordable access to internet by deploying a large constellation of LEO satellites (750 satellites) by 2020. SpaceX has also announced their own 4000 LEO satellite constellation. These satellites are small, thus reducing launching costs. A GaN-based EPS and PPU fits the equivalent capabilities of a much larger satellite into a much smaller and cost-effective one.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The greatest advantage of the technology proposed by SET Group is its ability to be used across a wide range of applications. An immediate application of our technology is for NASA's Solar Electric Propulsion systems. The PPUs in their system convert the 300V solar array output to the 700V - 2000V input level of an electric thruster. The proposed Wide Range GaN LLC Power Converter is a great candidate for that mission. In addition, the proposed work will serve as a platform to demonstrate GaN-based power conversion technology as a viable and better alternative than the current Si-based power conversion products.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Active Systems
Conversion
Distribution/Management
Characterization
Models & Simulations (see also Testing & Evaluation)
Prototyping


PROPOSAL NUMBER:17-2 S3.03-9009
PHASE-I CONTRACT NUMBER:NNX17CC78P
SUBTOPIC TITLE: Power Electronics and Management, and Energy Storage
PROPOSAL TITLE: Lightweight High Energy Density Capacitors for NASA AMPS and PPUs
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sigma Technologies International, Inc.
10960 North Stallard Place
Tucson,AZ 85737 -9527 (520) 575-8013
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Angelo Yializis
ayializis@sigmalabs.com
10960 N Stallard Place
Tucson ,AZ 85737 -9527
(520) 575-8013

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

All NASA Power Processing Units (PPUs) including DC to DC and DC to AC converters and inverters require a DC-link capacitor, placed between the DC source (PV solar array or battery) and the switching power semiconductors.  NASA technical personnel has identified a failure mode in Multi-Layer Ceramic (MLC) DC-link capacitors currently used in PPUs that can cause them to short.   Polymer Multi- Layer (PML) capacitors that Sigma Technologies proposed as a solution, have self-healing properties and do not short.  The Phase I development demonstrated that the PML parts have superior capacitance stability with temperature and voltage bias. MLC capacitance drops by as much as -80% at -196oC  and -40% at +200oC ,  while PML capacitance variation is limited to -15% and  0% respectively.  Furthermore, PML capacitors have approximately 5X higher energy density and 10X higher specific energy. In the Phase II program plug compatible PML capacitors with multi-pin electrodes will be produced and evaluated with a voltage rating specifically designed for 120V PPUs.  Some PML parts will be produced with the same capacitance as that of MLCs and others with higher capacitance but equal or lower volume. Equal capacitance parts will dramatically reduce capacitor size and weight and will improve reliability.  Higher DC-link capacitance is always desirable in PPU circuits, because and it can further minimize ripple current, voltage fluctuations and transient suppression.  Use of higher capacitance PML parts, will improve the functionality and reliability of the overall PPU circuit, without a penalty in weight and volume.  PML capacitors will be supplied to NASA technical personnel during the development period for electrical and environmental evaluation. The potential business opportunity of expanding the PML capacitor market to that of high voltage and high capacitance MLCs, which are prone to micro-cracking, are costly and have inferior dielectric properties, will be explored.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Capacitors are used in most all electrical and electronic systems ranging from consumer electronics, to industrial electronics, medical instrumentation, transportation, communications and defense. DC-Link capacitors are needed to absorb ripple currents and transient voltage pulses created by switching devices such as IGBT, IGCT and MOSFETs used to convert lower DC voltage to higher DC and AC voltages. The proposed PML DC-link capacitors, have applications in inverter circuits used in renewable energy power generation systems, including photovoltaics and wind power generation, hybrid and electric vehicles and modular energy storage systems tied to the smart grid. PML capacitors are smaller, they have lower cost and higher performance, which will improve life and reliability of power converters. Hybrid and electric automotive drives will particularly benefit from the higher temperature and lower volume and weight of PML capacitors. Sigma Technology has partnered with several automotive OEMs and Tier-1 automotive suppliers and is in the process of supplying PML capacitor samples for evaluation. Unlike the surface mount PML parts developed for NASA these are larger capacitors, that carry 100s of Amps and will be used to replace metallized polypropylene capacitors which are larger that PML and have temperature limitations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Radioisotope power systems (RPS), Advanced Modular Power Systems (AMPS) and Solar Electric Propulsion (SEP) are programs that will directly benefit from this development. Hall thruster PPUs voltage requirements include a 120V input for a 300V direct drive. Also, roll-out photovoltaic arrays are tailored to 120V and 300V for SEP applications. These are voltage ratings that are ideally suited to PML capacitors. In addition to the higher voltage DC-link capacitors targeted by this program, lower voltage PML capacitor can replace tantalum (Ta) capacitors that are commonly used in many aerospace systems. When compared to Ta capacitors, the prismatic PML parts have a wider voltage range, higher frequency response, superior lower temperature performance and lower Equivalent Series Resistance (ESR), which often forces the use of multiple capacitors in parallel to reduce heat dissipation.

TECHNOLOGY TAXONOMY MAPPING (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.)
Conversion
Distribution/Management


PROPOSAL NUMBER:17-2 S3.04-8513
PHASE-I CONTRACT NUMBER:NNX17CP77P
SUBTOPIC TITLE: Guidance, Navigation and Control
PROPOSAL TITLE: AutoNav Mark 4: Autonomous Navigation Software
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
contact@bluesunenterprises.com
1942 Broadway Street, Suite 314
Boulder ,CO 80302 -5233
(720) 394-8897

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The growing number of missions in deep space, from Discovery class missions like Psyche and Lucy down to very small spacecraft like Lunar Flashlight, is driving the need for standardized, flexible, full-featured flight software for spacecraft guidance, navigation, and control (GNC). Autonomous GNC allows a spacecraft to perform most of its own navigation activities without the need for ground-based personnel and DSN time, reducing cost and required DSN contact time, saving money, and allowing specialized navigation personnel from different NASA centers to be easily shared among missions.

Autonomous GNC activities include:
  -spacecraft positioning
    absolute and relative (helio, planet, small-body)
    relative to small bodies, other spacecraft for rendezvous
  -orbit determination
  -target tracking of bodies, apertures, spacecraft, ground-based assets
  -trajectory derivation
  -low-thrust maneuvering for Solar Electric Propulsion (SEP)
  -ephemeris calculations

AutoNav from the Jet Propulsion Laboratory implements these functions, and components have flown on Deep Space 1 and Deep Impact. With an appropriate application of software development process to reengineer the code, a new AutoNav Mark 4 could be made available as a commercialized product meeting NASA Class B software standards, thereby enabling its easy inclusion on a wide variety of NASA and non-NASA missions.

AutoNav Mark 4 source code is to be designed and tested to be compatible with a variety of different CPUs (e.g. SPARC, PPC, Intel), real-time operating systems (VxWorks, RTEMS), and flight software cores like NASA Core Flight System. This approach allows AN4 to be deployed in the widest-possible set of environments:
  -within STRS-compatible space radios (Iris, UST)
  -in the flight software load of the spacecraft C&DH
  -in a dedicated stand-alone instrument like the Deep Space Positioning System

AutoNav Mark 4 provides highly capable autonomous GNC while saving missions money

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Since AutoNav Mark 4 works with any flight software core, it could be applied to non-NASA spacecraft: DoD, NOAA, and ESA missions are prime candidates. International release of software should be possible under ITAR controls. AutoNav Mark 4 could be directly applied to commercial launch vehicles in order to calculate ascent maneuvers, including for human access to space.

Installing AutoNav Mark 4 just on small commercial missions having a CubeSat form factor would allow these missions to proceed at reduced cost, removing much of the need for expensive navigator personnel time. This would free missions from having to implement these capabilities, leading to better reliability of navigation, simpler mission conops, more cross-mission synergy, and lower barriers of entry for less experience providers like universities and commercial providers.

Future commercial human spaceflight could utilize AutoNav Mark 4 for on-board spacecraft navigation and trajectory calculation. This would be most useful in the event of a communications failure, allowing the astronauts to autonomously calculate a return trajectory for re-entry and landing without any interactions with ground-based expertise. It would also allow a low earth orbiting mission to track down and rendezvous with other spacecraft or the International Space Station for servicing, cargo transfer, personnel transfer, and the like, without requiring contact with the ground or extensive ground interactions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
AutoNav Mark 4 is applicable to any space mission requiring any of the following:
-spacecraft positioning
absolute and relative (helio, planet, small-body)
relative to small bodies, other spacecraft for rendezvous
-orbit determination
-target tracking: bodies, apertures, spacecraft, ground-based assets
-trajectory calc
-maneuver calc
-low-thrust maneuvering for Solar Electric Propulsion (SEP)
-ephemeris calc

All mission perform many of the above activities, often using ground-based processes that are slow and expensive. Commercialized on-board autonomous navigation as provided by AutoNav Mark 4 can be targeted at the whole range of LEO, GEO, and interplanetary missions, large and small.

AutoNav Mark 4 for low-thrust missions (including Psyche and Next Mars Orbiter) would allow a dramatic reduction in navigation and trajectory calculation costs by moving the bulk of these activities onboard. Long missions like these would incur even larger savings using AN4 than more modest missions.

AutoNav Mark 4 is directly applicable to JPL's Deep Space Positioning System. By using a commercialized AutoNav, JPL would avoid most development costs, providing only new algorithms from its Navigation Section to plug into the AutoNav Mark 4 architecture.

Human spaceflight could use AutoNav Mark 4 for navigation and trajectory calculation in the event of communications failure, allowing safe reentry the atmosphere and landing without ground interaction.

TECHNOLOGY TAXONOMY MAPPING (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.)
Optical
Navigation & Guidance
Relative Navigation (Interception, Docking, Formation Flying; see also Control & Monitoring; Planetary Navigation, Tracking, & Telemetry)
Autonomous Control (see also Control & Monitoring)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Attitude Determination & Control
Sequencing & Scheduling
Image Processing


PROPOSAL NUMBER:17-2 S3.04-9428
PHASE-I CONTRACT NUMBER:NNX17CM20P
SUBTOPIC TITLE: Guidance, Navigation and Control
PROPOSAL TITLE: Versatile Attitude Control Actuators for Sub-Milliarcsecond Precision Pointing
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)
Nathaniel Demmons
nate@busek.com
11 Tech Circle
Natick ,MA 01760 -1023
(508) 655-5565

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

In cooperation with ROCCOR LLC, Busek seeks to develop thruster heads integrated with deployable booms. The high resolution, low quiescence and extreme throttling capabilities of Busek electrospray propulsion, combined with the customizable moment arms afforded by ROCCORs compact deployables will ensure the system is applicable to a wide variety of mission concepts.  A preliminary performance map was obtained for the BET-1mN thruster, demonstrating hundreds’ of µN’s of thrust from a single emitter.  Time of flight measurements indicated mixed mode operation (droplets/ions), indicating that updated thrust control algorithms may be necessary, as present implementations focus on droplet or ion dominated emission.  Thrust modulations were demonstrated via control of flow rate and beam voltage, demonstrating deep throttling and operation over a wide range of conditions.  Size, Weight, and Power (SWaP) for two integrated BET-1mN thruster systems were provided to the ROCCOR LLC and used to develop requirements for the boom.  A notional 2m deployable boom design was developed and static load modeling performed to identify deflection.  Under the Phase II effort, Busek shall update test setups to include in-situ mass flow measurement during direct thrust measurement in order to fully assess thruster performance.  Additional thruster characterization shall focus on completing parameterized thruster performance while also measuring thrust noise, stability, and capturing electrospray plume sweeps.  Updated thrust control algorithms will be implemented in hardware/firmware and commanded thrust control demonstrated as part of an integrated test with the BET-1mN thruster.  Deployable boom requirements will be updated and a prototype boom fabricated and tested.  Static load testing will be performed to validate Phase I modeling results.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA customers include, international partners (such as ESA), the DoD and commercial EO missions. The readily configurable nature of the proposed technology would enable customized applications to simultaneously meet customer needs in precision pointing and disturbance compensation; therefore, maximizing the commercial applicability of the technology. Furthermore, the ability to scale both thrust output and boom moment arm, by virtue of Busek and ROCCOR's respective scalable technologies, enables rapid customization of the system. Commercial EO applications may include optical communication pointing supporting high bandwidth up/downlinks or precision pointing in earth orbit for earth observation organizations. With strong links to the now TRL-7 electrospray system Busek demonstrated on the LISA Pathfinder mission; the time is now right for other organizations to embrace this technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology has numerous applications NASA missions improving both scientific and practical capabilities. Precision pointing applications include astronomical science objectives, such as exoplanet observations or other space-telescopes, laser communications and space situational awareness. In all cases, the greatly improved pointing over existing SoA (e.g reaction wheels) afforded by the proposed technology would both enhance pointing accuracy/stability and reduce the need for complex vibration and control accuracy mitigation strategies such as the use of active optics (e.g. fast steering mirrors). Laser communication benefits are particularly relevant with active NASA programs pursuing, for example, optical communication for Mars missions. Space situation awareness and identification of solar system objects would benefit from an ability to precisely track commanded attitude profiles while holding target positions <1 pixel. In this manner, long integration times can be facilitated permitting resolution of extremely dim (small) objects. The system developed here also applications to highly precise position control including formation flight missions and those requiring disturbance free flight. Disturbance reduction has been recently demonstrated in space by Busek's colloid thrusters, larger than those proposed here, on the NASA ST-7/ESA LISA Pathfinder mission.

TECHNOLOGY TAXONOMY MAPPING (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.)
Maneuvering/Stationkeeping/Attitude Control Devices
Navigation & Guidance


PROPOSAL NUMBER:17-2 S3.06-8949
PHASE-I CONTRACT NUMBER:NNX17CP34P
SUBTOPIC TITLE: Thermal Control Systems
PROPOSAL TITLE: A Two-Phase Pumped Loop Evaporator with Adaptive Flow Distribution for Large Area Cooling
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, LLC
16 Great Hollow Road
Hanover,NH 03755 -3116 (603) 643-3800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Weibo Chen
wbc@creare.com
16 Great Hollow Road
Hanover ,NH 03755 -3116
(603) 640-2425

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA’s future remote sensing science missions require advanced thermal management technologies to maintain multiple instruments at very stable temperatures and utilize waste heat to keep other critical subsystems above minimum operational temperatures. Two-phase pumped loops are an ideal solution for these applications. A critical need for these pumped loops is a microgravity-compatible evaporator having a large cooling area to maintain the temperatures of multiple electronics and instruments. The evaporator must be able to accommodate multiple heat loads with a wide range of heat flux densities and allow heat loads to be mounted on any available locations of its cooling surfaces to facilitate vehicle-level system integration. To this end, Creare proposes to develop a lightweight, compact evaporator with innovative internal design features to adaptively distribute liquid refrigerant to heated areas, preventing dryout in areas with high heat flux. This advanced flow distribution feature reduces liquid recirculation flow in the pumped loop and thus the system power input. The design features also provide strong internal structural support for the evaporator, reducing the size and mass of the evaporator cover plates. In Phase I, we proved the feasibility of the evaporator by developing a preliminary evaporator design, predicting its overall performance, and demonstrating its key performance features and fabrication processes by testing. In Phase II, we will optimize the evaporator design, fabricate a 0.5 m x 0.5 m evaporator, demonstrate its steady state and transient performance in a representative pumped loop, and deliver it to NASA JPL for further performance evaluation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The evaporator technology has applications in advanced two-phase thermal management systems for commercial and military satellites, aircraft, terrestrial cooling systems for electronics and laser systems, hybrid vehicle power electronics, and computer servers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed evaporator will enable reliable two-phase pumped loops for efficient and precision thermal control of critical instruments in remote sensing science satellites and exploration vehicles, including a future mission to Saturn's moon Enceladus and the Surface Water and Ocean Topography (SWOT) mission. The evaporator technology also has applications in future two-phase thermal management systems for rovers and habitats.

TECHNOLOGY TAXONOMY MAPPING (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.)
Active Systems


PROPOSAL NUMBER:17-2 S3.06-9615
PHASE-I CONTRACT NUMBER:NNX17CM46P
SUBTOPIC TITLE: Thermal Control Systems
PROPOSAL TITLE: 3D Manufacturing of Integrated Heat Exchangers
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Polaronyx, Inc.
2526 Qume Drive, Suites 17 and 18
San Jose,CA 95131 -1870 (408) 573-0930
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jian Liu
jianliu@polaronyx.com
2526 Qume Drive, Suites 17 and 18
San Jose ,CA 95131 -1870
(408) 573-0930

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This NASA SBIR Phase II proposal presents an unprecedented method to do additive manufacturing of high temperature materials for NTP with a femtosecond (fs) fiber laser. A proof of concept demonstration has been carried out at the end of Phase 1. It is the enabling technology for 3D manufacturing of high temperature materials. With our successful history in ultrafast laser AM and SM processing, this proposal has a great potential to succeed in phase II. A prototype will be developed and sample coupons will be delivered during Phase II time frame.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Successful development of the proposed AM technology will provide a vital tool to solve existing and potential issues as discussed in Section 1. This technology will be directly applied in the 3D printing area with combined market share of $10(s) of billions.
3D printing uses various technologies for building the products for all kinds of applications from foods, toys to rockets and cars. The global market for 3D Printing is projected to reach $2.99 billion by the year 2018, driven by the advent of newer technologies, approaches, and applications. Expanding use of the technology in manufacturing final products, declining cost of printers, and increasing use of 3D printing technology in newer areas bodes well for market growth. The 3D printing market is expected to grow at a CAGR of 25.76% between 2017 and 2023, to be worth $32.78 billion by 2023.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to NASA?s reactor core for NTP and heat exchangers for CubeSat, the proposed short pulse high power fiber laser AM & SM processing approach can also be used in other applications, such as rocket, aircraft, and satellite manufacturing. Esp. it will find great potential in refractory material manufacturing for NASA nuclear rockets and spacecrafts, along with low absorption materials (copper, glasses). PolarOnyx will develop a series of products to meet various requirements for NASA/military deployments.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Machines/Mechanical Subsystems
Lasers (Cutting & Welding)
Lasers (Machining/Materials Processing)
Fuels/Propellants
Spacecraft Main Engine
Nondestructive Evaluation (NDE; NDT)
Heat Exchange
Processing Methods


PROPOSAL NUMBER:17-2 S3.08-9948
PHASE-I CONTRACT NUMBER:NNX17CG67P
SUBTOPIC TITLE: Command, Data Handling, and Electronics
PROPOSAL TITLE: Rad-Hard Embedded Processing SIP
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Silicon Space Technology Corporation
1501 South MoPac Expressway, Suite 350
Austin,TX 78741 -6966 (512) 550-2954
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ross Bannatyne
rbannatyne@voragotech.com
1501 South MoPac Expressway, Suite 350
Austin ,TX 78741 -6966
(512) 550-2954

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

VORAGO Technologies has created a product design and MIL-PRF-38534 qualification plan for a radiation-hardened miniaturized System-In-Package (SIP) that comprises an ARM® Cortex®-M0 microcontroller (VORAGO VA10820), a 16-channel 14-bit analog-to-digital converter (Cobham RHD5950) and a 2Mbit FRAM (Cypress CYRS15B102).  All the design work and planning has been put in place to produce working packaged SIP devices and qualify them in phase II.

Each of the three rad-hard die will be mounted on substrate within a hermetic 68-pin ceramic package. Individual signals from each device are routed via the substrate within the chip, which also includes decoupling capacitors and pull-up resistors in the SIP. This optimizes the number of useful pins that are available to the system designer.

The SIP design optimizes the size, user simplicity and reliability of the solution. Using this SIP solution rather than three discretely packaged parts means that the area of the functionality can be reduced by approximately a factor of five and the number of pin interconnections on a PCB can be reduced by a factor of more than three.

In phase II, we propose to build 85 units of the device and qualify it. In addition, we will build evaluation boards and a software board support package so that the device can be easily evaluated and used for development work by NASA engineers. Our objective is to get as many units / evaluation boards onto NASA engineers desks as possible.

We have discussed this device with NASA engineers from GSFC, Ames, JPL, JSC and MSFC and have received very positive feedback that the SIP device would be useful to them and would help simplify and miniaturize their electronics designs. Comments from NASA engineers have been included in the Phase II Technical Proposal.

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
We can confidently claim that there will be a lot of interest in this device from commercial space companies. We know this to be true because VORAGO have experience in selling the VA10820 microcontroller since 2015. We have had regular feedback from many sources that the addition of an analog-to-digital convertor and non-volatile memory would be very attractive to reduce the PCB size and increase functionality. The SIP device addresses this feedback squarely.

There is a demand for a highly-integrated SIP like this in commercial space applications, particularly C & DH for interfacing to analog signals with digital interfaces and programmable control functionality. The benefit of this part over closest fit existing solutions is that there are no state-of-the-art (based on ARM Cortex) ?mid-range? embedded processors that are available in a small footprint with NVM and a precision analog-to-digital convertor.

Commercial space system developers that would have an interest in this SIP would include Ball Aerospace, Bigelow, Blue Canyon, Boeing, Busek, Tyvak, SSL, Millenium, Lockheed Martin, Moog Northrop Grumman, Planetary Resources, UTC, and Raytheon.

Other commercial non-NASA applications that could use the SIP would be in C & DH and payload applications in CubeSats and Smallsats.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In general, the SIP device will be a suitable solution for many NASA space-based observatories, fly-by spacecraft, orbiters, landers and robotic / sample return missions that require robust command and control capabilities. The SIP will be used in payload and C & DH functions and low speed telemetry systems. Typical applications of the SIP will be:

- Low power, small form factor interface for sensors and actuators
- Motor controller processor
- Power supply monitor and power sequencer
- Embedded control housekeeping processor
- Safety monitor / watchdog device
- Analog signal interface with digital serial communications output

An example application for programming the SIP to become a fixed-function device would be for VORAGO to program firmware into the device to operate as a power sequencing chip that can be used to bring up multiple power supply voltage rails in the required sequence and in conformance with the start-up timing requirements of the system. This would ensure that a system using multiple supply voltages booted up correctly. There is currently no radiation hardened power sequencer chip available that can provide power sequencing of this nature for up to sixteen independent voltage rails.

TECHNOLOGY TAXONOMY MAPPING (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.)
Sensor Nodes & Webs (see also Communications, Networking & Signal Transport)
Avionics (see also Control and Monitoring)
Navigation & Guidance
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Robotics (see also Control & Monitoring; Sensors)
Command & Control
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Data Acquisition (see also Sensors)
Data Processing


PROPOSAL NUMBER:17-2 S4.01-8340
PHASE-I CONTRACT NUMBER:NNX17CP65P
SUBTOPIC TITLE: Planetary Entry, Descent and Landing and Small Body Proximity Operation Technology
PROPOSAL TITLE: An Enhanced Modular Terminal Descent Sensor for Landing on Planetary Bodies
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Remote Sensing Solutions, Inc.
3179 Main Street, Unit 3, P.O. Box 1092
Barnstable,MA 02630 -1105 (508) 362-9400
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Carwell
carswell@remotesensingsolutions.com
3179 Main Street, Unit 3, P.O. Box 1092
Barnstable ,MA 02630 -1105
(508) 362-9400

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Remote Sensing Solutions (RSS) proposes the development of a modular, small, high performance terrain relative Terminal Descent Radar (TDR) for range and velocity sensing of planetary landing and vehicles engaging in proximity operations.  The innovation builds off of and improves upon the highly successful Curiosity / Mars Science Laboratory sky crane Terminal Descent Sensor.  Our improvements include significant improvements to the size, weight, and reproducibility of the design; a modular design; and improvement in the ability to detect and remove the effects of airborne debris. 

In this effort we propose to realize prototypes of our recurring, reproducible designs at Ka-band and W-band. We also propose to develop, implement, and validate through field demonstration new measurement algorithms that can mitigate issues of false velocity measurements due to moving dust and sand, particularly at low altitudes where thruster fire can cause movement of surface particles.  Such algorithms mitigate that concern for planetary bodies where dust or sand are a concern (i.e. the Moon, Mars, comets, asteroids, and even Europa), and, by extending measurements closer to the surface, save mission cost and complexity by decoupling the landing problem from errors in the inertial measurement unit.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The TDR developed by RSS would be broadly applicable to the commercial space sector as well as NASA. Beyond space applications, the sensors & algorithms that yield robust, independent range and velocity measurements have broad applicability to autonomous vehicles, including automonous underwater vehicles (AUVs) and unmanned aerial vehicles (UAVs). As evidenced from the letters included in this proposal, RSS has already begun working with several companies on the development and marketing of small, lightweight radars and sonars for UAVs and AUVs, respectively.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Every major landing mission since Surveyor has used radar as the key component for delivering range and velocity information. The JPL TDS proved highly successful but was not designed to be reproducible. Rebuilding TDS beyond Mars 2020 is likely cost prohibitive, as well as size prohibitive for smaller class missions. A reproducible, low-cost landing radar system would fill an immediate need for upcoming landing missions, including Discovery class through flagship concepts like a Europa lander, also including lunar landing, due to its ability to operate independent of sun illumination, lack of need for coherent surface features (required for an incoherent imaging system to measure horizontal velocity), and far superior performance compared to lidar in the presence of dust and other particulates. Such a sensor thus solves a key, critical long-term NASA need post-Mars 2020, enabling numerous classes of planned and future robotic and crewed missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Entry, Descent, & Landing (see also Astronautics)
Positioning (Attitude Determination, Location X-Y-Z)
Air Transportation & Safety
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)
Navigation & Guidance
Relative Navigation (Interception, Docking, Formation Flying; see also Control & Monitoring; Planetary Navigation, Tracking, & Telemetry)
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Space Transportation & Safety
Autonomous Control (see also Control & Monitoring)
Perception/Vision


PROPOSAL NUMBER:17-2 S4.03-8399
PHASE-I CONTRACT NUMBER:NNX17CP73P
SUBTOPIC TITLE: Spacecraft Technology for Sample Return Missions
PROPOSAL TITLE: Advanced Ignition System for Hybrid Rockets for Mars Sample Return, 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)
James Selin
jim.selin@ultramet.com
Ultramet
Pacoima ,CA 91331 -2210
(818) 899-0236 Ext: 117

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

To return a sample from the surface of Mars or any of the larger moons in the solar system will require a propulsion system with a comparatively large delta-V capability. Consequently, significant propellant mass will be required. While it is technically feasible to generate O2 and CO propellants by electrolysis of CO2 from the Martian atmosphere, it will only work on bodies where there is significant CO2 in the atmosphere, and the mass of the required infrastructure (electrolyzer, batteries, solar panels) is substantial. A recent study showed that a hybrid rocket with multi-start capability trades more favorably than either a CO2 electrolysis system or a bipropellant system where the propellants are generated on Earth. Using a high-performance hybrid propellant combination and being able to restart the hybrid rocket are the keys. In previous and ongoing work, Ultramet has demonstrated that electrically heated open-cell silicon carbide foam can be used as an igniter for both monopropellant and bipropellant rocket engines. Due to its low mass, excellent oxidation resistance, and favorable electrical characteristics, the foam can be heated to 1300°C in just seconds, which enables it to quickly ignite any propellant flowing through it. The Phase I project demonstrated that a foam heater could be turned on and off any number of times and that it was capable of heating oxygen and igniting paraffin. Applied to a portion of the oxidizer stream in a hybrid rocket engine, this will provide multi-start capability. In Phase II, Ultramet will team with Parabilis Space Technologies to design, fabricate, and test a hybrid rocket ignition system suitable for use with O2, NTO, or MON-25 on a Mars ascent vehicle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This technology can be used for igniting non-hypergolic bipropellants, ionic liquid monopropellants, and hydrazine in main and attitude control engines on commercial and military spacecraft, as well as main and reaction control engines on commercial and military boosters. Other aerospace applications include ignition systems and catalyst preheaters for aeropropulsion turbine engines and air heaters for hypersonic wind tunnels similar to the Aerodynamic and Propulsion Test Unit at Arnold Engineering Development Center (AEDC). Non-aerospace applications include ignition systems and catalyst heaters for turbine engines used for terrestrial power generation, and gas and water heaters where high efficiency is critical.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology will initially be targeted at hybrid rockets, and the near-term application will be hybrid rockets for a Mars sample return mission. More generally, foam-based heaters that are amenable to use at high temperatures in highly oxidizing environments can be used as igniters for virtually any non-hypergolic propellant combination. These include O2/CO, LOX/CH4, LOX/ethanol, and LOX/RP-1 among others. They can also be used to ignite hydrazine, as well as ionic liquid monopropellants such as LMP-103S and the E, Q, and A blends of AF-M315. This makes the technology applicable to engines of virtually any thrust class, from large booster engines to small attitude control engines. Specific missions of interest to NASA include ascent/descent engines for missions to Mars, the Moon, other planetary moons, and asteroids.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Coatings/Surface Treatments
Metallics
Exciters/Igniters
Fuels/Propellants
Launch Engine/Booster
Spacecraft Main Engine
Simulation & Modeling
Models & Simulations (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 S4.04-9333
PHASE-I CONTRACT NUMBER:NNX17CC40P
SUBTOPIC TITLE: Extreme Environments Technology
PROPOSAL TITLE: Large Area Diamond Tribological Surfaces with Negligible Wear in Extreme Environments
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Diamond Materials, Inc.
23 Brahms Court
East Stroudsburg,PA 18301 -8038 (570) 730-4108
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Oleg Voronov
oavoronov@aol.com
23 Brahms Court
East Stroudsburg ,PA 18301 -8038
(570) 730-4108

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

In Phase I we demonstrated a methodology for processing large area diamond-hardfaced composites for tribological surfaces and bearings. Sliding experiments showed low friction and wear of the superhard-faced composites at both low and high temperatures. The measured wear against sand and dust was so low that it could not be detected. In contrast, all other tested materials experienced rapid abrasive wear. Most importantly, a low-cost method to produce large area fabric reinforced diamond composites for tribological applications has been developed. The primary trust of Phase II will be to optimize the processing technology for producing tribological surfaces and bearings, and to evaluate their performance in extreme environments, such as that encountered in high temperature exploration of Venus. We will continue to collaborate with NASA and industrial partners to optimize and scale the new processing technology, and to fabricate prototype bearings for performance testing at NASA’s test facility. Hence NASA will acquire patented technology and qualified supplier of superhard-faced composite bearings to operate in extreme planetary environments.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Since the superhard-faced composites that we are developing and optimizing experience low wear in hot corrosive environments, and are relatively inexpensive to produce, they can be used in reciprocating engines, rotary engines, rock drill bits, high-speed machining, and many other applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to high performance bearings, potential applications include diamond substrates for radiation-resistant electronic equipment, silicon-based circuits and chips.

TECHNOLOGY TAXONOMY MAPPING (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.)
Structures
Tribology
Simulation & Modeling


PROPOSAL NUMBER:17-2 S5.02-8498
PHASE-I CONTRACT NUMBER:NNX17CG65P
SUBTOPIC TITLE: Earth Science Applied Research and Decision Support
PROPOSAL TITLE: An Interoperable Decision Support System for Flood Disaster Response Assistance
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Remote Sensing Solutions, Inc.
3179 Main Street, Unit 3, P.O. Box 1092
Barnstable,MA 02630 -1105 (508) 362-9400
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Guy Schumann
schumann@remotesensingsolutions.com
3179 Main Street, Unit 3, P.O. Box 1092
Barnstable ,MA 02630 -1105
(508) 362-9400

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

For flood monitoring and response, NASA and other agencies are increasingly stepping up to the challenge to harness its remote sensing and modeling resources during an event. As these capabilities are designed and then progressively improved, there is a coupled need for mechanisms to sustain them. There is to date no global decision support system for flood disasters that ingests all the data from existing systems and provides real-time critical information that can guide operational reactions on the ground. Because these capabilities evolve over time, any such interoperable system must incorporate changes and improvements thereof, it must be flexible, and itself robust and able to be maintained into the future. These challenges are addressed in this SBIR where Remote Sensing Solutions collaborates with existing efforts of the Dartmouth Flood Observatory to develop an interoperable one-stop-shop based on open geospatial data standards that unifies information relevant to flood disaster response. Four primary objectives have been defined to achieve this goal (product, i.e. data layer, design; system development; demonstration; commercialization plan). The technical approach to meet the objectives is streamlined into specific work packages, each one including a milestone target to ensure successful project completion.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
For commercialization, the team envisages ?paid access? to the DSS to ensure ongoing maintenance, upgrades and sustainability of the DSS. This would allow full free access to scientists, researchers, the development aid sector and government organizations as well as NGOs.
The team has identified the following two target customer groups to engage with: (i) Geospatial data and information management companies; Flood modeling vendor companies; (re-) insurance companies; mortgage lenders/banking industry; (ii) Emergency response organizations; humanitarian agencies; development aid organizations.
Note that the team has already engaged with most of the above identified end users/customers. See for instance attached Letter of Interest from a potential industry sector. Also, the team collaborates with the UN WFP, the World Bank and FEMA on a regular basis.
Potential users and customers include a large variety of actors operating in flood disaster response. The following list of selected development partners for Phase I and II provides an idea of the multitude of organizations that we expect to be using the proposed DSS: FEMA, USGS, NGA, StormCenter Communications Inc., Center for Space Research (CSR), JPL ARIA, World Bank, UN WFP, CEOS, Luxembourg Institute of Science and Technology (LIST)/ ESA, Louisiana Department of Transportation (LA DOT).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We plan to keep the proposed system flexible enough to accommodate data from future flood-related missions, such as the post-launch data products of the NASA/CNES SWOT mission, and the water level product planned for ICESat-2 (also ESA?s Sentinel 3). Also for pre-mission projects, in particular to the mission Science Definition Team (SDT) and Science Team (ST), such a DSS system proves very valuable since it provides a global viewing and analysis platform of many available geospatial data layers from major satellite missions as well as models.
The proposed DSS will be developed in close collaboration with relevant partners and stakeholders from all kinds of economic sectors. This will ensure maximum impact of a ?one-stop-shop? for flood disaster response that meets the top priority requirements of each community active in flood response, thereby greatly facilitating operations. Also for the NASA Applied Science Disasters Program, the DSS will be a very valuable resource for assisting disaster response.
This SBIR project will also help support continuation of the very successful GEO/CEOS Flood Pilot that ends officially in December 2017. In fact, the PI and many others on this team, including the NASA and non-NASA advisors have been active contributors to the Flood Pilot and would like to continue such activities, and such could be easily done under the auspices of this SBIR project.

TECHNOLOGY TAXONOMY MAPPING (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.)
Analytical Methods
Command & Control
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Display
Image Processing
Data Fusion
Data Modeling (see also Testing & Evaluation)
Data Processing
Knowledge Management


PROPOSAL NUMBER:17-2 S5.03-9687
PHASE-I CONTRACT NUMBER:NNX17CG35P
SUBTOPIC TITLE: Enabling NASA Science through Large-Scale Data Processing and Analysis
PROPOSAL TITLE: Open-Source Pipeline for Large-Scale Data Processing, Analysis and Collaboration
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, LLC
16 Great Hollow Road
Hanover,NH 03755 -3116 (603) 643-3800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jerry Bieszczad
jyb@creare.com
16 Great Hollow Road
Hanover ,NH 03755 -3116
(603) 640-2445

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

NASA's observational products generate petabytes of scientific data, which are highly underutilized due to computational requirements; disjoint data access protocols; and task-specific, non‑reusable code development. Our overall objective is to accelerate NASA science through development of an open-source, Python-based Pipeline for Observational Data Processing, Analysis, and Collaboration (PODPAC).  The PODPAC software framework will enable widespread exploitation of earth science data by enabling multi-scale and multi-windowed access, exploration, and integration of available earth science datasets to support both analysis and analytics; automatically accounting for geospatial data formats, projections, and resolutions; simplifying implementation and parallelization of geospatial data processing routines; unifying sharing of data and algorithms; and enabling seamless transition from local development to cloud processing. To achieve these objectives, we will work with NASA Science Team members involved with the SMAP (Soil Moisture Active Passive) and EOSDIS (Earth Observing System Data and Information System) programs and the wider scientific community to define technical specifications for the software, and plan a list of prioritized enhancements for each quarterly release cycle; further develop the core Python library based on user feedback and using agile development practices; develop integrations with cloud computing resources, specifically targeting Amazon Web Services; develop and demonstrate best-available remotely sensed soil moisture, high-resolution downscaled soil moisture, and flood/drought monitoring applications to promote infusion into NASA programs; and engage with scientific community through conferences, meetings, webcasts, and by providing support in order to promote adoption of the software.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
We envision primary non-NASA applications for high-resolution soil moisture prediction and data analytics in the areas of agriculture, forestry, disaster and humanitarian response, and recreation. In particular, the agriculture industry would benefit from detailed knowledge of near surface and root zone soil moisture conditions by enabling improved irrigation and fertilization efficiencies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We are initially targeting the SMAP program for PODPAC transition by supporting, publishing, and exploiting their observational soil moisture data products, while also developing value-added products. Creare has teamed with the NASA Science Team Leader for the SMAP satellite mission, and will use PODPAC to derive global high-resolution data products from the SMAP radiometer data to support applications in hydrology, agriculture, and humanitarian response. We will also target other NASA earth science observational programs, such as AIRS, AMSR-E, AMSR2, GMI, MODIS, and VIIRS for further deployment and transition of PODPAC. PODPAC will also be made available as open-source software for access by any NASA scientists performing geospatial data analysis.

TECHNOLOGY TAXONOMY MAPPING (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.)
Development Environments
Programming Languages
Software Tools (Analysis, Design)
Image Analysis
Image Processing
Computer System Architectures


PROPOSAL NUMBER:17-2 Z1.02-8904
PHASE-I CONTRACT NUMBER:NNX17CC73P
SUBTOPIC TITLE: Surface Energy Storage
PROPOSAL TITLE: Highly Efficient, Durable Regenerative Solid Oxide Stack
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)
Saurabh Vilekar
svilekar@precision-combustion.com
410 Sackett Point Road
North Haven ,CT 06473 -3106
(203) 287-3700 Ext: 263

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Precision Combustion, Inc. (PCI) proposes to develop and advance a highly efficient regenerative solid oxide stack design. Novel structural elements allow reforming of regolith off-gases (e.g., methane and high hydrocarbons) within a solid oxide stack as well as efficient H2O/CO2 electrolysis, overcoming shortcomings of traditional approaches. The resulting design offers the potential for light-weight and simple design with high efficiency and durability. This effort would be valuable to NASA as it would significantly reduce the known spacecraft technical risks and increase mission capability/durability/efficiency while at the same time increasing the TRL of regenerative solid oxide systems for ISRU application. The technology concept of our highly-efficient regenerative Solid Oxide Stack was demonstrated in Phase I and will be advanced in Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Targeted non-NASA applications include energy storage as a solution to the renewable energy intermittency problem and individual innovation spinoffs to specific SOFC and SOEC stack designs. This technology offers the potential for substantial improvement to stack efficiency, thermal stress and life.

Continued public focus on energy efficiency and air quality will lead to continued interest in new power generation solutions, hydrogen generation and energy storage. Applications also include potential use in hydrogen generation electrolysis systems for vehicle refueling and power to gas applications. Vehicle refueling is a promising application as fuel cell material handling vehicles and fuel cell automobiles are entering initial markets. Power to gas is a new application for our technology in use with energy storage where this can be used to create synthetic natural gas. Other targeted non-NASA applications include military uses which will benefit from portable fuel & energy production within a single technology. We will also explore application for off-line systems for residential use for energy storage and power generation. The variable fuel capability of this system, including hydrogen, methane, and other hydrocarbons makes this technology commercially attractive to multiple domestic and international markets.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary target application is for an advanced regenerative solid oxide fuel cell/electrolyzer that enables a balanced C-H-O cycle supporting multiple mission critical purposes within a sustainable Martian ISRU system. The technology offers a step advance in oxygen generation and energy storage through CO2/water electrolysis as part of the air revitalization system, with added function for building up supplies of oxygen and fuel.

Specific applications include Martian bases, rovers, and hydrogen docking stations. Synergies in our proposed system are expected to result in increased efficiencies, improved utilization, reduced thermal and other stresses and improved seals for improved reliability and life, and higher power densities supporting greater capability and/or reduced launch mass/cost while simultaneously reducing requirements for supplemental material re-supply. The regenerative stack can provide power for bases as well as the next generation of rover and hydrogen docking stations for missions which can provide a pathway for robotic vehicles to travel while operating on fuel cell power. This comprehensive approach is expected to benefit from multiple thermal and resource synergies resulting in potentially game-changing system applicability to multiple mission applications.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fuels/Propellants
Conversion
Generation
Storage


PROPOSAL NUMBER:17-2 Z1.02-9685
PHASE-I CONTRACT NUMBER:NNX17CC64P
SUBTOPIC TITLE: Surface Energy Storage
PROPOSAL TITLE: Bifunctional Membrane for High Energy, Long Shelf Life Li-S Batteries
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Navitas Advanced Solutions Group, LLC
4880 Venture Drive Suite 100
Ann Arbor,MI 48108 -9559 (734) 205-1434
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Hong Wang
hwang@navitassys.com
4880 Venture Drive Suite 100
Ann Arbor ,MI 48108 -9559
(734) 205-1450

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The adoption of high energy lithium sulfur batteries hinges on significant improvements in charge/recharge cycle life.  Cycle life is limited by migration of dissolved polysulfide species which creates an electrochemical short circuit.  In this NASA SBIR, Navitas Systems proposes to develop an atomically precise and bifunctional membrane separator for lithium sulfur batteries that impedes polysulfide transport.  Bifunctionality will combine pore structure engineered for high capacity and selectivity to polysulfides with metal-like electronic conductivity to support electrochemical regeneration.  Phase I results showed that the proposed separator significantly improves the energy density and cycle life of lithium sulfur batteries. The Phase I proof of concept effort focused on validating the membrane materials property advantages in lab prototype cells.  Phase II will scale up production of separator using high volume roll-to-roll (R2R) coating.  Phase II will demonstrate separator robustness to automated high-speed cell assembly operations and to variation in the porous polymer substrate.  Membrane performance, cycle life, and abuse tolerance advantages will be validated in commercially relevant prototype pouch cells with at least 2Ah capacity.  Phase II technical objectives are to reduce coating thickness to <5 µm, continuously coat at least 20m of separator, demonstrate a 400 Wh/kg lithium sulfur battery cell with 200% improvement in cycle life, and show immunity to thermal runaway under NASA mission-relevant abuse testing protocols..

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
If successful, the proposed technology is expected to improve LSB cycle life by >2X which will help enable adoption of batteries that double the specific energy of commercial lithium ion batteries. Initial target markets include consumer electronics, drones, and soldier portable power, with the ultimate target of meeting performance, life and cost goals for Electric Vehicle batteries.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High energy lithium sulfur batteries can safely provide 500+ Wh/kg and potentially reduce the mass of energy storage systems by up to 50%. Through improving cycle life, the proposed separator advance will address the key limitation for space applications. With improved cycle life, lithium sulfur batteries will meet multi-use or cross platform space energy storage applications. Successfully deployed safe lithium-sulfur batteries would result in significant mass and volume savings and operational flexibility. Potential NASA applications include EVA space suits and tools, human example, lunar and martian landers, construction equipment, rovers, science platforms and surface solar arrays.

TECHNOLOGY TAXONOMY MAPPING (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.)
Nanomaterials
Storage


PROPOSAL NUMBER:17-2 Z1.03-9659
PHASE-I CONTRACT NUMBER:80NSSC17P1229
SUBTOPIC TITLE: Surface Power Generation
PROPOSAL TITLE: Linear Acoustic Nuclear Conversion Engine (LANCE)
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nirvana Energy Systems, Inc.
3130 Alpine Road, Suite 288 Box 6
Portola Valley,CA 94028 -7541 (216) 898-9990
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Geoffrey Bruder
geoff.bruder@nirvana-es.com
8150 Dow Cir, Suite 100
Strongsville ,OH 44136 -1764
(216) 898-9990

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Nirvana Energy Systems (NES) has pioneered and is commercializing an innovative ThermoAcoustic Power Stick (TAPS), partially based on technology developed by Xerox PARC (Palo Alto Research Center) and NASA. NES has demonstrated and is building a 1 kW TAPS for use in remote power applications where reliability for 15+ years is of paramount importance. Moreover, NES is developing the Thermoacoustic Radioisotope Generator (TRG), a 300 W Radioisotope Power System (RPS), under the Small Business Innovative Research (SBIR) program for NASA based on TAPS technology. The novel TAPS technology has no hot moving parts and incorporates well proven, reliable linear motors and alternators in an engine based on the Stirling cycle. NES has designed, optimized, built and tested all sub-systems for reliability, ease of manufacturing and cost reduction over currently available Stirling engines. The TRG is a 300 W tunable power thermoacoustic device which is insensitive to radioisotope heat degradation, capable of 20+ years continuous operation, is inexpensive to manufacture using well established methods, and yields greater than 25% thermal to electrical efficiency all while being designed for a convertor specific power greater than 30 W/kg and anticipated system specific power near 10 W/kg. The 1 kW remote power device served as the foundation for the Linear Acoustic Nuclear Conversion Engine (LANCE), which will satisfy all of the Z1.03 solicitation requirements, as a robust and redundant 2.5 kW tunable power supply, representing the ultimate in remote power devices and the next step in reliable dynamic power conversion for space.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Nirvana Energy Systems is currently working to commercialize the NASA technology through an exclusive patent license granted for the Alpha-STREAM technology that the TAPS technology is partially based on. The NES TAPS technology could be easily adapted to home use where high efficiencies are possible and the unit would function as a micro-Combined Heating and Power system. In an installation such as this the TAPS unit could be natural gas fed, where to achieve overall high system efficiencies the unit would utilize excess heat to provide heated water for potable needs or for hydroponic heating. Excess electrical energy production would be sent to the grid. Similar to applications for home power generation, other applications include commercial businesses, military uses (vehicles and domesticated areas), and the transportation industry. In particular, these industries desire higher electrical outputs and efficiencies but with long-term reliability and cost of ownership being of critical importance as well. The TAPS architecture would be able to provide all of these as it is a "set and forget" power generation system capable of tunable output powers at high efficiencies. Moreover, the reverse cycle of the TAPS system could be used for cooling in many cases, including as a refrigerant free domestic cooling system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary goal of LANCE is to develop a thermal-to-electrical power conversion system that produces 2.5 kW of net electrical output, has >25% efficiency, and durability for a lifetime of greater than 10 years. Due to the significant manufacturing and assemble cost reductions afforded by the TAPS architecture over traditional free piston Stirling systems the TAPS solution could be used as a direct replacement over traditional thermoelectric or other Stirling based systems in future space missions. Future NASA missions would benefit greatly from the cost-reductions afforded by the TAPS system as well as its modularity and relative ease of assembly. Furthermore, the TAPS technology enables architectures that are difficult, or impossible with other systems. Specifically, TAPS can easily be utilized for a combined power and cooling duplex, and some preliminary designs have been created. Such systems would enable a sustained presence in extreme planetary environments such as the surface of Venus.

TECHNOLOGY TAXONOMY MAPPING (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.)
Conversion
Generation


PROPOSAL NUMBER:17-2 Z2.01-9331
PHASE-I CONTRACT NUMBER:NNX17CM49P
SUBTOPIC TITLE: Thermal Management
PROPOSAL TITLE: Variable Gas-Conductance Radiator: Lightweight, High Turndown Spacecraft Radiator
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Quest Thermal Group
6452 Fig Street Unit A
Arvada,CO 80004 -1060 (303) 395-3100
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Dye
scott.dye@questthermal.com
6452 Fig St., Unit A
Arvada ,CO 80004 -1060
(303) 395-3100 Ext: 102

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Spacecraft thermal control is a critical element to maintaining spacecraft, manned, unmanned, robotic or instrument, at proper temperatures for humans, instruments and electronics to function properly. NASA Science Mission Directorate and STMD have need for advanced thermal control systems for future spacecraft and exploration vehicles.  Variable Gas Radiator™ technology, using variable gas conductance in an IMLI insulation to control, in a Phase I prototype achieved a turndown ratio of 36:1, was successfully proven feasible and TRL3 achieved. Quest believes VGR technology could provide high turndown ratios at any given temperature, in a lightweight radiator.  This new technology and product has many applications within NASA and the commercial spacecraft/satellite market.

Phase II work will continue development of VGR technology, including enclosure redesign, more flight-like pressure control hardware, extensive characterization, and  early flight-qual testing.  During Phase II, Quest will mature the technology to TRL 5 and have prototypes for NASA and Prime Contractor evaluation.

Phase II development of the Variable Gas Radiator (VGR) program begins studying advanced spacecraft heat rejection requirements for NASA and commercial spacecraft and missions, continues with study and review of the Phase I results. VGR enclosure and hardware development will be a focus. VCR design will be iterated, and prototypes tested for radiant heat flow, with improvement expected in overall radiator performance and turndown capability.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Quest Thermal?s Variable Gas Radiator technology was proven feasible in a Phase I program, and could be further developed, tested and matured in a Phase II program to reach TRL 5. It might then be flight proven in a NASA Phase III test program or ISS experiment, reaching TRL 7. As the technology matures, Quest would reach out to satellite thermal engineers and thermal component (radiator) manufacturers to begin discussions on VGR.

During the Phase II program, Quest will conduct market research on the spacecraft radiator/thermal control market using both internal staff and an external business development consultant. This market study is part of a Technology Assessment we will conduct, and should lead to customer responses to VGR, and direct leads at major spacecraft Prime Contractors.

Major satellite manufacturers include Boeing Defense, Space and Security, SSL (Space Systems/Loral), Lockheed Martin, Orbital ATK, Ball Aerospace, Thales Alenia Space and Airbus Defense and Space. There are also spacecraft component specialty manufacturers that supply thermal control components such as radiators and heat pipes, and these include Orbital ATK, Lockheed Martin/Vought System and Sierra Nevada Corp.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Variable Gas Radiator? technology is a novel highly variable spacecraft radiator being developed for NASA to provide needed new technology for spacecraft thermal control for advanced spacecraft and missions demanding variable radiated heat control. A VGR prototype provided a turndown ratio 36:1, current spacecraft radiators offer a 4:1 turndown ratio, and VGR with further development should achieve at least 40:1 turndown capability.

NASA in the SBIR 2017 solicitation sought unique solutions for thermal control technologies that facilitate a low mass highly reliable thermal control system for exploration vehicles and for science missions. Future spacecraft will require more sophisticated thermal control systems that operate in severe environments ranging from full sun to deep space and dissipate a wide range of heat loads. Potential NASA applications for this new technology include NASA Resource Prospector, CATALYST landers, cubesats, as well as comm sats.

Variable heat radiators are an important enabling technology needed for NASA?s future exploration missions. For example, it is listed as needed for NASA Design Reference Missions (e.g., DRM8 and 9) which are crewed missions to Mars. VGR technology, if proved successful, could be infused into future NASA spacecraft, including manned spacecraft, robotic exploration vehicles, Earth observing satellites, science and interplanetary spacecraft.

TECHNOLOGY TAXONOMY MAPPING (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.)
Smart/Multifunctional Materials
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)
Active Systems
Heat Exchange
Passive Systems


PROPOSAL NUMBER:17-2 Z2.01-9765
PHASE-I CONTRACT NUMBER:NNX17CJ28P
SUBTOPIC TITLE: Thermal Management
PROPOSAL TITLE: Passive Set-Point Thermal Control Skin for Spacecraft
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Physical Sciences, Inc.
20 New England Business Center
Andover,MA 01810 -1077 (978) 689-0003
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Woolf
dwoolf@psicorp.com
20 New England Business Center
Andover ,MA 01810 -1077
(978) 738-8132

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Current manned and unmanned spacecraft require sophisticated thermal control technologies to keep systems at temperatures within their proper operating range. Future manned and unmanned missions to the moon, mars, and other destinations will require new technologies to maintain spacecraft temperature near a set-point while under variable heat loads and thermal environments under increasingly stringent size, weight and power constraints. Passive components, such as coatings with variable emissivity, can greatly extend and expand NASA mission capabilities. Physical Sciences Inc. will develop a passive thermal control skin (TCS) with a constant emissivity from 8 C to 30 C and an infrared turndown ratio of greater than 8 between 8 C and -10 C. The TCS will control both the infrared emissivity as a function of thermal load while maintaining a low solar absorptivity at all radiator temperatures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The passive set-point thermal control skin (TCS) has potential applications on commercial satellites. Satellites orbiting the earth, when in direct sunlight, have some of their surfaces receiving solar radiation, while the other surfaces only see deep space. As the satellite warms and heat is distributed throughout the satellite, more of the TCS enters its "emissive" state, improving the self-cooling ability of the satellite. PSI?s TCS would maximize the passive cooling ability of these satellites, freeing up power for other satellite functionality.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed passive skin can significantly reduce the SWaP of spacecraft thermal control systems. For manned missions, the set-point can be near room temperature to reduce the work required by active thermal management components, removing the need for dual-loop thermal control systems. For unmanned missions, the passive skin can be designed such that the temperature set-point is at either the high or low end of the operating range of the craft electronics, depending on the various requirements, heat loads and thermal environments of the mission.

Our innovation directly addresses the need within NASA Technology Roadmap Area 14; specifically 14.2.3.7 (Variable Emissivity Radiator), which has been called out as a need for NASA?s planned, crewed Asteroid Redirect Mission (ARM), and more generally, NASA?s preparation to send a crewed spacecraft to Mars.

TECHNOLOGY TAXONOMY MAPPING (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.)
Passive Systems


PROPOSAL NUMBER:17-2 Z3.01-8823
PHASE-I CONTRACT NUMBER:NNX17CM31P
SUBTOPIC TITLE: In-Situ Sensing of Additive Manufacturing Processes for Safety-Critical Aerospace Applications
PROPOSAL TITLE: In-Line Inspection of Additive Manufactured Parts Using Laser Ultrasonics
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Intelligent Optical Systems, Inc.
2520 West 237th Street
Torrance,CA 90505 -5217 (424) 263-6300
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Marvin Klein
marvink@intopsys.com
2520 West 237th Street
Torrance ,CA 90505 -5217
(424) 263-6361

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

At present there are no reliable, cost-effective process control techniques to minimize defect production and for qualification of finished parts fabricated by additive manufacturing (AM). In our Phase I project we have demonstrated the feasibility of filling this gap by applying laser ultrasonic testing (LUT) for nondestructive evaluation of each AM deposited layer in real time as it is formed. This in-line inspection qualifies the part layer-by-layer, directs defect removal during the manufacturing process, and ensures qualified finished parts that require no further testing. In this proposed Phase II project we will team with a manufacturer of powder bed fusion AM machines to develop a three-step layer-by-layer inspection and validation system, consisting of: (1) optical profilometry for defect detection, (2) laser ablation to remove the defect indications and (3) LUT to validate the removal of the defects. The IOS technology development will include advanced signal processing and optimized beam parameters for optimized signal-to-noise, as well as integration of the controls with the AM machine controls. A preliminary and a full-scale prototype LUT system will be developed and tested on the manufacturer’s AM machine. At the beginning of the project we will be at TRL 4; at the end of the project we will be at TRL 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Additive manufacturing is valuable for producing parts that are difficult or expensive to produce by machining or forging. Aside from space, industries that are adopting additive manufacturing include military and commercial aviation, automotive, medical/dental, and consumer products. Aircraft engine suppliers have been investing heavily in capacity for AM parts manufacturing. Key high-value components such as injection nozzles are found multiple times in a turbine engine. The use of AM will reduce engine weight and cost. Components designed with complex cooling channels that were expensive or even impossible to make can now be produced by AM. For NASA and non-NASA use, the introduction of in-line, real-time laser ultrasonic testing to characterize 3D-printed parts supports Executive Order 13329, "Encouraging Innovation in Manufacturing."

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Additive manufacturing is finding broad applications by NASA and its contractors for the fabrication of high-value, safety-critical components. AM of components for rocket engines and spacecraft thrusters is particularly advanced. Within NASA, technology development and demonstration efforts for AM of metals are being conducted primarily at Marshall Space Flight Center (MSFC), Langley Research Center (LaRC), and Glenn Research Center (GRC). As an example, MSFC is pursuing AM of critical engine components for future heavy-lift space launch systems. GRC is collaborating with Aerojet Rocketdyne to develop a liquid-oxygen/gaseous hydrogen rocket injector assembly built by additive manufacturing.
The inspection technology described in this proposal is aligned with the NASA Space Technology Roadmaps, and addresses needs described in the recent NASA memorandum "Nondestructive Evaluation of Additive Manufacturing."
NASA's commercial space partners are actively involved in projects to incorporate AM components into their launch and spacecraft systems. For example, the SuperDraco engines for the SpaceX Dragon V2 manned spacecraft have 3D-printed combustion chambers that enable the engines to produce 100 times the thrust than the Draco engines in current unmanned versions of the Dragon.
Eventual applications of AM will extend to production of replacement or repaired components in space.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Measuring/Sensing)
Interferometric (see also Analysis)
Optical/Photonic (see also Photonics)
Nondestructive Evaluation (NDE; NDT)
Process Monitoring & Control
Quality/Reliability


PROPOSAL NUMBER:17-2 Z3.02-8909
PHASE-I CONTRACT NUMBER:NNX17CP68P
SUBTOPIC TITLE: Advanced Metallic Materials and Processes Innovation
PROPOSAL TITLE: Thermoplastic Forming of Bulk Metallic Glasses for Precision Robotics Components
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Supercool Metals, LLC
5 Science Park, 2nd Floor
New Haven,CT 06511 -1301 (203) 747-1989
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Evgenia Pekarskaya
evgenia@supercoolmetals.com
5 Science Park, 2nd Floor
New Haven ,CT 06511 -1301
(646) 244-0247

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Demand for novel manufacturing methods for space systems brings unique properties of bulk metallic glasses (BMG) into the spotlight. In addition to superior mechanical properties associated with enhanced reliability, BMG technology can offer new manufacturing processes that result in components with higher precision and complexity, eliminating machining and minimizing final assembly. In this project, we propose to utilize the unique thermoplastic forming (TPF) ability of BMGs to net shape high precision robotic gears. Within Phase I, we have proven feasibility of this technology. The technical objectives for Phase II is to further advance the technology to a level that allows NASA to test and use BMG gears in NASA missions. This requires high precision, repeatability, robustness, and consistency of fabricated parts. In addition, a technical focus will be on expanding the versatility of TPF-based fabrication process in terms of the range of geometries and sizes of flexsplines and the range of BMG alloys that can be used with TPF processes. Identifying the suite of BMG alloys that can be used for TPF-based molding would provide NASA with an option to select the best property combinations in terms of specific strength, ductility, wear, friction, and costs. An additional technical objective is to develop strategies to reduce friction and wear through surface finish of the molded flexsplines and fabrication of surface composites in a one processing step. The outcome of the project will be manufacturing capabilities for precision robotic components and ready-to-test flexspline gear parts with complex thin walled geometries, improved properties and dimensions suitable for Europa Lander and Kennedy Space Center and other NASA’s locations. Beyond space applications, the use of versatile thermoplastic forming processes for precision gears has a strong potential to bring cost savings for a wide range of industries that use robotic mechanisms.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Combining the properties of best structural metals with the processability of thermoplastics brings unique opportunities to robotics, aerospace, defense, automotive and biomedical industries. Specific applications that we are addressing in this NASA Phase II project include precision robotics components that outside space can be used for industrial and consumer applications. Miniaturization of robotics equipment is an important trend in medical and defense applications and thermoplastic forming of BMGs is uniquely suited for this.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Development of novel manufacturing processes for structures with superior mechanical properties has long been identified as one of the critical needs for NASA. In this project, we focus on forming precise robotics components with thin walled structures and high dimensional accuracy using bulk metallic glasses (BMGs). BMG robotics components are highly attractive for use at low temperature and harsh environments, such as Europa mission, due to improved mechanical properties and ability to operate unlubricated. Such BMG gears can also be used in robotics arms at Kennedy Space center, Goddard Space Flight Center and other NASA's locations. Beyond robotics, BMG technology is also attractive for small satellites and pressure vessels and other structural space applications.

TECHNOLOGY TAXONOMY MAPPING (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.)
Metallics
Structures
Robotics (see also Control & Monitoring; Sensors)
Prototyping
Processing Methods


PROPOSAL NUMBER:17-2 Z4.01-8593
PHASE-I CONTRACT NUMBER:NNX17CL41P
SUBTOPIC TITLE: In-Space Structural Assembly and Construction
PROPOSAL TITLE: Reversible Adhesion Concept for In-Space Assembly
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ATSP Innovations
60 Hazelwood Drive
Champaign,IL 61820 -7460 (217) 778-4400
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jacob Meyer
jacob.l.meyer@atspinnovations.com
60 Hazelwood Drive
Champaign ,IL 61820 -7460
(217) 778-4400

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

ATSP Innovations will develop a reversible adhesion concept for use in reconfigurable space frame construction. This reversible adhesion concept is based on application of aromatic thermosetting copolyester (ATSP) to selected adhesive contact points. By virtue of a class of reversible solid-state chemical reactions (called interchain transesterification reactions - ITR) intrinsic to the polymer, ATSP was shown to bond and debond with itself for >50 cycles during the Phase I with high mechanical strength allowing load values >6 the requirement of the solicitation in an very small contact area.

In Phase II of this project we will apply this reversible adhesive concept to assembly and reconfiguration of truss structures composed of tubular beams and we will do electrical, thermal and mechanical characterizations of  the reversibly joined tube segments. Based on the reversible adhesion concept developed and demonstrated in Phase I, a self-aligning attachment mechanism for tubular beams and hub joints with integrated heating is proposed. Designed attachment mechanisms and developed processes will be applied to assembly and reconfiguration of truss unit cell. Polymeric reversible adhesive will be subjected to outgassing and radiation experiments (to determine applicability to space environment) in simulation of low earth orbit with additional bond/debond cycles following radiation exposure implemented via a toolkit developed in Phase I. The high mechanical strength provides design flexibility for space in the joints for electrical contacts, thereby allowing multifunctionality of the space structures; with full scale dimension of the real truss structure, the joint would be able to reach a bond strength of 56,760N (113 times the required 500N).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Industry wide reversible adhesive: Thermally stable, high strength reversible adhesives are potentially usable in the construction, automotive, electronics, and the wider aerospace industry. Additionally, reconfigurable microfluidic devices and reconfigurable medical devices are other potential concepts derivative from this work.

Structural material: ATSP has a high glass temperature (170C to 310C for different chemical compositions) and an excellent profile of mechanical properties from cryogenic to high temperatures; thus ATSP bulk material or ATSP composites are excellent materials for broad temperature structure applications.

Tribological applications: ATSP-based coatings used here as reversible adhesives (with thickness of ~ 10s of microns) and bulk ATSP also have excellent tribological performance under extreme working conditions, including high temperature, cryogenic temperature, high contact pressure, high chamber pressure, starved lubrication, abrasive wear, etc. ATSP-based coating showed: zero wear at temperatures from -160C to 260C with dry sliding, extremely low wear coefficient (4.15x10-8 mm3/Nm) under starved lubrication condition, stable coefficient of friction (COF) and low wear rate under sand abrasive condition, and extreme low COF for oil and gas drilling application. The broad temperature use profile also suggests potential use as bearings in space applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Reconfigurable space frames will enable future NASA facilities in remote locations in our solar system where a servicing or new/replacement mission may be infeasible or cost-prohibitive to have its mission profile adapted for new applications. Future space missions are envisioned towards both sustainment of long-term on-mission space stations (e.g. ISS) and construction of on-site habitable structures beyond low-Earth orbit (e.g. Human Exploration of Mars), which requires innovative concepts for reconfigurable and reusable designs in response to changing mission needs. Specifically, NASAs Solar Electric Propulsion (SEP) project is sought to develop electrically propelled spacecraft having on-board multiple solar arrays (e.g. MegaFlex and Mega-ROSA concept designs). Likewise, Orbital Replacement Units (ORUs) are utilized to repair/replace malfunctioning segments of on-mission space systems (e.g. ISS) at present and will be soon be employed to build on-site space structures.

Use of a high strength, highly stable thermally driven polymeric reversible adhesive will enable minimization of mass, volume, electrical and labor inputs to assemble and reconfigure truss and other structures. Multifunctional design will accommodate capacity for electrical transmission within reconfigurable space frame structures - thereby simplifying and reducing required distinct components for adapting structures to changing mission profiles.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Joining (Adhesion, Welding)
Polymers
Smart/Multifunctional Materials
Fasteners/Decouplers
Structures
In Situ Manufacturing
Processing Methods


PROPOSAL NUMBER:17-2 Z4.01-9457
PHASE-I CONTRACT NUMBER:NNX17CL54P
SUBTOPIC TITLE: In-Space Structural Assembly and Construction
PROPOSAL TITLE: Multifunctional Self-Aligning Reversible Joint Using Space-Qualifiable Structural Fasteners
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
510 Earl Boulevard
Miamisburg,OH 45342 -6411 (937) 320-1877
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Hermiller
hermillerjm@crgrp.com
510 Earl Blvd.
Miamisburg ,OH 45342 -6411
(937) 320-1877 Ext: 1129

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Cornerstone Research Group, Inc. (CRG) proposes to develop a multifunctional reversible attachment method to facilitate modular in-space construction. CRG will demonstrate a mechanically robust, easily reversible, self-aligning fastener system with provisions for installation of electrical power connections. The proposed approach is highly versatile and can be extended to include other types of system support connections such as data transfer, fluid flow, or thermal load transfer. This state-of-the-art fastening system leverages CRG’s space-qualifiable thermoset shape memory polymer (SMP) fasteners providing NASA with a scalable, modular joining capability that can be used with autonomous assembly systems. In Phase I representative SMP fastening devices successfully demonstrated >50 simulated use cycles including: assembly, reaction of design loads, and disassembly. Leveraging CRG’s prior development work on shape memory polymer fastener systems, the proposed R&D herein will provide NASA with a multifunctional, reversible structural attachment system with technology readiness level (TRL) of 5 at the conclusion of the Phase II effort. In follow-on development CRG’s joining technology will be integrated with automated assembly robotic systems in support of critical mission demonstrations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Industrial fasteners: Blind fasteners and removal anchors, Anti-tamper or security enclosures. Commercial spacecraft: Satellite Assembly and Solar Array Assembly. Defense aerospace: Surveillance satellites, Manned space-craft and habitat assembly, and UAV assembly and payload attachment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Space Technology Game Changing Development Program, In-space Robotic Manufacturing and Assembly (IRMA), CIRAS, Archinaut, and Dragonfly Programs.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fasteners/Decouplers
Machines/Mechanical Subsystems
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Tools/EVA Tools
Models & Simulations (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 Z5.01-9019
PHASE-I CONTRACT NUMBER:NNX17CA29P
SUBTOPIC TITLE: Payload Technologies for Free-Flying Robots
PROPOSAL TITLE: Modules and Software for Free-Flying Robots
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
(888) 547-4100

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Energid Technologies will develop an articulated arm for modular attachment to the Astrobee platform. The arm design includes new actuators with wiring and structural support that will robustly operate with the Astrobee platform. Arms may be attached singly, in pairs, or in multiple pairs for bracing and manipulation. Grippers will use an innovative design that allows tool-free customization to new tasks. To control the arms, grippers, and base, Energid's Actin software toolkit will be extended and applied to control the arms in manipulation and acrobatic modes. Momentum management and conservation is integral to the control during acrobatic mode. Included will be dynamic simulation software that, by leveraging Energid's commercial Actin software, will be cross platform, fast, and feature rich. The simulation, modeling both the Astrobee and the arms, will support design validation efforts as well as mission planning and testing. It will seamlessly transition between simulating terrestrial test beds and the fielded Astrobee. The full system will be validated using a custom hardware testbed and granite table operation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Energid has sold approximately 400 of its own robots to customers in many fields and markets. This contract will enable Energid to extend these sales into new markets, particularly for use with terrestrial quadcopters. In addition, Energid will license the control and simulation software improvements made to its Actin software toolkit. Actin is delivered as libraries and header files that can be compiled into new software. It is used in ground, air, surface, and undersea environments. This form of Energid's technology has found application in software for manufacturing, entertainment, agriculture, and oil exploration. Energid will license the new software and provide services to support it.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The arm Energid proposes will advance the application of Astrobee by allowing it to perform more tasks in new ways. The simulation software, which includes both arm and base dynamics and sensors will support NASA and other researchers in exploring algorithms and missions before fielding. The value provided through these applications will lead to additional work for Energid from NASA. Energid will provide support for the arms and simulation software's application on upcoming missions both as a prime contractor and as a supporting subcontractor to large NASA prime contractors.

TECHNOLOGY TAXONOMY MAPPING (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.)
Autonomous Control (see also Control & Monitoring)
Robotics (see also Control & Monitoring; Sensors)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Models & Simulations (see also Testing & Evaluation)


PROPOSAL NUMBER:17-2 Z5.02-8656
PHASE-I CONTRACT NUMBER:NNX17CA46P
SUBTOPIC TITLE: Robotic Systems - Mobility Subsystems
PROPOSAL TITLE: Tensegrital Wheel for Enhanced Surface Mobility
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ProtoInnovations, LLC
5453 Albemarle Avenue
Pittsburgh,PA 15217 -1132 (412) 916-8807
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
DIMITRIOS APOSTOLOPOULOS
da1v@protoinnovations.com
5453 Albemarle Avenue
Pittsburgh ,PA 15217 -1132
(412) 916-8807

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

ProtoInnovations, LLC is developing an inventive system for wheeled mobility that exploits the geometric and mechanical attributes of tensegrity to engage with the terrain in an effective and efficient manner. Dubbed the tensegrital wheel, this unique wheel design emulates the behavior of a variable pressure tire without the need for an inflation system. The construction of the tensegrital wheel is such that it absorbs and diffuses ground forces evenly. The stiffness of the tensegrital wheel can be tuned to match the demands of a given terrain that the wheel is to operate on or can be adjusted on-the-fly. These attributes allow for better adaptation to the terrain thus increasing the amount of thrust that can be generated at the wheel/ground interface, and improving a vehicle’s dynamic response and obstacle negotiation. We assert that the tensegrital wheel can be designed to achieve an exceptional strength-to-weight ratio and capacity for long-life specifically in the context of planetary exploration. In Phase I of this SBIR we proved the feasibility of the concept through analysis, testing, and demonstrations. In Phase II we will optimize various tensegrtial wheel designs and advanced the maturity and readiness of this system for filight worthiness.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Tensegrital wheels could be applied in a variety of vehicles and field machinery in mining, design, construction, farming, and utility industries. What makes the tensegrital wheel a promising option is its adjustable compliance, great payload ratio, low-ground pressure, and scalability.
Many military vehicles currently use active control of tire air pressure to adjust compliance of the tires and deal with deflation due to punctures. As with planetary rover systems, using the tensegrity wheel for this application negates the need for pumps, pneumatic lines and pneumatic rotary joints. No pneumatic tire means no risk of puncture. In addition, the tensegrital wheel offers a lightweight alternative to unconventional wheel designs such as Michelin?s TWEEL?.
Farm and industrial vehicles can find application for the tensegrital wheel as well. A tractor, for instance, might negotiate cross slopes more safely and effectively by selectively adjusting the compliance of the wheels so that the uphill wheels are more compliant than the downhill wheels providing a measure of center-of-gravity control. Likewise the pose of industrial vehicles such as manlifts can be provided with additional control through the use of the tensegrital wheel technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The tensegrital wheel will benefit future NASA planetary exploration missions by enhancing the mobility and controllability of surface exploration rovers. Potential missions of interest include surface missions to Mars and the Moon. The ability of the tensegrital wheel to better conform to the terrain and its inherent capacity to evenly distribute reaction loads through its structure would result in measurable improvements in in-soil traversability, obstacle climbing, stability, and response to dynamic events. The tesnegrital wheel affords significant advantages over existing wheel systems for planetary rovers. While the structural design of existing wheel systems provides compliance approximating that of a pneumatic tire, such compliance is fixed by the design. Because if the high payload-supporting capacity, very low ground pressure, and scalability this wheel design opens up a number of possibilities in planetary vehicle design and mission capabilities.

TECHNOLOGY TAXONOMY MAPPING (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.)
Machines/Mechanical Subsystems
Structures
Vehicles (see also Autonomous Systems)
Robotics (see also Control & Monitoring; Sensors)


PROPOSAL NUMBER:17-2 Z5.02-9041
PHASE-I CONTRACT NUMBER:NNX17CJ39P
SUBTOPIC TITLE: Robotic Systems - Mobility Subsystems
PROPOSAL TITLE: Deft Control Software (DCS) for Remote Robotic Operations with Underlying Structure
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
BluHaptics, Inc.
108 Northwest Canal Street
Seattle,WA 98107 -4933 (303) 630-9153
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Fredrik Ryden
fredrik@bluhaptics.com
108 NW Canal St
Seatte ,WA 98107 -4933
(206) 724-9160

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Future space missions will increasingly rely upon tele-operated robots to perform work remotely. This will require substantial improvements in robotic function, cognition, and human/machine interaction. The goal of this work is to realize this future by addressing key challenges in robotic space operations.

BluHaptics has successfully demonstrated both the feasibility and potential impact of using our Deft Control Software (DCS) to provide pilot assistance to enable safe, intuitive and efficient remote teleoperation of NASA’s robotic systems. The primary goal of our Phase II effort is to develop and deliver a solution that enables intuitive tele-robotic control in dynamic scenarios, such as when targets and possibly interfering objects are moving in the workspace. This proposed approach combines 3D sensing and novel machine learning algorithms with simultaneous localization and mapping (SLAM) for workspace visualization SLAM, to obtain real-time tracking that provides pilot guidance. By increasing situational awareness and implementing safety features such as collision-avoidance, DCS can garner pilot trust, improve
safety, mitigate training time and support rapid task switching.

We will perform physical experiments and task demonstrations using two separate robotic platforms that are readily available to our team: (1) MANTIS -- a compact and highly dexterous manipulator designed to fit inside an ExpressRack locker; and (2) Schilling Titan4 -- a work-class hydraulic manipulator commonly used in offshore oil and gas operations. Phase II work will demonstrate how these operator assistance capabilities impact the feasibility and effectiveness of complex robotic operations in two task scenarios that are key to the success of future NASA missions.

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The DCS algorithms developed throughout this program will position BluHaptics to fill a major capability gap for the US Navy, which is the ability to autonomously (minimally supervised) connect electronic and communications subsea assets and to perform periodic maintenance. At a high level, the Navy would like to covertly install/maintain subsea monitoring systems, which is logistically difficult now as a surface vessel is required for the task. The machine learning algorithms developed as part of the program will allow naval operations to use reconnaissance data to train robots for intervention tasks to close the capability gap.

Outside the USG sector, DCS algorithms can be adapted and integrated into Dex-OS to support advanced capabilities for the offshore energy industry, who seek to reduce operations expenses by moving control stations from the ship onto shore and also reduce dependencies on large support ships by making the ROVs resident near major subsea asset clusters. DCS algorithms can evolve as intervention tasks become more challenging either due to complexity or due to bandwidth and latency constraints.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Even before commencement of this Phase II program, BluHaptics will collaborate with TUI first in their MANTIS Phase II program, and then within a soon-to-be proposed MANTIS Phase III program, where BluHaptics Dex-OS will provide basic control of the KRAKEN arm to enable swapping of microplate sample trays. This initial integration effort will also provide a foundation for the additional MANTIS related work as proposed here. Dex-OS can then be further developed for other programs such as TUI's orbital FabLab, which uses the KRAKEN arm to handle 3D printed parts and perform self maintenance. This type of joint development and collaboration provides a perfect example of how BluHaptics general commercialization strategy is applied in practice.

DCS algorithms will enable operations support on earth to utilize simulation-based unsupervised machine learning and one- touch minimally supervised machine learning to quickly train the control system to enable assistive control to perform tasks with underlying structure on the ISS. BluHaptics will pursue Phase III programs with NASA to amplify the capabilities of platforms such as Robonaut2 to enable (for example) telerobotic work on the ISS such as swapping of express lockers, connecting/disconnecting cables, flipping switches and other repetitive tasks that could free up astronauts to perform higher value tasks.

TECHNOLOGY TAXONOMY MAPPING (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.)
Operating Systems
Autonomous Control (see also Control & Monitoring)
Intelligence
Man-Machine Interaction
Perception/Vision
Robotics (see also Control & Monitoring; Sensors)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Command & Control
Teleoperation
Image Processing


PROPOSAL NUMBER:17-2 Z5.02-9047
PHASE-I CONTRACT NUMBER:NNX17CJ35P
SUBTOPIC TITLE: Robotic Systems - Mobility Subsystems
PROPOSAL TITLE: A General Purpose Software Toolkit for Robot Control and Application Programming
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TRACLabs, Inc.
100 North East Loop 410, Suite 520
San Antonio,TX 78216 -1234 (281) 461-7886
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Stephen Hart
swhart@traclabs.com
16969 N. Texas Ave. Suite #300
Webster ,TX 77598 -4085
(281) 678-4194

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Over previous Phase I, II, and III NASA SBIR projects, TRACLabs has created a software toolkit for
programming and controlling humanoid robots and other mobile manipulators. This open-source toolkit,
called the CaRtesian-based AFfordance Template Suite for MANipulation (or CRAFTSMAN), incorporates
state-of-the-art motion generation techniques along with principles of user interface design and software
engineering to fill a gap in the robotics research community for advanced sensor-driven application
development. While this toolkit was initially supported by NASA, further support from a large-scale
automotive client and robotics manufacturers has allowed TRACLabs to mature the code-base for its
deployment in industrial and commercial contexts. Despite this commercialization success, the capabilities
of CRAFTSMAN motion control have mainly been focused on a small set of robot-independent trajectory
generation algorithms, and the deployment of the system has been limited to classes of manipulation tasks
where goals can be represented as spatial waypoints for the robot’s end effectors or navigation systems.

It is the goal of this work to refactor CRAFTSMAN into a more general plugin-based control framework that supports techniques for advanced motion planning, reactive control, and automous stance location. We argue that this refactor would be beneficial by providing a common application programming framework that can be used on multiple systems in a variety of environments, and where new functionality can quickly be integrated to facilitate a number of NASA-relevant missions. We call this next generation of out toolkit CRAFTSMAN++.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
TRACLabs is already working with a large-scale automotive customer to integrate CRAFTSMAN into a production cell at one of their factories. This "flexible workcell" was installed in the Fall of 2017 and continues to operate 24/7 without human supervision. TRACLabs is currently in negotiations to reproduce the developed cell at another location within the same plant, as well as to adapt the software to additional tasks. The customer's ultimate goal is to build the "factory of the future" where robots can adapt quickly to part location or shape variation and can work safely with humans without the need for barriers or other expensive safety equipment.

While the mentioned customer has chosen TRACLabs to be their primary software developments for this effort, the need for flexible robot software in industrial applications is becoming increasingly obvious. As the demands for robust & capable systems grows, application software will need to rely less on tools based on precomputed motions, and more on sensor-driven, reactive techniques that can reliably perform complex assembly tasks. Our software will greatly facilitate this goal. Based on our success to this point, we expect substantial interest from additional commercial partners in automotive, energy, construction, and service domains to integrate our control software (and any improvements we make to it through further development) and have begun discussions to these ends with a number of potential customers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This work is directly applicable to improving the capabilities of current NASA robotic systems such as Valkyrie, SSRMS, and Resource Prospector. TRACLabs has contacts with NASA JSC ER robotics specialists including Scott Askew, Dr. Joshua Mehling, Dr. Kimberly Hambuchen, Dr. Ron Diftler, and Dr. Bill Bleuthmann. TRACLabs also has contacts Within NASA MOD ROBO flight controllers, including Quinn Carelock (DX2 branch chief), Scott Wenger (robotics team lead), Jennie Young (USA), and Tifanie Smart (USA) and can leverage these contacts to guide the development of capabilities and human interfaces that NASA robots require. As future NASA robotics missions are expected to rely heavily on dexterous mobile robots such as Valkyrie, these robots will need sophisticated application development and autonomy software in order to function. Such capable systems will assist humans with tasks such habitat construction or geological excavation or will be required to perform autonomous repair tasks on satellites or Deep Space Gateway. The CRAFTSMAN++ toolkit will allow task developers to program these capabilities while also allowing a human teleoperator to monitor and control these robots to ensure mission success.

TECHNOLOGY TAXONOMY MAPPING (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.)
Development Environments
Autonomous Control (see also Control & Monitoring)
Robotics (see also Control & Monitoring; Sensors)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Command & Control
Process Monitoring & Control
Teleoperation
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 Z6.01-8732
PHASE-I CONTRACT NUMBER:NNX17CP47P
SUBTOPIC TITLE: High Performance Space Computing Technology
PROPOSAL TITLE: FLASHRAD: A Non-Volatile 3D Rad Hard Memory Module for High Performance Space Computers
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Irvine Sensors Corporation
3001 Red Hill Avenue, B3-108
Costa Mesa,CA 92626 -4506 (714) 444-8700
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Yamaguchi
jyamaguchi@irvine-sensors.com
3001 Red Hill Avenue, B3-108
Costa Mesa ,CA 92626 -4506
(714) 444-8785

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The computing capabilities of onboard spacecraft are a major limiting factor for accomplishing many classes of future missions. Although technology development efforts are underway that will provide improvements to spacecraft CPUs, they do not address the limitations of current onboard memory systems. In addition to CPU upgrades, effective execution of data-intensive operations such as terrain relative navigation, hazard detection and avoidance, autonomous planning and scheduling, and onboard science data processing and analysis require high-bandwidth, high-capacity memory systems to maximize data storage and provide rapid access to observational data captured by high-data-rate instruments (e.g., Hyperspectral Infrared Imager, Interferometric Synthetic Aperture Radar).

Three-dimensional ICs, after a long wait, are now a reality. The first mainstream products are 3D memory cubes that offer manifold improvements in size, capacity, speed, and power. Unfortunately, none of these are ready for space. The purpose of this research and development is to pursue a non-volatile, 3D memory module that can meet the high-reliability requirements of space and interface to the High Performance Space Computer (HPSC) using a high-speed serial interface. Development will include fabricating a 3D memory cube and RTL for a FPGA based memory controller which will eventually be migrated to a rad-hard ASIC.  The FPGA based platform will integrate a 3D memory cube to produce a 3D memory module prototype that will validate and demonstrate the features, reliability, and performance of the envisioned 3D module.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Optimization of the logic base of a memory cube has not been available for any application. Development of the design tools to achieve better optimization of these logic bases will in turn lead to a broader application base which will benefit not only the users for space applications, but will benefit terrestrial users to help improve the efficiency of their electronics by addressing SWaP issues.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The computing capabilities of onboard spacecraft are a major limiting factor for accomplishing many classes of future missions. Although technology development efforts are underway that will provide improvements to spacecraft CPUs, they do not address the limitations of current onboard memory systems. In addition to CPU upgrades, effective execution of data-intensive operations such as terrain relative navigation, hazard detection and avoidance, autonomous planning and scheduling, and onboard science data processing and analysis require high-bandwidth, high-capacity memory systems to maximize data storage and provide rapid access to observational data captured by high-data-rate instruments (e.g., Hyperspectral Infrared Imager, Interferometric Synthetic Aperture Radar).Three-dimensional ICs, after a long wait, are now a reality. The first mainstream products are 3D memory cubes that offer manifold improvements in size, capacity, speed, and power. Unfortunately, none of these are ready for space. The purpose of this research and development is to pursue a non-volatile, 3D memory module that can meet the high-reliability requirements of space and interface to the High Performance Space Computer (HPSC) using a high-speed serial interface. Development will include fabricating a 3D memory cube and RTL for a FPGA based memory controller which will eventually be migrated to a rad-hard ASIC. The FPGA based platform will integrate a 3D memory cube to produce a 3D memory module prototy

TECHNOLOGY TAXONOMY MAPPING (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.)
Metallics
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Manufacturing Methods
Materials (Insulator, Semiconductor, Substrate)
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Processing Methods


PROPOSAL NUMBER:17-2 Z6.01-9874
PHASE-I CONTRACT NUMBER:NNX17CG53P
SUBTOPIC TITLE: High Performance Space Computing Technology
PROPOSAL TITLE: Double Data Rate 3 Controller for Use in Radiation Environments
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microelectronics Research Development Corporation
4775 Centennial Boulevard, Suite 130
Colorado Springs,CO 80919 -3332 (719) 531-0805
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Greg Pauls
greg.pauls@micro-rdc.com
4775 Centennial Boulevard, Suite 130
Colorado Springs ,CO 80919 -3332
(719) 531-0805 Ext: 4

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Manned and robotic space missions require high-performance electronic control systems capable of operating for extended periods in harsh environments subject to radiation, extreme temperatures, vibration and shock.  Semiconductor technologies capable of meeting these demanding requirements tend to have limited capabilities, are expensive, and are not easily configured for specific mission requirements.  Leading-edge applications will benefit from the ability to implement high speed interconnect protocols between host processors and system slaves, such as sensors, actuators, power managers, imagers and transceivers.  The development of a Radiation Hardened Double Data Rate (DDR3) embedded memory controller macro is proposed for insertion into digital integrated circuits suitable for scalable single and multi-core processors, special purpose logic functions and scalable memory blocks on a space-qualified, radiation hardened integrated circuit digital fabric.  A Structured ASIC architecture is under development at Micro-RDC capable of meeting space-grade requirements while creating a cost-effective, quick-turn development environment.  The SASIC fabric will implement known Radiation-Hardened-By-Design (RHBD) techniques on an advanced 32nm CMOS SOI process, supporting high-density, high-speed, low-power implementations.  A unique Master Tile architecture with through-seal-ring connections allows the designer to define dedicated logic functions, scalable memory blocks and user-defined I/Os; all on a single, scalable integrated circuit.  The 32nm SOI CMOS process technology platform incorporates RHBD building-blocks (e.g. flip-flops, gates, distributed memory, block memory, I/O) required for the systems designer to implement functional blocks for application-specific requirements.  During this project key blocks for a DDR3 memory controller macro will be developed and prototyped for insertion into the Micro-RDC platform allowing more complex digital processing elements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Companies that deploy satellites for purposes similar to NASA's Earth-centric applications will greatly benefit by gaining access to the advanced 32nm SOI CMOS process technology in a cost efficient manner. There are a number of applications that require this kind of performance within military, intelligence and commercial satellites which are showing growing demand in units deployed and performance. The 2014 FAA Commercial Space Transportation Forecasts predicts that an average of seventy eight commercial payloads will be launched annually over the next decade. A reasonable estimate of the number of classified military and intelligence payloads at least equals the commercial deployments. Micro-RDC currently offers a 90nm CMOS platform, 50MHz RHBD Structured ASICs capable of handling low to mid-range control and compute requirements in space. The 32nm SOI CMOS platform will increase to 300MHz, greatly improving densities and processing speed, including the ability to interface to DDR3 memory. Modern multi-processor computing requires access to high capacity memory in order to support sensors, actuators, image capture and processing subsystems and data communications links.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA supports various requirements ranging from science missions, space station, and deep space missions requiring high-performance computing and controls. Interplanetary and long term low Earth orbit systems require radiation tolerances capable of ensuring that the on-board electronics outlast the life expectancy of the systems. These demanding requirements of radiation tolerance and harsh operating environments force satellite systems developers to consider capabilities that are uniquely optimized for their applications. The Structured ASIC solves the dilemma of balancing performance, cost, risk and time to deployment against alternative solutions. Scalable, high performance control systems can support a wide range of applications when integrated circuit flexibility is available. The ability to right-size integrated circuits while adding functional blocks, such as high speed DDR3 memory, while maintaining performance at low costs enables NASA to use this technology across a wide range of programs and applications. NASA programs/missions that could benefit include the Thermal Infrared Sensor (TIRS) mission, Climate Absolute Radiance and Refractivity Observatory (CLARREO), BOReal EcosystemAtmosphere Study (BOREAS) and the Methane Trace Gas Sounder. Longer term missions include lunar landers and orbiters, Mars missions (MAVEN), solar system exploration (e.g. Titan, Juno, Europa, comet nucleus return, New Discovery, and Living with a Star (LWS)).

TECHNOLOGY TAXONOMY MAPPING (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.)
Telemetry (see also Control & Monitoring)
Electromagnetic
Verification/Validation Tools
Simulation & Modeling
Avionics (see also Control and Monitoring)
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Intelligence
Protective Clothing/Space Suits/Breathing Apparatus
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Characterization


PROPOSAL NUMBER:17-2 Z7.01-8404
PHASE-I CONTRACT NUMBER:NNX17CP64P
SUBTOPIC TITLE: Supersonic Parachute Inflation Materials Testing, And Instrumentation
PROPOSAL TITLE: Weaved Distributed Plastic Optical Fiber Sensor (DIFOS) SHM system
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Redondo Optics, Inc.
811 North Catalina Avenue, Suite 1100
Redondo Beach,CA 90277 -2198 (310) 406-1295
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
edgar mendoza
emendoza@redondooptics.com
811 North Catalina Avenue, Suite 1100
Redondo Beach ,CA 90277 -2198
(310) 292-7673

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

ROI with the support of a strategic partners from the decelerator vehicle business will complete the engineering development, produce, extensively laboratory test, environmentally qualify on a relevant parachute platform, and deliver to NASA a low power lightweight, small form factor, weaved DIFOS SHM system. At the end of the Phase II program, ROI will identify a relevant parachute platform an instrumented with a large array of POF sensors weaved within the textile fabrics of the parachute. The instrumented parachute demonstration platform will be laboratory and airborne tested under simulated load test conditions encountered by NASAs decelerator systems, and it will evaluate the time synchronize data collection and wireless data transferring fidelity and quality of the DIFOS SHM system. ROI will also develop am airworthiness qualification plan, including compliance with environmental, vibration, shock, pressure, and water immersion. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The DIFOS SHM system represents a new, innovative, and reliable solution for the in-flight time synchronized distributed monitoring of the passive and dynamic structural state (load/stress/strain) levels of trailing body deployable supersonic decelerator technologies. Its, lightweight, compact package, self-power efficient, wireless communication, distributed and embedded DIFOS SHM network system provide unique cost affordable solution for many SHM/NDE applications. In the parachute market, the major share is controlled by the military sector, which uses them extensively on its aircraft and for use by the paratroopers. Growing conflicts and wartime scenario across world is a major factor driving the employment of parachutes in military. Further, sales of unmanned aerial vehicles have been experiencing high growth around the world. This is one major booster for the global parachute market. The DIFOS technology addresses the global SHM/NDE aerospace and avionics market expected to grow to over 6.8-billion in 2020 and with the potential to instrument over 6000 space flight vehicles, military, and commercial airplanes, and peripheral structural monitoring system with additional markets in wind turbines, energy power plants, oil & gas, pipelines, petrochemical and geothermal exploration, civil infrastructures, health-care, and security.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
All of NASA's current and future space vehicle programs will benefit significantly from this project, wherein the key technological challenge is to develop methodologies for monitoring load, stress, strain, flaws, fatigue, and degradation in large complex structures. NASA's Robotic Exploration Program has a critical need for advanced sensor systems to enhance and expands NASA's current SHM. Specific NASA applications of the DIFOS SHM system include un-attended inspections on large and complex composite structures, i.e., decelerator systems parachutes and ballutes, honeycomb structures, multi-wall pressure vessels, thermal blankets, meteoroid shields, batteries, etc., commonly found in spacecraft, and habitats, and support infrastructures.

TECHNOLOGY TAXONOMY MAPPING (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.)
Structures
Entry, Descent, & Landing (see also Astronautics)
Nondestructive Evaluation (NDE; NDT)
Diagnostics/Prognostics
Aerodynamics
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)


PROPOSAL NUMBER:17-2 Z7.02-9990
PHASE-I CONTRACT NUMBER:NNX17CA19P
SUBTOPIC TITLE: Deployable 3D Woven Thermal Protection Materials
PROPOSAL TITLE: Novel Spider 3D Woven Seamless ADEPT Aero-Shell
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Bally Ribbon Mills
23 North 7TH Street
Bally,PA 19503 -1904 (610) 845-2211
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Curt Wilkinson
curtwilkinson@ballyribbon.com
23 North 7TH Street
Bally ,PA 19503 -1904
(610) 845-2211 Ext: 3051

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Bally Ribbon Mills will focus on the advancement, development, and demonstration of the proposed innovation, ADEPT Spider Weaving. Phase 2 will demonstrate and produce one-piece ADEPT spider woven aero shells for the Sprite C and SR-1 configurations. The Sprite C aero shells shall be delivered and ready to attach to the current Sprite C understructure for arc jet testing. The SR-1 aero shells will demonstrate the ability to scale-up the Spider Weaving process and provide aero shells ready to attach to the current SR-1 understructure. The proposed technology to manufacture aero-shell will allow each mission to utilize an aero-shell design that fits within existing launch vehicle systems and later transforms into a low ballistic coefficient configuration for descent and landing. 

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology can be applicable for commercial space industry such as applications to venture tourism, communications, and safely deploy scientific payloads to Saturn, Jupiter and Uranus.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications that could utilize BRM's Spider Woven aero shells include 6m ADEPT Venus Mission Concept, 16m Lifting ADEPT Human Exploration, 1m ADEPT Mars Lander Malin SSS Concept and 1.0+m Lifting Nano ADEPT.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Textiles
Entry, Descent, & Landing (see also Astronautics)
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)
Processing Methods


PROPOSAL NUMBER:17-2 Z7.03-8438
PHASE-I CONTRACT NUMBER:NNX17CL36P
SUBTOPIC TITLE: Deployable Aerodynamic Decelerator Technology
PROPOSAL TITLE: High-Capacity, High-Speed, Solid-State Hydrogen Gas Generator
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Anasphere, Inc.
81 8th Street #1
Belgrade,MT 59714 -3320 (406) 595-3286
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Bognar
jbognar@anasphere.com
81 8th Street #1
Belgrade ,MT 59714 -3320
(406) 595-3286

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Deployable aerodynamic decelerators are an enabling technology for missions to planets and moons with atmospheres as well as for returning payloads to Earth.  These decelerators require a gas source for inflation, and the objective is to provide an improvement over existing pressurized gas inflation systems. 

A hydrogen gas generator suitable for the inflation of Hypersonic Aerodynamic Inflatable Decelerators (HIADs) was developed and tested.  Key areas of Phase I work included the design of a heat generation and transfer system to function under zero-g conditions, component designs resistant to damage from the launch environment, design of an associated filtration and containment system, the fabrication and test of generators incorporating the foregoing designs, and the development of thermal models of the system.  Live tests successfully proved the operation of all of the new design features developed in Phase I. 

Phase II work will include: scaling up Phase I generator designs, building and testing larger generator examples with the largest being suited to 12-meter HIADs, environmental testing of the generators, nondestructive testing to assess the effects of environmental testing, a zero-g drop test, development of handling and lifecycle plans for the generators, and the deliverable of a fully functional generator to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Low-cost access to space will be enabled by HIAD systems which apply this generator technology because HIADs offer a practical means of recovering launch vehicle components such as engines. Commercial space ventures can also apply HIAD technology for the more efficient return of material to Earth.
Separately, unattended inflation of balloons in difficult environments, such as airborne or at-sea applications, will be facilitated by this hydrogen generator. The generator can also be used to supply hydrogen in logistics-constrained areas for balloon inflation and other purposes such as operating fuel cells.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application will be Hypersonic Inflatable Aerodynamic Decelerators (HIADs) as planned for use on missions to planets and moons with atmospheres as well as returning payloads to Earth. An additional application could be the inflation of planetary balloons.

TECHNOLOGY TAXONOMY MAPPING (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.)
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)


PROPOSAL NUMBER:17-2 Z8.01-8547
PHASE-I CONTRACT NUMBER:NNX17CC46P
SUBTOPIC TITLE: Small Spacecraft Propulsion Systems
PROPOSAL TITLE: Multi-Mode Micropropulsion
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Froberg Aerospace, LLC
900 Innovation Drice, Suite 200M
Rolla,MO 65401 -3690 (636) 497-6998
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Berg
steven.berg@frobergaerospace.com
900 Innovation Dr. Ste. 200M
Rolla ,MO 65401 -3690
(636) 497-6998

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

This project will further development of a thruster capable of both chemical monopropellant and electrospray propulsion using a single "green" ionic liquid propellant. the thruster concept consists of an integrated microtube/electrospray thruster that shares all propulsion system hardware between electric and chemical thruster modes, i.e. one propellant, one propellant tank, one feed system, and one thruster. Thus, the thruster is not significantly more massive than a standalone state-of-the-art chemical or electric thruster, but capable of either thrust mode and selectable as mission needs arise. This has several benefits, including the optimization of trajectories using both chemical and electric thrust manuevers as well as a significantly increased mission design space for a single propulsion unit. The propulsion system is capable of both high impulse per unit volume and high thrust per unit volume as the total impulse per unit volume is 1500 N-s/U in the chemical thrust mode and 2750 N-s/U in the electric thrust mode, where either type of manuever could be selected on-the-fly. Operation and high performance in both modes has previously been demonstrated at the single emitter level. The specific objectives for this study are to design and build a cubesat sized multi-emitter thruster and test in both chemical and electrospray modes of operation. Two thrusters will be built and separate chemical and electric thrusters tested in parallel. Then, back-to-back operation of a single thruster will be demonstrated and indirect and direct performance measurements will be acquired. Additionally, the development of the multi-mode monopropellant will be furthered through material compatibility tests and hazard classification. Finally, system level items including PPU and and feed system components will be researched and selected and/or designed.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Multi-mode micropropulsion has potential to meet Air Force needs for fractionated, composable, survivable, autonomous systems, i.e., satellites that can be assembled, tested, and launched within days of operational requirement. Specifically, the large mission design space resulting from ability to select and complete chemical or electric maneuvers at will significantly enhances the capabilities of these 'plug-and-play' satellites. It has potential to impact the exploding small/CubeSat market, an estimated market value of $7.4B, with a predicted 360% increase in launches over the next 5 yrs, and future plans for competing space-based internet constellations. The large mission design space enabled by multi-mode propulsion could be beneficial to this market in that a single, off-the-shelf system is capable of many different types of missions. An entirely new propulsion system would not have to be developed for each mission individually, reducing costs associated with development, testing, and risk. Additionally, the multi-mode capability has been shown to drastically increase the mission capabilities of swarms or constellations of small satellites.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Multi-mode propulsion fulfills NASA technology needs as outlined in the In-Space Propulsion Technology Roadmap, monopropellant microthrusters and electrospray thrusters, as well as fulfilling needs highlighted by the National Research Council, specifically the need for both chemical and non-chemical propulsion that fulfills the needs for high mobility micro-satellites and extremely fine pointing and positioning for certain astrophysics missions. Research has shown the benefits of multi-mode micropropulsion for NASA missions, including, more efficient small satellite formation flight, optimized attitude control, enhanced transfer rate and useful mass for Jovian missions, more favorable conditions for lunar impact, launch mass savings, and payload mass advantage to GEO. Additionally, the flexibility of the multi-mode propulsion platform allows for a common unit to be used for many different types of missions, eventually reducing both risk and development time for many types of science payload missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fuels/Propellants
Maneuvering/Stationkeeping/Attitude Control Devices
Spacecraft Main Engine


PROPOSAL NUMBER:17-2 Z8.01-9758
PHASE-I CONTRACT NUMBER:NNX17CP36P
SUBTOPIC TITLE: Small Spacecraft Propulsion Systems
PROPOSAL TITLE: Fiber-fed Advanced Pulsed Plasma Thruster (FPPT)
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CU Aerospace, LLC
301 North Neil Street, Suite 502
Champaign,IL 61820 -3169 (217) 239-1703
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Curtis Woodruff
woodruff@cuaerospace.com
301 N. Neil St.-Suite 502
Champaign ,IL 61820 -3169
(309) 255-8442

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

CU Aerospace (CUA) proposes the continued development of a Fiber-fed Pulsed Plasma Thruster (FPPT) that will enable cis-lunar and deep space missions for small satellites. While classic PPT technology is mature, it has historically been limited by its propellant load to precision pointing and small delta-V applications. A recent thruster advancement by CUA, Monofilament Vaporization Propulsion (MVP), adapted extrusion 3D printing technology to feed polymer propellant fiber to a resistojet thrust chamber. FPPT leverages this advancement by feeding PTFE fiber to its discharge region, enabling class-leading PPT propellant throughput and variable exposed fuel area. An innovative, highly parallel ceramic capacitor bank dramatically lowers system specific mass. FPPT is inherently safe; its non-pressurized, non-toxic, inert propellant and construction materials minimize range safety concerns. The Phase I effort accumulated more than 582,000 pulses, with thrust-stand measured Ibits from 0.057 – 0.241 mN-s at 960 – 2400 s specific impulse, representing a dramatic enhancement from state-of-art PPT technology. A Phase II 1U FPPT thruster will provide 2200 – 4900 N-s total impulse, enabling 0.4 – 1.0 km/s delta-V for a 5 kg CubeSat.  A 1U design variation with 590 g propellant enables as much as ~10,000 N-s and 2 km/s for a 5 kg CubeSat.  Advancing the technology to a 2U form factor increases propellant mass to 1.4 kg and delta-V to 10.7 km/s for an 8 kg CubeSat. CUA anticipates delivering to NASA a life-tested flight-like > 2,000 N-s 1U integrated system by the end of Phase II including the advanced thruster head with igniter system, PTFE fiber feed system, power processing unit, and control electronics.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Commercial interest in very small satellites continues to grow. In the 1-50 kg satellite sector, launches have shifted from a fairly balanced distribution between civil, government, commercial, and defense (2009-2016) to a distribution dominated by commercial interests. Moving forward, it is more important than ever that these satellites have access to propulsion systems to extend their asset time on orbit. The proposed thruster offers CubeSats and other small satellites a significant propulsion capability with high impulse per unit volume. The FPPT thruster will provide a compact, light-weight, non-hazardous propulsion technology solution that will be made available in a family of sizes that can meet the differing needs of users in DOD, industry, and universities for CubeSat and small-satellite missions. FPPT will require no safety equipment for storage, transportation, integration, and testing, and place no demanding requirements on the launch provider, making it an ideal low-cost solution for industry, research, and academic small-satellite propulsion needs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Historically, pulsed plasma systems have targeted small delta-V applications such as ACS. With the demonstrated high performance of CUA's FPPT (Isp up to 2400 seconds) and its innovative propellant feed and storage system, FPPT exceeds the goals of the Z8.01 topic and outperforms previous state of the art PPT systems, as well as newer technologies. With an anticipated > 2,000 N-s total impulse from a 1U system, large orbit transfers and even inclination changes of tens of degrees are now available to smaller satellites. The intrinsic safety of FPPT and its inert, unpressurized PTFE propellant position it as a prime candidate for secondary payload missions where costs and logistics are dominated by range safety concerns. The solid propellant has no handling, storage, or operational restrictions. The ease of handling and storage for the solid propellant can extend operation to planetary missions with no additional monitoring or controls. FPPT system unit costs are anticipated to be significantly below competing CubeSat propulsion systems.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ablative Propulsion
Fuels/Propellants
Maneuvering/Stationkeeping/Attitude Control Devices
Spacecraft Main Engine
Relative Navigation (Interception, Docking, Formation Flying; see also Control & Monitoring; Planetary Navigation, Tracking, & Telemetry)
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)


PROPOSAL NUMBER:17-2 Z8.02-9171
PHASE-I CONTRACT NUMBER:NNX17CA35P
SUBTOPIC TITLE: Small Spacecraft Communication Systems
PROPOSAL TITLE: Compact Multi-Protocol Modem
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Innoflight, Inc.
9985 Pacific Heights Boulevard, Suite 250
San Diego,CA 92121 -4712 (858) 638-1580
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thao Pham
tpham@innoflight.com
9985 Pacific Heights Boulevard, Suite 250
San Diego ,CA 92121 -4712
(858) 638-1580 Ext: 181

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Legacy SDR (Software Defined Radio) has been somewhat hailed as the “be all, end all” solution to communications systems.  Reality is that SDR platforms are challenged by the clock speed of the underlying processor, and the fact that waveform design is not a simple process.  As missions keep pushing for higher throughput communications platforms, it is often the case that legacy SDR platforms cannot.  It is also a common end result that the SDR power consumption is very high when compared to non SDR platforms.  These factors pose quite a challenge for mobile platforms – spacecraft platforms in particular.

Innoflight is introducing advance Hybrid-SDR platforms together with Model Based System Engineering (MBSE) design flow.  The combined technologies will provide a streamlined approach for the design of advanced multi-mode communications system that are applicable to NASA’s NEN (Near Earth Network), SN (Space Network), and DSN (Deep Space Network) infrastructure and are ready to support next generation optical (i.e. laser) communications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Unmanned platforms are being deployed in many applications in the DoD and commercial sectors. Such platforms are used in terrestrial, aviation, and maritime applications. Such systems rely on numerous advanced network communication systems. Most of these applications are also sensitive to SWaP and will benefit from Hybrid-SDR performance.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA applications include:
1) CubeSat missions.
2) Missions requiring advanced communications modes.
3) Lunar and deep space missions.
4) Optical communications systems.
5) Balloons and UAVs.

TECHNOLOGY TAXONOMY MAPPING (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.)
Lasers (Communication)
Ranging/Tracking
Telemetry (see also Control & Monitoring)
Microwave
Simulation & Modeling
Architecture/Framework/Protocols
Transmitters/Receivers
Models & Simulations (see also Testing & Evaluation)
Prototyping
Software Tools (Analysis, Design)


PROPOSAL NUMBER:17-2 Z8.02-9571
PHASE-I CONTRACT NUMBER:NNX17CP24P
SUBTOPIC TITLE: Small Spacecraft Communication Systems
PROPOSAL TITLE: Efficient and Secure Network and Application Communications for Small Spacecraft
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Antara Teknik, LLC
5233 Castlereigh Court
Granite Bay,CA 96746 -7123 (916) 622-6960
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
MEHMET ADALIER
madalier@antarateknik.com
5233 Castlereigh Court
Granite Bay ,CA 96746 -7123
(916) 834-4729

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

For complex missions that are away from Earth's resources, there is an unmet need for more autonomous operations with minimal Earth contact. Additionally, secure proximity- and autonomous-communication among various types of space vehicles are needed to implement complex and time-varying networks of spacecraft and sensors, which are capable of sharing rich, near-real-time streams of information. Efficient, secure, mission-configurable, and dynamic key management and cipher suites supporting multiple QoS levels for the bundle protocol are required to augment current and future Delay and Disruption Tolerant Networking (DTN) solutions to satisfy these mission requirements. Antara’s innovation will enhance the security of NASA’s DTN implementations, specifically, the Interplanetary Overlay Network (ION), and deliver a standards driven adaptation of the Constrained Application Protocol (CoAP) over the bundle protocol (CoAP-over-bp). Phase II activities include the development of taraCoAP Cyber-Physical Autonomous Asset Observation and Management module. Further R&D will drive the Elliptical Curve Crypto Key Management and Distribution module, the interoperable AntaraTek Cipher Suite for BPSec, and the scalable taraCoAP to TRL-7. The AntaraTek software will also be tested with ISS DTN payload communications (e.g., TReK). Additionally, the software will  be infused to rad-hard FPGAs and future compute platforms such as the High Performance Spaceflight Computing chiplet. Utilizing the ION framework will lower the cost and the time to develop a high TRL solution and reduce implementation risk. Antara's innovations will deliver higher security and performance relative to existing system technology, support complex and time-varying networks, scale to large networks, and enable secure communications for the Solar System Internet. Successful deployment of the innovation will address NASA technology gaps TA5.3.1 and TA5.3.3 and enhance the state-of-art for DTN implementations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Public Service and Safety: The technology will provide interoperable communications and real-time information sharing among Department of Homeland Security/FEMA first responders during disasters to effectively mitigate against threats and hazards.
Defense and Intelligence: The innovation will integrate with existing and future Software Defined Radio based communications devices and Situational Analysis/Battle Management apps to rapidly infuse emerging DTN based capabilities in order to enhance the resiliency of Mobile Ad-hoc Networks and securely extend the reach of forward deployed forces to increase tactical agility, facilitate collaboration, coordinated actions, and robust access to mission-critical data, information, and knowledge.
Commercial/Internet of Things: The innovation will securely enhance IoT applications in stressed environments such as cargo and vehicle tracking, global asset tracking, smart-city Machine to Machine communications, and humanitarian relief monitoring.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed efficient and secure low-power communications system, based on delay and disruption tolerant inter-networking, is a horizontal, fundamental enabling capability which will support multiple NASA applications and missions including the Solar System Internet. The proposed innovations will be applicable to planned and new missions by enabling the integration of standards-based, low-power, and secure key management and application communication components to the DTN network architecture/ION to provide scalable, flexible and secure bi-directional communications for swarms of spacecraft, satellite, and other applicable systems. Antara's innovations will directly support NASA use-cases such as ISS DTN communications and Autonomous Operations and Complex Network Topologies as described in TA5.3. The successful deployment of the innovations in space will help lower operational costs of systems by replacing manual scripting and commanding of individual spacecraft communications links. Additionally, the innovations will enable secure proximity communications and autonomous communication among various types of space vehicles to implement complex and time-varying networks of spacecraft and sensors that are capable of sharing rich, near-real-time streams of information.

TECHNOLOGY TAXONOMY MAPPING (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.)
Simulation & Modeling
Autonomous Control (see also Control & Monitoring)
Man-Machine Interaction
Robotics (see also Control & Monitoring; Sensors)
Ad-Hoc Networks (see also Sensors)
Architecture/Framework/Protocols
Network Integration
Algorithms/Control Software & Systems (see also Autonomous Systems)
Command & Control
Prototyping


PROPOSAL NUMBER:17-2 Z8.04-9706
PHASE-I CONTRACT NUMBER:NNX17CA57P
SUBTOPIC TITLE: Small Spacecraft Structures, Mechanisms, and Manufacturing
PROPOSAL TITLE: MakerSat
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tethers Unlimited, Inc.
11711 North Creek Parkway South, Suite D113
Bothell,WA 98011 -8808 (425) 486-0100
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Blaine Levedahl
blevedahl@tethers.com
11711 N Creek Pkwy S, D113
Bothell ,WA 98011 -8808
(425) 486-0100

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

As SmallSats become the “Satellite of Choice” for NASA and other Government and Private Space Missions, there is a growing need to enable SmallSats to perform “Long Baseline” and “Spatially Diverse” observation, measurement and collection missions.  Traditionally, these types of missions would be performed either by using formation flying or by using “large” satellites equipped with complex / advance deployable structures. The proposed “MakerSat Demonstration Mission” effort addresses a third alternative for accomplishing this class of missions:  In-Space Manufacturing “Constructable” technologies, that allow SmallSats to “grow / evolve” into significantly larger structures.  A SmallSat that once on orbit can increase its size from one to two orders of magnitude provides an exciting option to formation flying or deployable structures.  The goal of the proposed effort is to develop a demonstration mission that proves the viability of Constructable technologies as an alternative solution for “Long Baseline” and “Spatially Diverse” observation, measurement and collection missions.  

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In addition to direct NASA applications, the advancements from the proposed "MakerSat Demonstration Mission" effort for In-Space structural construction technologies would be directly applicable to constructing large structures in-space and enabling new missions in both the commercial space industry and the DoD. To support this assertion, TUI is already developing complementary in-space manufacturing technologies with both the DoD and commercial partners.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
SmallSats, including CubeSats, are quickly maturing technologically towards advanced capabilities, which will result in significant contributions to the achievement of NASA?s scientific and exploration missions. In fact, SmallSats are seriously being considered for complex, long duration missions to deep space locations and for Earth observing constellations. However, while SmallSats have the benefit of small size and mass, making them generally easier and cheaper to launch, many space applications require larger physical sizes or alternate structural architectures. These applications can be realized through the innovation of novel In-Space Manufacturing ?Constructable? techniques that can drive the utility of SmallSats even further.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Machines/Mechanical Subsystems
Structures
Antennas
In Situ Manufacturing


PROPOSAL NUMBER:17-2 Z8.05-9148
PHASE-I CONTRACT NUMBER:NNX17CG44P
SUBTOPIC TITLE: Small Spacecraft Avionics and Control
PROPOSAL TITLE: Integrated Waveguide Optical Gyroscope
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Gener8, Inc.
500 Mercury Drive
Sunnyvale,CA 94085 -4018 (650) 940-9898
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Bischel
bbischel@gener8.net
500 Mercury Drive
Sunnyvale ,CA 94085 -4018
(650) 940-9898

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

We propose a radical new approach for to the design and fabrication of an integrated Waveguide Optical Gyroscope (iWOG) that enables the development of very small IMU with near tactical grade performance, higher reliability, high level of robustness and lower cost.  Modeling demonstrate that the iWOG will have more than an order-of-magnitude improvement in bias stability over temperature (for the same volume) when compared to the highest performance commercially available MEMs gyroscope.  The iWOG is also inherently radiation hardened and is the ideal technology for future CubeSat applications at NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A commercial market exists today for a new gyroscope technology that has a 10x improvement in bias stability over temperature and vibration when compared to best available MEMs gyroscope. The largest market is rotation sensors for Self-Driving Vehicles. The proposed iWOG technology will result in the smallest volume optical gyroscope on the market today. It will also enable new DoD applications including airborne PODs, Line of Sight stabilization, weapon designation, individual soldier navigation, turret stabilization, and UAVs navigation

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This proposal will develop the key enabling component in a low cost, high precision inertial navigation system that would have 10 x better performance over MEMs navigation systems. Low cost, higher precision and low weight/power (SWaP) inertial sensors are necessary components for future NASA applications that include SmallSat, CubeSat, Unmanned Aircraft Systems (UAS) and Sounding Rockets.

TECHNOLOGY TAXONOMY MAPPING (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.)
Inertial (see also Sensors)
Inertial
Navigation & Guidance
Relative Navigation (Interception, Docking, Formation Flying; see also Control & Monitoring; Planetary Navigation, Tracking, & Telemetry)
Waveguides/Optical Fiber (see also Optics)


PROPOSAL NUMBER:17-2 Z8.05-9429
PHASE-I CONTRACT NUMBER:NNX17CG30P
SUBTOPIC TITLE: Small Spacecraft Avionics and Control
PROPOSAL TITLE: Milliarcsecond Small Spacecraft Attitude Control System
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)
Daniel Courtney
dcourtney@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 proposes to develop a highly modular attitude control system (ACS) which will provide orders of magnitude improvements over state-of-the-art alternative ACS for CubeSats. The low inertia of CubeSats combined with vibrational disturbances and resolution limitations of state-of-the-art ACS presently limit body-pointing and position control accuracy. Busek’s electrospray thrusters aboard the ESA LISA Pathfinder spacecraft recently demonstrated precision control at nm scales; this work extends that success to CubeSat platforms. Passively fed electrospray thrusters are highly compact, including fully integrated propellant supplies, and are capable of ~100nN thrust control at 10’s of nN noise. Thrust can be throttled over >30x, to a scalable maximum of 10’s of uN.  These traits, combined with >900s Isp enable these systems to replace traditional reaction wheel ACS; improving pointing error from arcsecs to 10’s of milliarcsec. This work addresses critical development gaps, in both thruster-heads and a multi-axis power processing unit, presently gating the technology. Phase I established a thorough baseline dataset, which confirmed critical performance metrics, and established development gaps. Phase II will emphasize total impulse goals and thruster system maturation. Task 1 will execute design modifications developed in Phase I and augment existing test capabilities. Task 2 will identify and address impulse limiting mechanisms. Task 3 will develop and validate solutions to known mechanical risks and incorporate evolved requirements into a low-mass engineering-model thruster module. Task 4 will focus on power processing development, targeting a control architecture which maximizes the precision control capabilities of the technology and serves multiple thruster heads. These efforts will converge in Task 5 where engineering model thruster performance will be rigorously evaluated over a complete life demonstration. 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Compact propulsion systems that are scalable in both thrust and deltaV without loss of performance are an enabling technology for CubeSat missions and therefore have numerous commercial applications. Potential non-NASA customers include, international partners (such as ESA), the DoD and commercial EO missions. The modular nature of the proposed technology would enable customized applications that simultaneously meet customer needs in precision pointing and disturbance compensation; therefore, maximizing the commercial applicability of the technology. The virtual elimination of vibrational jitter while superseding reaction wheel precision presents a clear competitive advantage. The proposed system would be applicable to a myriad of CubeSat sizes from ~3U to >25kg; the market size is therefore large and includes rapidly growing platforms. Commercial applications may include optical communication alignment for high bandwidth up/downlinks or precision pointing during EO missions in low orbits. De-orbiting applications are particularly relevant to new LEO EO and telecommunication initiatives. International consensus is forming around the need for orbital debris management, which poses risks to functioning space assets. The proposed system could enable precision attitude control and a de-orbit means from a single integrated system; thus reducing the burden of integrating a de-orbit system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA's 2015 technology roadmap recognizes the importance of electrospray propulsion to attitude control, formation flight and positioning of small spacecraft. Specific applications benefiting from precision pointing include astronomical missions, planetary (including earth) observations, laser communications and space situational awareness. The greatly improved body pointing afforded by the proposed technology would present designers with previously unobtainable levels of stability and resolution; permitting both lower cost/complexity realization of existing needs and enabling new objectives in these fields. Applications benefiting from highly precise position control include formation flights and missions requiring disturbance free flight. This includes drag-compensation enabling enhanced mission durations at low orbit altitudes below 350km. The proposed work would allow small spacecraft, CubeSats and larger, to benefit from precision control in a manner akin to the NASA Disturbance Reduction System (DRS), featuring Busek thrusters, aboard the LISA Pathfinder mission. Developing a highly featured PPU and controller would also enable other DRS sub-components, such as GSFC contributed control algorithms, to be applied over a wider NASA mission portfolio. Moreover, through replacing wheels or expanding wheel de-saturation capacity in deep space missions, the proposed work would decrease spacecraft size/complexity and enable new missions.

TECHNOLOGY TAXONOMY MAPPING (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.)
Maneuvering/Stationkeeping/Attitude Control Devices
Navigation & Guidance
Relative Navigation (Interception, Docking, Formation Flying; see also Control & Monitoring; Planetary Navigation, Tracking, & Telemetry)
Attitude Determination & Control
Command & Control


PROPOSAL NUMBER:17-2 Z9.01-9204
PHASE-I CONTRACT NUMBER:NNX17CM65P
SUBTOPIC TITLE: Small Launch Vehicle Technologies and Demonstrations
PROPOSAL TITLE: Flight Demonstration of a Micropump-based Stage Pressurization System
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vector Launch Inc.
824 East 16th Street
Tucson,AZ 85719 -6603 (520) 207-9734
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Robertson
james.robertson@vector-launch.com
10539 Humbolt Street
Los Alamitos ,CA 90720 -5401
(888) 346-7778 Ext: 45

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Vector Launch, Inc. proposes to apply recent advances in micropump and additive manufacturing technologies to develop and demonstrate a micropump-based autogenous pressurization system for its commercial Vector-R and mature the technology with multiple static-fire-tests leading to a demonstration flight test (TRL 6). The Vector-R is a 2-stage pressure-fed, LOX/subcooled propylene commercial small launch vehicle, designed to place up to 60 kg in low earth orbit. Electrically-driven micropumps drive a small portion of each propellant over a novel 3D-printed heat exchanger at the engine to pressurize the tanks. Excess flow can be diverted to the engine as needed. 

This approach reduces system mass, complexity and acquisition cost as well as operational costs. It eliminates the need for all high-pressure tanks and associated components. It can be used on any pressure-fed stage, for launch vehicle and in-space application when using high vapor pressure propellants such as LOX/methane or LOX/propane. As such, it is an enabler for missions targeted to use in-situ propellants since the need for a separate pressurant like helium is either greatly reduced or eliminated.  

By leveraging Vector’s ongoing commercially-funded Vector-R micro-launcher development, it is possible to reach TRL 6-ready system during Phase II and transition to the Vector-R operations (TRL-9) soon after.  

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
With the Vector-R micro-launcher, Vector is positioning itself to provide responsive, dedicated launch to the micro- and nanosat market expected to burgeon in the next few years. Candidate small spacecraft which could benefit from dedicated services or reduced launch costs provided by the technology include commercial entities operating constellations, such Planets (formerly known as Planet Labs) and Google's Terra Bella (formerly known as Skybox Imaging), as well as numerous other CubeSats and nanosats development efforts funded NSF, the Air Force, ORS and SMDC. Aggregators such as Spaceflight Industries would also benefit of the availability of dedicated, responsive launch for their numerous customers, particularly those targeting specific orbits or mission timelines

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology offers the means of drastically reducing the mass, complexity and cost of pressure-fed propulsion stages employing high vapor pressure propellants like LOX, methane, propylene and propane. The reductions in costs apply to both acquisition and operational costs of propulsive stages since the proposed system is simpler and lighter.

Applications include small launch vehicle stages where turbo-pumps are inefficient and cost-prohibitive. For Vector, the immediate application of the technology which will benefit NASA is the Vector-R launch vehicle. This vehicle is designed to provide dedicated launch services to nanosats up to 60 kg, with planned operations starting in July 2018. Candidate small spacecraft which could benefit from dedicated launch services or reduced launch costs provided by the technology include numerous CubeSats and nanosats in development at NASA or funded by NASA, such as NASA's CubeSat Launch Initiative and Educational Launch of Nanosatellites.

Longer-term potential applications include future missions to Mars and other bodies which use pressure-fed systems, whether directly or in conjunction with pump-fed engines. For Mars ascent, this technology is particularly attractive when using in-situ propellants since it eliminates the need for a pressurant like helium. The application of this technology for Mars missions is likely to be years away.

TECHNOLOGY TAXONOMY MAPPING (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.)
Fuels/Propellants
Launch Engine/Booster


PROPOSAL NUMBER:17-2 Z9.01-9883
PHASE-I CONTRACT NUMBER:NNX17CM64P
SUBTOPIC TITLE: Small Launch Vehicle Technologies and Demonstrations
PROPOSAL TITLE: Affordable Small Satellite Launch Vehicle Reaction Control System
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Valley Tech Systems, Inc.
160 Blue Ravine Road, Suite A
Folsom,CA 95630 -4718 (775) 473-5219
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Carlson
russ.carlson@vts-i.com
1170 Financial Blvd. Ste. 300
Reno ,NV 89502 -2384
(775) 473-5219

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Due to the rapid maturity of small satellite technologies to meet near term commercial, science and military space applications there is a driving need for development of increased affordable space launch system capability. To address this need, Valley Tech Systems is proposing a SBIR Phase II development of a new solid propulsion Reaction Control System (RCS) that leverages over 12 years and $12M of parallel MDA and USAF controllable solid propulsion missile interceptor and strategic deterrent propulsion technology investments. This new technology will replace older, heavier and less preforming Cold Gas ACS products providing NASA and future launch system providers with increased capability with improved affordability. Our solid RCS is applicable to both a future commercial booster flyout Attitude Control System (ACS) applications and future Post Boost Propulsion System (PBPS) payload delta-v and ACS providing increased satellite orbital insertion accuracies. The Phase II program will mature the new solid RCS technology to a TRL-6 ready for insertion into follow-on commercial launch system integration and flight testing. The result is a new affordable solid RCS that fills an identified critical technical gap for future affordable access to space.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The new Small Satellite Launch Vehicle technology is leveraging parallel DoD development efforts that is indirectly being applied to future MDA missile interceptor propulsion Divert and Attitude Control Systems (DACS) and booster ACS applications that yield ship board compatible capability with legacy liquid propulsion system like performance and impulse flexibility. In addition, the USAF is considering in-directly applying the technology to future Ground Based Strategic Deterrent (GBSD) Post Boost Propulsion and booster Roll Control System applications, taking advantage of inherent solid propellant affordability, safety, storability and compatibility with parallel Navy nuclear deterrent applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The new Small Satellite Launch Vehicle technology RCS has numerous direct applications including reaction control of launch booster and post boost payload control for small, medium and large satellite applications. In addition, the technology is indirectly applicable to future NASA applications such as: Mars lunar lander propulsion, Mars Ascent Vehicle Reaction Control System (MAV RCS), Hypersonic Inflatable Aerodynamic Decelerators (HIAD) gas generation, and Towed Glider Air-Launch System (TGALS) applications. Additionally, controllable solid thruster technology is indirectly applicable to future controlled gas generation application for power generation, long duration highly accurate satellite pointing/station keeping and liquid tank pressurization.

TECHNOLOGY TAXONOMY MAPPING (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.)
Maneuvering/Stationkeeping/Attitude Control Devices


PROPOSAL NUMBER:17-2 Z10.01-9245
PHASE-I CONTRACT NUMBER:NNX17CC75P
SUBTOPIC TITLE: Cryogenic Fluid Management
PROPOSAL TITLE: Multi-Environment MLI: Novel Multi-Functional Insulation for Mars Missions
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Quest Thermal Group
6452 Fig Street Unit A
Arvada,CO 80004 -1060 (303) 395-3100
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Dye
scott.dye@questthermal.com
6452 Fig St., Unit A
Arvada ,CO 80004 -1060
(303) 395-3100 Ext: 102

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Human exploration requires advances in cryogenic propellant storage for missions to Earth orbit, cis-lunar, Mars and beyond. NASA has need of new technology offering high performance insulation for Mars missions, including Mars LOX or LCH4 surface liquefaction and storage and Mars Lander/Ascent Vehicle. Quest Thermal Group has developed Multi-Environment MLI (MEMLI), a novel multi-functional thermal insulation system that uses a thin lightweight semi-rigid Vacuum Shell supported by Quest IMLI layers and spacers for low heat flux and optimized for Mars atmospheric pressure. 

Quest engineers designed, modeled, analyzed, fabricated and tested a novel multi-functional insulation capable of providing high thermal performance both in-space and on-Mars surface for Mars missions.  A thin metal semi-rigid vacuum shell is optimally supported by Quest IMLI spacers, providing low heat flux and low mass. 

A 10-layer MEMLI prototype provided low 0.19 W/m2 heat flux both in-vacuum and at 4.5 torr CO2 (105-210K), with a low mass of 1.5 kg/m2.  Multi-Environment MLI was successfully proven feasible, is at TRL4, and remains a strong candidate for NASA Mars surface liquefaction and Mars Lander needed new technology.

This Phase II program will continue developing MEMLI, with focus on further development of lightweight, supported Vacuum Shells for use on more real world tanks, development of flight-like hardware for vacuum control, increasing robustness and durability, and maturing the technology. 

Tasks in the Phase II program include validation of Mars mission requirements, Phase I review, updating structural and thermal models, continued development of very thin welded semi-rigid vacuum shells (down to 0.005” thick) studying their application, performance and durability for Mars missions. MEMLI will be built, installed and tested on larger, more complex cryogenic tanks for performance in all mission environments (in-air prelaunch, in-space cruise, and on-Mars surface).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Quest Thermal develops & promotes new technologies. IMLI will fly on GPIM, IMLI will fly on a RRM3 flight experiment, Quest is working with ULA on several new technologies for launch vehicles. Clearly, an insulation system designed for outstanding performance for Mars missions will have limited non-NASA use, although, perhaps SpaceX might benefit from this technology.

MEMLI provided good thermal performance and potentially provides new capabilities and benefits for launch vehicles and spacecraft, depending on their mission and requirements. MEMLI, for example, provides a lower heat flux than Spray On Foam Insulation, at near equal mass, with much greater robustness than SOFI.

Several aerospace prime contractors are now following with interest Quest and Ball Aerospace development of IMLI and related insulation systems. LRMLI (and variants such as CLRMLI or VCMLI) could significantly improve upper stage cryotank thermal insulation, reducing cryopropellant boiloff losses and increasing payload capacity for missions with long coasts. Use of high performance VCMLI to replace SOFI would improve payload capacity in cryogenic upper stages, such as Vulcan and SLS. ULA funded in 2016 a subcontract to Ball and Quest to do early development and testing of VCMLI, in hopes of using it on an upcoming Delta IV Heavy mission, NROL-44, where the VCMLI would reduce boiloff from the Delta Cryogenic Second Stage LH2 tank.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA has critical needs for improved cryogenic storage technology, including active and passive insulation. Mars missions have other demanding requirements, including the ability for low heat flux in Mars atmosphere, as well as during in-space travel, with durability and low mass. Quest designed, built, tested and demonstrated good performance from new Multi-Environment MLI (MEMLI) technology, which offers thin, lightweight vacuum shells supported by IMLI layers and spacers. MEMLI may offer one third to one half the heat flux of equal layers of conventional netting-MLI, with a thin 0.010? Al vacuum shell, and MEMLI may have one-third the mass of conventional MLI and conventional vacuum shell.

MEMLI, with equal heat flux in-space and on-Mars, and providing sufficient durability at low mass, is a strong candidate to insulate LOX or LCH4 storage tanks from Mars surface liquefaction activities, may prove useful for Mars Lander/Ascent Vehicle cryogenic management needs, and the thin vacuum shell offers better thermal performance in-air than SOFI, with a relatively durable metal vacuum shell, potentially offering new capabilities insulating launch vehicles.

Thin, lightweight vacuum shells may provide new capabilities and benefits for NASA space exploration missions and spacecraft.

TECHNOLOGY TAXONOMY MAPPING (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.)
Smart/Multifunctional Materials
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)
Fuels/Propellants
Cryogenic/Fluid Systems
Passive Systems


PROPOSAL NUMBER:17-2 Z10.02-8691
PHASE-I CONTRACT NUMBER:NNX17CJ37P
SUBTOPIC TITLE: Methane In-Space Propulsion
PROPOSAL TITLE: High Response Control Valve
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
WASK Engineering, Inc.
3905 Dividend Drive
Cameron Park,CA 95682 -7230 (530) 672-2795
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Wendel Burkhardt
wendel.burkhardt@waskengr.com
3905 Dividend Drive
Cameron Park ,CA 95682 -7230
(530) 672-2795 Ext: 105

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

WASK Engineering proposes to refine the design of an piezo actuated throttling valve fabricated in Phase 1 that has demonstrated the ability to open within 2.6 msec to meet the requirements of a 100 lbf RCS thruster.  This includes verifying the valve cycle life and valve leakage amounts.  Similar valves designed by WASK Engineering have operated for more than 2x109 cycles while maintaining a leakage rate of less than 1x10-3 sccm of He. The current valve design is configured to operate with cryogenic propellants and support the flow rates requried for a 100 lbf liquid oxygen/liquid methane thruster.  A piezo actuated valve has many benefits for RCS thrusters. The speed with which the valve can adjust its throttle position means that with two such valves the thruster propellant mixture ratio can be rapidly adjusted to prevent
hardware damage. The valves have the ability to continuously throttle over a range of thrust levels, allowing the thruster to operate from zero to full thrust. The piezo crystals use very little power, reducing the overall power consumption, again reducing weight.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The valve is applicable for propellant flow control to both cryogenic and non-cryogenic thrusters. We are already in discussions with a potential customer for application of the valve developed in the Phase 1 effort to gaseous RCS thrusters. The size, availability, reliability, low power consumption, and very high response rate are all features that have helped generate the interest in the valve. We are also examining the potential of increasing the flow rate through the valve to provide a wider range of applicability to the valve. These applications include the ability to act as a pressure and flow regulator, the ability to eliminate pressure regulators from a system due to the ability of the valve to throttle, and as a valve for cold gas thrusters where the rapid valve response allows the generation of very small impulse bits for precision control applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications include extremely durable, high-performance, low cost RCS systems for manned space flight to support high performance propulsion requirements such as orbit transfer, descent, ascent and pulsing attitude control. The ability to throttle makes the control very effective, as the impulse bit can be adjusted from large to very small depending on the immediate requirement. This has the benefit of simplifying the control system due to the very small minimum impulse bit possible. These valves can also be used as propellant valves for small monopropellant and bipropellant thrusters. This is especially the case if throttling is desired in the thrusters.

TECHNOLOGY TAXONOMY MAPPING (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.)
Actuators & Motors
Pressure & Vacuum Systems
Maneuvering/Stationkeeping/Attitude Control Devices
Cryogenic/Fluid Systems


PROPOSAL NUMBER:17-2 Z10.03-9105
PHASE-I CONTRACT NUMBER:NNX17CS17P
SUBTOPIC TITLE: Nuclear Thermal Propulsion (NTP)
PROPOSAL TITLE: Novel Sorbent to Remove Radioactive Halogens and Noble Gases from NTP Engine Exhaust
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TDA Research, Inc.
12345 West 52nd Avenue
Wheat Ridge,CO 80033 -1916 (303) 422-7819
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ambalavanan Jayaraman
krhodus@tda.com
12345 West 52nd Avenue
Wheat Ridge ,CO 80033 -1916
(303) 940-5391

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

Solid-core Nuclear Thermal Propulsion (NTP) has been identified as the advanced propulsion concept which could provide the fastest trip times with fewer Space Launch System (SLS) launches for human missions to Mars. Current environmental regulations require that radioactive halogens, noble gases, aerosols and particulates must be filtered out of NTP engine exhaust during ground testing. In Phase I, we demonstrated the ability of our sorbent to remove ppm levels of halogens and noble gases from helium at high space velocities over multiple regeneration cycles.

In this SBIR Phase II project, TDA Research, Inc. proposes to develop a novel scrubber that contains our high-capacity sorbent to remove of the radioactive halogens and noble gases from NTP engine exhaust, as part of NASA's larger exhaust treatment system. In Phase II, we will continue to optimize the sorbent formulation, scale up its production, and design and build a portable sub-scale unit to demonstrate its ability to selectively remove >99.5% radioactive halogens and noble gases under simulated NTP engine exhaust conditions. Based on the performance results, we will carry out a detailed design of the full-size scrubbing system for treating NTP engine exhaust and estimate its size, cost and energy requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There is a much larger commercial market for the sorbents developed here in spent nuclear fuel reprocessing facilities to control emissions of radioactive halogens and noble gases. Some of the radioisotopes that are recovered (such as iodine-131) are also important in nuclear medicine.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The sorbents developed in the Phase II will find use in scrubber systems for NTP engine exhaust during ground testing. Current environmental regulations require that radioactive halogens, noble gases, aerosols and particulates must be filtered out of NTP engine exhaust during ground testing to stay within safe limits. A high efficiency sorbent that removes radioactive halogens and noble gases (greater than 99.5%) is of specific interest to NASA.

TECHNOLOGY TAXONOMY MAPPING (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.)
Spacecraft Main Engine
Lifetime Testing


PROPOSAL NUMBER:17-2 Z11.01-9048
PHASE-I CONTRACT NUMBER:NNX17CL93P
SUBTOPIC TITLE: NDE Sensors
PROPOSAL TITLE: Millimeter-Wave Camera
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Texas Research Institute Austin, Inc.
9063 Bee Cave Road
Austin,TX 78733 -6201 (512) 263-2101
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Austin
raustin@tri-austin.com
9063 Bee Caves Road
Austin ,TX 78733 -6201
(512) 263-2101 Ext: 217

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The primary objective of this effort is to design and build a practical millimeter wave imaging system capable of effectively addressing a myriad of nondestructive inspection issues related to complex composites and structures during manufacturing and use.  The design of this imaging system will be founded on a long history and extensive experience by the proposing team facilitating and ensuring a successful outcome. The system is expected to be designed to:

i)operate in the frequency range of 30-40 GHz:

ii)have high-spatial and range resolutions in the few millimeter range rendering the system a 3D imager

iii)produce and render images in real-time,

iv)provide high system dynamic range for high detection sensitivity

v)small and portable for in-space applications,

vi)modular in design to accommodate large structures in terrestrial inspection applications while also suitable for in-space applications by personnel with varied technical skill-sets namely, technicians, engineers and astronauts.

The proposed work in this Phase II to develop, built and test a practical prototype imaging system builds on the Phase I design work.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed systems non-ionizing energy can rapidly image hidden weapons. It can image, in 3D, features hidden inside walls. This includes substructure, pipes, wiring, joists, fasteners, etc through drywall, paneling, siding, plywood and other common materials. It could also be used to detect and determine the extent of damage such as mold, water ingress, termites/carpenter ant nests, etc. A related application would be civil engineering such as inspecting FRP repairs to bridge decks and FRP wraps around concrete columns. In the petrochemical industry, the system could be used to image blockages, build-ups, and damage in fiberglass pipes, tanks and pressure vessels. Microwave testing is being commercialized in the petrochemical industry for inspecting fiberglass vessels. The proposed imaging innovation would greatly expand these capabilities. When a material being tested for radar performance fails radar testing, it is currently difficult to discern the location in the structure that caused failure. We are developing a tool to localize anomalies that caused far field range test failures in radomes. While effective, the tool is raster scanned over the radome. The imaging system proposed here would be a much faster way to localize regions for repair. The same tool could be used to determine if radar absorbers around antennas are functioning properly and to locate anomalies. It could also be used for radar absorbing/low observable coatings for the same purposes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The system proposed could be used to inspect: Thermal Protection Systems; High Temperature Reusable Surface Insulation; and Advanced Flexible Reusable Insulation. The proposed system would images these materials better and faster. Human Exploration Operations programs, e.g. crew transportation systems; ISS; Orion; deep space habitation; and Advanced Exploration Systems. The NASA/MSFC Meteoroid Environment Office (MEO) could use the system to determine location and depth of simulated micrometeoroids and orbital debris post impact testing. In-service, this capability could be used by people in space to determine the size and depth of debris and impact damage, allowing appropriate repairs. The camera could also be used to inspect multi-layer polymers, Nextel, ceramic fabrics etc such as those used in Whipple bumpers. While the camera cannot image through metal layers, such layers can act as reflectors and enhance imaging in materials above a metal layer. It could also be used to assess damage to the composite overwrap on pressure vessels. The system should be capable of imaging inside any dielectric material, including Kevlar fabrics, Kevlar/epoxy, fiberglass, and foams. The system could also be applied to inspection of more Earthbound applications within the Safety, Security and Mission Services/Construction & Environmental Compliance and Restoration programs. It could image composite, elastomer, polymeric, ceramic and civil materials for degradation.

TECHNOLOGY TAXONOMY MAPPING (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.)
Structures
Electromagnetic
Nondestructive Evaluation (NDE; NDT)
Diagnostics/Prognostics
Antennas
Condition Monitoring (see also Sensors)
Characterization
Quality/Reliability
3D Imaging


PROPOSAL NUMBER:17-2 Z11.02-9901
PHASE-I CONTRACT NUMBER:NNX17CL99P
SUBTOPIC TITLE: NDE Simulation and Analysis
PROPOSAL TITLE: Electromagnetic Characterization of Advanced Composites by Voxel-Based Inverse Methods
SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Victor Technologies, LLC
P.O. Box 7706
Bloomington,IN 47407 -7706 (812) 360-3645
PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Harold Sabbagh
has@sabbagh.com
P.O. Box 7706
Bloomington ,IN 47407 -7706
(812) 360-3645

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)

The nondestructive
characterization of advanced composites, such as
carbon-fiber reinforced polymers (cfrp), by electromagnetic means is
well established [6]-[24].  What is
needed to advance the state of the art are sophisticated inversion
algorithms that allow layup and impact damage to be determined in
localized regions, which means that the more traditional methods of
model-based inverse methods must be replaced by voxel-based methods.
Thus, one will be able to better distinguish such things as
delaminations from fiber-breakage due to impact damage, or other
parameters that
characterize the mechanical state of the cfrp structure, such as
elastic modulus and Poisson's ratio on a
voxel-by-voxel basis. This information can then be input to damage
evolution models.  We describe
two such methods, bilinear conjugate-gradients and set-theoretic
estimation.  The challenge is to extend these methods to anisotropic
materials.  We do that in this project, and will develop the
algorithms for inclusion
in our proprietary eddy-current code, \vic, during Phase II.
In addition, we continue our program of discovering and exploiting
parallelism in VIC-3D(R) to speed up the modeling and processing of
problems that involve massive data generation.

 

 

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are
35 commercial and university research institutions around the
world that own copies of VIC-3D(R) which they use for the same purposes as
NASA LaRC. They will have the same advantages with the enhanced
version of VIC-3D(R). Furthermore, aerospace companies, such as Boeing,
and SpaceX (Elon Musk),
that are developing vehicles that use advanced composites, such as
carbon-fiber reinforced polymers (cfrp) will be
able to use the enhanced version of VIC-3D(R). A more prosaic industry
that is using cfrp advanced composites in their vehicles is auto
racing, especially IndyCar. With a successful Phase II, we will be in
a better position to approach them and offer our services through VIC-3D(R) for
inspecting their cars. Composites are also being used in the
burgeoning wind-turbine industry, and, of course, in sporting
equipment, such as golf clubs and tennis rackets.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA LaRC already owns
a copy of VIC-3D(R) which it uses for modeling forward and inverse
problems in eddy-current NDE. With the enhancements proposed in this
project, NASA LaRC will be able to extend its modeling capability to
more accurately characterize damage conditions in cfrps, as well as
run large problems much more efficiently.

TECHNOLOGY TAXONOMY MAPPING (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.)
Composites
Nanomaterials
Nondestructive Evaluation (NDE; NDT)
Simulation & Modeling
Characterization
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Data Modeling (see also Testing & Evaluation)


ADDITIONAL SELECTIONS


PROPOSAL NUMBER: 17-2 A3.02-8740
PHASE 1 CONTRACT NUMBER: NNX17CL55P
SUBTOPIC TITLE: Autonomy of the National Airspace Systems (NAS)
PROPOSAL TITLE: Selecting Days for Concept and Technology Evaluation in SMART-NAS Test-Bed Scenario Generation

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Crown Consulting, Inc.
1400 Key Boulevard
Arlington, VA 22209 - 1577
(703) 650-0663

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Thomas Joseph Davis
tdavis@crownci.com
210 Livingstone Drive
Cary, NC 27513 - 2914
(703) 203-7221

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Timothy Joseph Nolan
tnolan@crownci.com
15 Legend Circle
Dillon, CO 80435 - 1577
(767) 767-3913

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

Technology Available (TAV) Subtopics
Autonomy of the National Airspace Systems (NAS) is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Crown Consulting, Inc. (CCI) will investigate and demonstrate methods to enable rapid selection of days for scenario generation in the development and evaluation of Air Traffic Management (ATM) concepts and technologies (C&T) in the NASA developed Shadow Mode Assessment using Realistic Technologies for the National Airspace System (SMART-NAS) Testbed (SNTB). The proposed capability will enable the rapid generation of highly operationally relevant scenarios for use in the development and evaluation of technology demonstrators such as the NASA Airspace Technology Demonstrator (ATD)-2 and ATD-3, as well as future ATM concepts such as Unmanned Aerial System (UAS) Traffic Management (UTM), and Air Traffic Management Exploration (ATM-X). The latter includes new mid-term operational concepts such as Integrated Demand Management (IDM), and far-term operational concepts such as Urban Air Mobility (UAM) and Increasingly Diverse Operations (IDO), which considers the integration of supersonic aircraft, spacecraft and UAS into the National Airspace System (NAS)

 

The proposed innovation seeks to augment the scenario generation capability of NASA’s SNTB with methods and tools for selecting traffic, winds and weather based on the needs of the experiment allowing for highly operationally relevant scenarios. These methods and tools would actively categorize incoming and historical data using advanced machine-learning algorithms, allowing fast access to NAS streaming and legacy data in a big-data warehouse such as the NASA’s ATM-Data-Warehouse through queries generated via a simple user interface for specifying desired characteristics. In addition to historical data, processed data such as benefit metrics, generated by SNTB simulations implementing the concept and technology of interest, can also be categorized by machine-learning algorithms for selecting days to generate scenarios for HITL tests to verify conditions for most or least C&T benefit.   

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed innovation seeks to overcome the current limitation of being able to select a few relevant scenario days by providing NASA with an automated way for identifying days of interest based on high-level characteristics specified by the user. This will directly lead to better scenario generation for development, integration, benefit assessment and operational feasibility evaluation via HITL simulations of near term ATM technology, such as the:
* Airspace Technology Demonstrators(ATDs): Integrated Arrival/Departure/Surface (IADS), Metroplex Traffic Management (ATD-2) and Applied Traffic Flow Management (ATFM) (ATD-3),
* Integrated Demand Management
* UTM, UAS in the NAS, Urban Air Mobility

This will allow Crown to easily provide advanced software components that will directly assist and enhance these ATM research projects. In addition, this software can be applied to other NASA Big Data systems for providing the same capabilities for space and autonomy research.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Potential customers for this innovation include:
* Government, industry, and academia researchers exploring new operational concepts for the NAS.
* FAA offices involved in development, verification, validation and approval of new concepts or procedures.
* Flight operators involved in the development, verification and validation, and implementation of Airline Operation Center (AOC) based tools to support new or existing operational concepts.
* Industry, including suppliers of decision support tools and software for the FAA and flight operators, involved in the development, verification and validation, and implementation of decision support tools and software to support new or existing operational concepts.
* Other government agencies and industries with the need to extract specific types of data from large, diverse datasets based on complex combinations of the raw data, but using well defined queries.

TECHNOLOGY TAXONOMY MAPPING (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.)
Air Transportation & Safety
Analytical Methods
Data Modeling (see also Testing & Evaluation)
Data Processing
Knowledge Management
Software Tools (Analysis, Design)

PROPOSAL NUMBER: 17-2 A3.02-9118
PHASE 1 CONTRACT NUMBER: NNX17CA58P
SUBTOPIC TITLE: Autonomy of the National Airspace Systems (NAS)
PROPOSAL TITLE: Machine Learning of Multi-Modal Influences on Airport Delays

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
The Innovation Laboratory, Inc.
2360 Southwest Chelmsford Avenue
Portland, OR 97201 - 2265
(503) 242-1761

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Jimmy Krozel
Jimmy.Krozel@gmail.com
2360 SW Chelmsford Ave.
Portland, OR 97201 - 2265
(503) 224-5856

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Michelle Camarda
Michelle.Camarda@gmail.com
2360 Southwest Chelmsford Avenue
Portland, OR 97201 - 2265
(503) 242-1761

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

Technology Available (TAV) Subtopics
Autonomy of the National Airspace Systems (NAS) is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

This SBIR system is a machine learning system that uses a very large database of airside and landside data to predict pushback and takeoff times of aircraft at a given airport.  Airside data sources describe the state of the system after TSA security screening is complete, and includes information about the crew and passengers arriving at the departure gate, turnaround and pushback preparation, ramp and taxiway movement, and aircraft arrival to and departure from the gates.  Landside data sources describe the state of the airport prior to TSA screening, including TSA queue line delays, passenger movement through the airport via cameras, parking availability, road transit delays, congestion, and accidents, and weather conditions. These data are used to classify the current day data using cluster analysis, and take off time and pushback time predictions are made based on the cluster analysis results.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
This work is fundamental to Air Traffic Management (ATM), and will naturally fit into ATM research being performed at NASA Ames and NASA Langley. It will likely be used in ATM research efforts, Trajectory-Based Operations (TBO) research, and in the SMART NAS system under development at NASA.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Based on a partnership with Metron Aviation, plans are to include this SBIR software into products and services that Metron Aviation sells in the National Airspace System (NAS) as well as throughout the world.

TECHNOLOGY TAXONOMY MAPPING (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.)
Air Transportation & Safety
Algorithms/Control Software & Systems (see also Autonomous Systems)
Analytical Methods
Condition Monitoring (see also Sensors)

PROPOSAL NUMBER: 17-2 H7.02-9710
PHASE 1 CONTRACT NUMBER: NNX17CM58P
SUBTOPIC TITLE: In-Space Manufacturing of Precision Parts
PROPOSAL TITLE: Metal Advanced Manufacturing Bot-Assisted Assembly (MAMBA) Process

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Tethers Unlimited, Inc.
11711 North Creek Parkway South, Suite D113
Bothell, WA 98011 - 8808
(425) 486-0100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Rachel Muhlbauer
muhlbauer@tethers.com
11711 North Creek Parkway South, Suite D113
Bothell, WA 98011 - 8808
(425) 486-0100 Extension :267

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Robert Hoyt
hoyt@tethers.com
11711 North Creek Parkway South, Suite D113
Bothell, WA 98011 - 8808
(425) 486-0100

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

Technology Available (TAV) Subtopics
In-Space Manufacturing of Precision Parts is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Tethers Unlimited, Inc. (TUI) proposes to develop the Metal Advanced Manufacturing Bot-Assisted Assembly (MAMBA) Process, a robotically managed metal press and milling system used to create precision parts on orbit.  This manufacturing process provides an alternative to 3D printing metals in space, which is difficult due to space environment, feedstock safety concerns, and print quality issues.  Instead, the MAMBA-Process relies on an ingot forming technology to create a metal ingot.  This ingot can then be milled and machined to form a precision part using a standard CNC milling technique.  In order to minimize astronaut time and exposure to the process, the MAMBA-Process will be highly automated and outfitted with a robotic assistant, capable of removing the ingot from the press and placing the ingot in the mill.  Automated tool changes are also possible for the mill, enabling complex shapes with fine edge finishes.  Testing of the process technologies led to a lab demonstration of ingot formation and milling in the Phase I effort, maturing the MAMBA Process to TRL-3.  In the Phase II effort, a full scale engineering unit will be built and tested, maturing the various the payload subsystems to TRL-5 and preparing the work needed to validate this technology for flight.   

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The innovations proposed in the MAMBA-Process would allow NASA to create precision parts on-orbit as needed. Rather than fly a storage room of potential spare parts, the MAMBA-Process could be used to make these components when a need arises, limiting the initial launch volume. In addition, the acceptance of used parts into the Positrusion-Press sub-technology allows for the recycling of used or failed parts, minimizes stored waste, and enables a closed loop ecosystem for metal fabrication. The ability to re-use mass taken on mission, dependent on the mission stage, would greatly increase capability per budgeted mass. In addition, the MAMBA-Process would enable the flexibility to replace critical components when resupply is impossible or improbable.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The MAMBA-Process was designed specifically for in-space use, which limits a traditional terrestrial commercial pathway. Similar to NASA, the MAMBA-Process technologies could be used by any commercial spaceflight companies with a focus on manned space travel. It also could be used in commercial space labs, such as the one currently under development by Bigelow Aerospace. Additionally, this type of process would have utility aboard submarines where resupply is similarly limited.

TECHNOLOGY TAXONOMY MAPPING (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.)
In Situ Manufacturing
Metallics

PROPOSAL NUMBER: 17-2 H8.01-8465
PHASE 1 CONTRACT NUMBER: NNX17CL63P
SUBTOPIC TITLE: ISS Utilization and Microgravity Research
PROPOSAL TITLE: Evaluation of Multifunctional Radiation Shielding Material Against Long Duration Space Environment - Utilization of MISSE-FF

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Geoplasma, LLC
6703 Odyssey Drive, Northwest Suite 304
Huntsville, AL 35806 - 3308
(256) 489-4748

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. John Scott O'Dell
scottodell@plasmapros.com
4914 Moores Mill Road
Huntsville, AL 35811 - 1558
(256) 851-7653 Extension :104

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Timothy Neal McKechnie
timmck@plasmapros.com
4914 Moores Mill Road
Huntsville, AL 35811 - 1558
(256) 851-7653 Extension :103

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

Technology Available (TAV) Subtopics
ISS Utilization and Microgravity Research is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

NASA’s vision for space exploration includes long duration human travel beyond Low Earth Orbit (LEO) and sustained human presence on other planetary surfaces. For this vision to be a reality, one of the major challenges is to minimize radiation exposure to the crew and equipment. A material based solution typically results in paying a penalty due to additional weight. During this effort, a multifunctional composite is being developed as an integral part of a spacecraft or habitat to provide shielding against Galactic Cosmic Rays (GCRs) and secondary particles, enhanced structural integrity, and durability against overall space environment. During Phase 1, innovative fabrication methods have been developed to produce the radiation shielding composite.  Mechanical testing showed that compared to traditional aerospace aluminum alloys significant enhancements in specific strength and stiffness were obtained. During Phase 2, the composite will be optimized and samples will be produced for testing.  A primary task will be to use the MISSE-FF facility to test the composite against the combined space environment. Samples tested on ground for mechanical and radiation properties will be compared to samples tested on LEO to unambiguously demonstrate the multifunctionality of the composite.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Potential NASA applications for this technology include structural radiation shielding for the protection of humans and electronics in aerospace and space vehicles, space structures, such as stations, orbiters, landing vehicles, rovers, habitats, and nuclear propulsion. Potential customers include Boeing, Orbital-ATK, Lockheed, SpaceX, Bigelow Aerospace, and other NASA contractors.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
In addition to NASA, the technologies can be leveraged across broad government and commercial applications including radiation shielding (particle accelerators, nuclear reactors, radioactive waste containment, satellite hardware, high-altitude airliners, medical patient shielding), electromagnetic pulse protection, sensors for neutron detection, and advanced nanoscale ceramic particles and tubes for composite reinforcement.

TECHNOLOGY TAXONOMY MAPPING (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.)
Ceramics
Coatings/Surface Treatments
Composites
Isolation/Protection/Radiation Shielding (see also Mechanical Systems)
Isolation/Protection/Shielding (Acoustic, Ballistic, Dust, Radiation, Thermal)
Nanomaterials
Polymers
Smart/Multifunctional Materials
Structures

PROPOSAL NUMBER: 17-2 S1.04-9289
PHASE 1 CONTRACT NUMBER: NNX17CG56P
SUBTOPIC TITLE: Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter
PROPOSAL TITLE: Type-II Superlattice Based Low Dark Current Short-Wavelength Infrared Photodetectors With Optical Response From 0.4 to 2.5um

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
NOUR, LLC
1500 Sheridan Road, - 8A
Wilmette, IL 60091 - 1880
(847) 491-7251

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Abbas Haddadi
ahaddadi1984@gmail.com
1801 Maple AVE, SUITE 8A
Evanston, IL 60201 - 3149
(847) 491-7208

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Manijeh Razeghi
NOURRazeghi@yahoo.com
1500 Sheridan Road, Unit 8A
Wilmette, IL 60091 - 1880
(847) 491-7251

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

Technology Available (TAV) Subtopics
Sensor and Detector Technology for Visible, IR, Far IR and Submillimeter is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

In recent years, Type-II superlattices have experienced significant development. However, the full potential of Type-II superlattice has not been fully explored and alternate superlattice architectures hold great promise. Despite demonstration of SWIR photodetectors based on this material system, there has been no report about Type-II superlattice-based photodetectors that have been sensitive to visible light. We propose to develop Type-II superlattice-based photodetectors and focal plane arrays for NASA's imaging and spectroscopy applications in the spectral band from visible to extended short-wavelength infrared (0.4–2.5 um) with a very low dark current density. In mid- and long-wavelength infrared spectral bands, Type-II superlattice-based photodetectors already offers performance comparable to the state-of-the-art mercury cadmium telluride but at a fraction of the cost due to the leveraging of commercial growth and process equipment. Our goal is to extend that benefit into the short-wavelength infrared. Using the best material currently available and a novel bandgap-engineering design and process, we will fabricate photodetectors and, ultimately, focal plane arrays.

In Phase I, we are going to demonstrate photodetector designs based on Type-II superlattices, which can cover spectral range between 0.4 to 2.5 um with a very low dark current density (<10^(-11) A/cm2) at temperatures below 100 K.. In Phase II, we are going to continue reduction of the dark current density to <10^(-13) A/cm2-level at temperatures below 100K. Then, we will use the optimized device design to develop and deliver 1K×1K imagers to NASA for planetary sciences.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Visible-SWIR photodetectors are of special interest to NASA for planetary observation missions. The Visible-SWIR imagers can be used to study the world's ecosystems and provide critical information on natural disasters such as volcanoes, wildfires and drought. Visible-SWIR imaging will be able to identify the type of vegetation that is present and whether the vegetation is healthy. It can provide a benchmark on the state of the worlds ecosystems against which future changes can be assessed. Moreover this imaging method can assess the pre-eruptive behavior of volcanoes and the likelihood of future eruptions as well as the carbon and other gases released from wildfires. The data from Visible-SWIR imagers can be used for a wide variety of studies primarily in the Carbon Cycle and Ecosystem and Earth Surface and Interior focus areas.

The large-format Visible-SWIR cameras, with ultra-low dark current, we will be developing and delivering in Phase II of this program will be able to provide high resolution mapping of planetary bodies.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The key applications of visible-SWIR imaging are listed below:
* Mineral exploration, resource management, and environmental monitoring.
* In agriculture for monitoring the development and health of crops.
* In geology for rapidly mapping nearly all minerals of commercial interest
* For ecology, surveillance, and historical manuscript research
* For research in areas such as nano-drug delivery and nano-toxicology
* For use in many research areas, such as vegetation research, forensics, life sciences, food analysis, and mineral research.
* FTIR imaging microscopy
* Gas imaging (e.g. for the petrochemical industry)
* Security and surveillance (day and night)
* Missile defense
* Space-based situational awareness
The development of high-performance visible-SWIR imagers based on Type-II superlattices has the potential to eliminate the need for expensive mercury-cadmium-telluride materials and thus the potential to significantly reduce the operational cost of these sensors and thus potentially open up new lower cost commercial applications.

TECHNOLOGY TAXONOMY MAPPING (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.)
Detectors (see also Sensors)
Infrared
Materials & Structures (including Optoelectronics)
Materials (Insulator, Semiconductor, Substrate)
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)
Multispectral/Hyperspectral
Optical/Photonic (see also Photonics)
Telescope Arrays
Thermal Imaging (see also Testing & Evaluation)
Visible

PROPOSAL NUMBER: 17-2 S2.01-8266
PHASE 1 CONTRACT NUMBER: NNX17CG48P
SUBTOPIC TITLE: Proximity Glare Suppression for Astronomical Coronagraphy
PROPOSAL TITLE: Proximity Glare Suppression using Carbon Nanotubes

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Lambda Consulting/Advanced Nanophotonics
4437 Windsor Farm Road
Harwood, MD 20776 - 2200
(240) 678-9475

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. John Hagopian
J_Hagopian@comcast.net
4437 Windsor Farm Road
Harwood, MD 20776 - 2200
(240) 678-9475

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. John Hagopian
J_Hagopian@comcast.net
4437 Windsor Farm Road
Harwood, MD 20776 - 2200
(240) 678-9475

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

Technology Available (TAV) Subtopics
Proximity Glare Suppression for Astronomical Coronagraphy is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

In Phase I we demonstrated each aspect required for design and fabrication of Lyot Stops and Apodization Masks for use in a coronagraphic instrument and delivered working components to collaborators at NASA and the Space Telescope Science Institute for evaluation.  The technical achievements included: 1) first high quality mirror with carbon nanotubes 2) First nanotubes grown on metallic coatings  3) Dark patterned carbon nanotubes  with micron-scaled features.   During Phase II we will work with the NASA and STScI collaborators to determine how to improve these components and deliver second generation components to extend the performance of the STScI test bed in support of implementation on future NASA missions such as HABEX or UVOIRS.  In addition we will work with NASA collaborators to design and fabricate carbon nanotube coated Lyot Stops for the Visible Nulling Coronagraph (VNC) test bed, also of key importance to the decadal missions referenced above.  Lastly, we plan to collaborate with the LISA telescope team at NASA GSFC to design and fabricate a carbon nanotube apodization mask on a powered secondary mirror that could be used in single crystal silicon telescope as a pathfinder for LISA.  One of the technical goals of Phase II are to pattern more complex Lyot Stop geometries while maintaining geometrical accuracy through the nanotube growth process.  Further optimization of the apodization masks for coronagrahic use include: 1) increasing the metallic coating reflectance to near ideal  2)  optimization of the nanotube darkness on the metallic coatings 3) greyscale patterning of carbon nanotubes and medium reflectance coatings on the mirrors to achieve enhanced diffraction suppression.  For the LISA telescope diffraction spoiler application we will demonstrate patterning and growth of carbon nanotubes at the micron scale which when combined with metallic nanostructures can provide enhanced field suppression; another enabling technology to NASA missions. 

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Stray-light and diffraction suppression is critical to NASA instrumentation because it improves signal to noise and observational efficiency in high contrast regions present in Earth, solar and coronagraphic applications. The PI and ANP/LC have delivered a large variety of instrument components including, baffles, stops, tubes and beam dumps. Development of a process compatible with reflective coatings and high quality optics for this SBIR, will enable an entirely new class of components and instrumentation for scientific observations. NASA requires calibrators for all manner of instruments to allow scientific data to be of the highest accuracy. On-mirror diffraction suppression is enabling for e-LISA as the telescope is used in duplex and requires extreme suppression of the the high power transmitted beam. This is also a challenge in Laser Communications and of great interest to NASA that will be addressed by this SBIR. Carbon nanotubes have the highest emissivity ever measured and arenearly ideal in this respect. We expect that further enhancement of the rob ustness of carbon nanotube coatings demonstrated in this SBIR will result in the use of this technology on more NASA instruments. The PI has built and tested carbon nanotube absorber thermal detectors with superconducting transition edge detectors; a modified CVD process will make the use of carbon nanotube absorbers compatible with more detector technologies.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
During Phase I of this SBIR we developed coatings and chemical vapor deposition processes compatible with high surface quality single crystal silicon mirrors. Phase II will continue optimization of these optical components for NASA and commercial use. We believe that this technology can be applied to autonomous vehicle imaging where stringent stray light control is required to enable robust operation in challenging lighting conditions. In addition, success during Phase I has initiated collaborative efforts with the Swatch group, who are interested in patterning nanotubes on gold or silver coated substrates for high end watches. Advanced Nanophotonics, Inc. is also collaborating with the technical arm of Universal Studios to deliver samples of ultradark nanotube coatings for use in special effects.

TECHNOLOGY TAXONOMY MAPPING (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.)
Image Capture (Stills/Motion)
Infrared
Lasers (Communication)
Mirrors
Nanomaterials
Optical
Radiometric
Spacecraft Instrumentation & Astrionics (see also Communications; Control & Monitoring; Information Systems)
Transmitters/Receivers
Visible

PROPOSAL NUMBER: 17-2 S2.04-8778
PHASE 1 CONTRACT NUMBER: NNX17CG28P
SUBTOPIC TITLE: X-Ray Mirror Systems Technology, Coating Technology for X-Ray-UV-OIR, and Free-Form Optics
PROPOSAL TITLE: Pyramid Nanostructured Coatings for Stray Light Suppression

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Applied Sciences, Inc.
141 West Xenia Avenue
Cedarville, OH 45314 - 0579
(937) 766-2020

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Carla Leer Lake
cleer@apsci.com
141 West Xenia Avenue
Cedarville, OH 45314 - 0579
(937) 766-2020 Extension :134

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mrs. Marty Rochon
rochon@apsci.com
141 West Xenia Avenue
Cedarville, OH 45314 - 0579
(937) 766-2020 Extension :100

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

Technology Available (TAV) Subtopics
X-Ray Mirror Systems Technology, Coating Technology for X-Ray-UV-OIR, and Free-Form Optics is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Vertical arrays of carbon nanotubes have been shown to yield values as low as 0.1 % of total hemispherical reflectance, while this improvement would afford significant gains for in-space telescopic imagery, the complexities and cost with fabrication pose significant barriers to capturing this level of stray light suppression.  The current work is directed to capturing the same or comparable levels of reflectance, with SCCNT coating which can be applied at room temperature using conventional spray-up method onto flat and curved objects.  Applied Sciences SCCNT coatings demonstrated a total hemispherical reflectance of 1%, 5x better than the legacy material – Z306, in Phase I. The proposed innovation seeks the development of practical and affordable SCCNT coatings into an aerospace qualified polymer for stray light suppression. In Phase II, the cost and simplicity of this approach will be exploited to optimize reflectance over the desired spectral range. The SCCNT can be tuned for absorption/scattering over a broad spectral region by altering the geometry and functionality, allowing degrees of freedom in optimizing absorption.  Additionally, a novel method of graphene growth on SCCNF offers further enhancement of absorption of stray light, at low cost and ease of application. This new approach comes at a much lower cost, is readily scalable and safer than the competing technology.

 

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed technology is aimed for stray light suppression in spaceflight instruments. The proposed technology could find application on the following missions/telescopes: LUVOIR LISA. On components such as masks, baffles, entrance aperture and stops.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed innovation comes at a much lower cost than the current state of the art, and is readily scalable. Commercial applications include optical apertures, binoculars, night vison goggles, analytical instrumentation and other devices that benefit from stray light suppression.

TECHNOLOGY TAXONOMY MAPPING (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.)
Coatings/Surface Treatments
Mirrors
Nanomaterials
Optical
Polymers
Smart/Multifunctional Materials
Telescope Arrays
Visible

PROPOSAL NUMBER: 17-2 S3.02-9418
PHASE 1 CONTRACT NUMBER: NNX17CM51P
SUBTOPIC TITLE: Propulsion Systems for Robotic Science Missions
PROPOSAL TITLE: Trussed TRAC Boom for Solar Sails

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
ROCCOR, LLC
2602 Clover Basin Drive, Suite D
Longmont, CO 80503 - 7555
(720) 200-0068

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dana Turse
dana.turse@roccor.com
2602 Clover Basin Drive, Suite D
Longmont, CO 80503 - 7555
(303) 909-7649

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Stephanie Amend
stephanie.amend@roccor.com
2602 Clover Basin Drive, Suite D
Longmont, CO 80503 - 7555
(801) 710-1252

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

Technology Available (TAV) Subtopics
Propulsion Systems for Robotic Science Missions is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

In response to NASA’s need for 1,000m2-10,000m2 class solar sails for future exploration missions, Roccor is developing the composite Trussed TRAC (T-TRAC) Boom system. Like the original TRAC boom to be flight validated on the upcoming NEA (Near-Earth Asteroid) Scout mission (McNutt, et al [2014]), T-TRAC has a triangular cross-section that flattens and rolls around a spool for packaging.  Unlike the original TRAC, T-TRAC is applicable to much larger scale sail systems.  The proposed T-TRAC boom is advancing TRAC technology through: 1) scaling up the cross-section size and length of the boom, 2) light weighting the boom through material re-distribution and removal, and 3) cross-section geometric modification and closing. Preliminary analyses indicate these steps will achieve more than a 5X increase in TRAC Boom structural mass efficiency over recently developed high strain composite (HSC) TRAC Booms, while maintaining an extremely compact roll stowed configuration that leverages the solar sail mechanical design heritage established with the recent Nanosail D (Alhorn, et al [2011]) and upcoming NEA Scout TRAC-deployed sail systems.

The overarching Phase II objective is to further develop and mature the T-TRAC technology such that it can be considered for NASA’s future mid-sized solar sail missions.  Multi-scale micro-mechanics, laminate, cross-section, and full section analyses will be performed to optimize laminate architecture and TRAC geometry.  The Phase II effort will culminate in the design, production and demonstration of a four-boom T-TRAC deployment system.  

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
*Mid-scale (1,000-10,000m2) solar sails
*Large-scale (>100kW) solar arrays for solar electric propulsion

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
*Commercial roll-out solar arrays

TECHNOLOGY TAXONOMY MAPPING (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.)
Actuators & Motors
Characterization
Composites
Deployment
Models & Simulations (see also Testing & Evaluation)
Polymers
Prototyping
Simulation & Modeling
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Structures

PROPOSAL NUMBER: 17-2 S3.04-9783
PHASE 1 CONTRACT NUMBER: NNX17CG21P
SUBTOPIC TITLE: Guidance, Navigation and Control
PROPOSAL TITLE: Cislunar Autonomous Positioning System (CAPS)

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Space, LLC
2100 Central Avenue Suite 102
Boulder, CO 80301 - 3783
(720) 545-9191

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Jeffrey Parker
parker@advancedspace.com
2100 Central Ave Suite 102
Boulder, CO 80301 - 3783
(720) 545-9191

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Bradley Cheetham
cheetham@advancedspace.com
2100 Central Avenue Suite 102
Boulder, CO 80301 - 3783
(720) 545-9189

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

Technology Available (TAV) Subtopics
Guidance, Navigation and Control is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Future missions operated by NASA, commercial entities, and international agencies will face increasing congestion due to limited communication and navigation infrastructure. To address this potential bottleneck, Advanced Space proposes to continue developing a high-impact navigation technology that will enable future missions. Specifically, the proposed effort will further develop capabilities to enable autonomous onboard flight navigation that incorporates spaceborne and ground-based measurements. The Cislunar Autonomous Positioning System (CAPS) will use the existing flight radio, antenna, attitude determination and control, and other subsystems of the spacecraft to provide the host spacecraft with an autonomously generated absolute position estimate. CAPS is a peer-to-peer navigation solution that is a self-sustaining, scalable, and evolvable innovation that operationalizes and leverages investments made in algorithms, flight computers, and radios over the past decade. CAPS can be thought of as a subsystem of a host spacecraft that can process inter-spacecraft range and range-rate measurements between multiple spacecraft in cislunar space to determine absolute position estimates for all participating spacecraft. The focus of the proposed effort is to design and develop key software components that will prepare CAPS for flight demonstrations and ultimately broad adoption by future missions to the lunar vicinity.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
There are many potential customers for CAPS. Applications that benefit NASA are the first priority. These missions include missions such as Orion EM-1, Lunar Flashlight, Lunar Ice Cube, LunaH-Map, Skyfire, Orion EM-2-5, Deep Space Gateway Power and Propulsion Element, Deep Space Gateway Habitat, Resource Prospector, and MoonRise to name a subset. Ultimately any mission operating in orbit around or on the surface of the Moon would be a potential key customer. Notably, missions that include distributed scientific sensing platforms would particularly benefit from the capability that CAPS would deliver.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Other potential customers for CAPS include commercial companies such as lander and orbiter activities. Further market opportunities are expected in support of international customers. A convergence of science and exploration missions at or around the Moon is expected in the coming years, which will be accompanied by numerous commercial and international missions. In all of these cases demand for tracking and navigation services will be stressed. The addition of small satellite explorers and the potential for long-duration habitats and reusable in-space stages all compound the need and result in a robust market opportunity.

TECHNOLOGY TAXONOMY MAPPING (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.)
Autonomous Control (see also Control & Monitoring)
Ranging/Tracking
Simulation & Modeling
Verification/Validation Tools

PROPOSAL NUMBER: 17-2 S4.01-9312
PHASE 1 CONTRACT NUMBER: NNX17CS52P
SUBTOPIC TITLE: Planetary Entry, Descent and Landing and Small Body Proximity Operation Technology
PROPOSAL TITLE: Non-mechanical High-Resolution Low-SWaP Lidar

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)
Steve Serati
sserati@bnonlinear.com
Boulder Nonlinear Systems, Inc.
Lafayette, CO 80026 - 8878
(303) 604-0077

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Mark Tanner
mtanner@bnonlinear.com
450 Courtney Way, Unit 107
Lafayette, CO 80026 - 8878
(303) 604-0077

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

Technology Available (TAV) Subtopics
Planetary Entry, Descent and Landing and Small Body Proximity Operation Technology is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

This Phase II effort will be a proof-of-concept demonstration of a non-mechanical (no moving parts) 3D lidar system that provides in real time high-resolution terrain point cloud information.    The objective is to build a compact sensor that meets the low size, weight and power (SWaP) requirements of planetary landers being developed for future NASA planet, moon and asteroid exploration.   The lidar sensor will provide 5cm by 5cm by 5cm resolution over a 30-degree by 30-degree field of regard at a standoff distance of 1 km or more.  This will be accomplished using a unique electro-optic scanner that provides the largest angle-aperture product of any commercially-available non-mechanical scanning technology. 

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed low-SWaP lidar will have application in many NASA missions needing real-time 3D information such as fixing and refueling space craft, close approaches to asteroids, autonomous vision-based guidance and control for robotic systems and terrain mapping and hazard avoidance for autonomous land, air and sea vehicles.
The technology developed in this project, especially the versatile non-mechanical beam scanning system, can be also tailored for other NASA sensor platforms such as coherent Doppler lidar for 3D wind sensing or differential absorption lidar (DIAL) for trace gas detection. Also, a reliable, low-SWaP gimbal replacement would also be useful for several other space-borne applications including active remote sensing using laser-based sensors, satellite-to-satellite communication, and position tracking within a cluster of nano-satellites, to name a few.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The proposed non-mechanical beam steering technology married with lidar sensors have numerous commercial applications. The platform can provide a low-SWaP package for hazard/collision avoidance for autonomous automobiles and unmanned vehicles, which is currently is gathering a lot of interest in the commercial sector. Other potential large markets are 3D imaging for autonomous robotics (factory automation), noncontact structure analysis, topographical mapping and gesture recognition for augmented reality systems.

Additionally, the non-mechanical scanner technology is well suited to deployment on wind farms for guiding and controlling power-generating wind turbines. The sensor is particularly well suited for this application because the low-SWaP package is ideal for mounting directly to a turbine or even packaging in an ocean-going buoy for sea-based wind farms. Such a buoy network would also have weather warning and prediction applications. Within the Department of Defense, this technology is being developed for applications such as munitions seeker tracking, passive imaging, and conventional hard-target lidar. Also, there is interest from automotive manufacturers who wish to use the technology for non-mechanical headlight steering.

TECHNOLOGY TAXONOMY MAPPING (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.)
3D Imaging
Entry, Descent, & Landing (see also Planetary Navigation, Tracking, & Telemetry)
Lasers (Ladar/Lidar)
Lasers (Weapons)
Optical
Optical/Photonic (see also Photonics)
Robotics (see also Control & Monitoring; Sensors)

PROPOSAL NUMBER: 17-2 S4.02-9202
PHASE 1 CONTRACT NUMBER: NNX17CP50P
SUBTOPIC TITLE: Robotic Mobility, Manipulation and Sampling
PROPOSAL TITLE: Extended Length Marsupial Rover Sensing Tether

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Luna Innovations, Inc.
301 1st Street Southwest, Suite 200
Roanoke, VA 24016 - 1921
(540) 769-8400

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Emily Templeton
submissions301@lunainc.com
3155 State Street
Blacksburg, VA 24060 - 6604
(540) 753-4259

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael E Pruzan
pruzanm@lunainc.com
301 1st Street Southwest, Suite 200
Roanoke, VA 24016 - 1921
(540) 769-8430

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

Technology Available (TAV) Subtopics
Robotic Mobility, Manipulation and Sampling is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Luna proposes to continue the development of extended length capabilities for its marsupial rover sensing tether (MaRS Tether).  Luna’s revolutionary technology measures the distributed tension and curvature of a tether that connects a rover to its base station and can identify pinch points, snags, or high tension. Previous SBIR programs with NASA JPL have demonstrated the capabilities of a 50m tether to identify a snag location with JPL’s Axel Rover, and proved the feasibility of future miniaturization of the tether’s acquisition system.  During this multiphase effort, Luna is building upon these successes to extend the sensing length to 1000m, to enable NASA to pursue more complex exploration missions, such as navigating a large crater to study features on the crater wall. During Phase I, Luna demonstrated the feasibility of sensing tension up to 800m, and curvature up to 400m, and added a spot scan mode to enable fast update rates over a short section of the tether.  In addition to increasing the sensing length for curvature measurements, during this Phase II Luna will increase the system robustness and deliver a prototype acquisition system, 1000m extended length tether, and a shorter 50m tether for testing at JPL.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The NASA market for self-sensing tethers is focused on missions featuring robotic exploration, especially using the Axel rover. NASA is planning specific missions including Mid-Size Rovers, Astrobiology Field Lab, Network Landers, Europa Explorer, and Titan-Enceladus Explorer to bring back samples from comets, asteroids, and the lunar south polar basin, and Mars. Market opportunities for tethered rovers within NASA often coincide with Mars exploration missions that are launched every 26 months. Prime contractors supporting NASA?s rover missions include Lockheed Martin Astronautics. Extending the range of the sensing technology will increase the scope of missions where these sensing tethers can be used. For example, missions to explore the large Martian craters that show evidence of liquid water through recurring slope lineae will require tether lengths of several hundreds of meters.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Sensing tether technology has particular application in robotics, where tethered robots range from search and rescue rovers to underwater vehicles, and from tethered military robots to energy sector inspection robots. This technology has the potential to transform tethers from a necessary but cumbersome umbilical cord into a dynamic sensor that can aid in monitoring the health and position of the robot. Extending the length of this technology will increase the types of robot missions where this technology can be applied. The underwater sensing community could similar sensing cables to precisely locate marine sensors.

In addition to sensing tethers, extending the length of Luna?s strain sensing technology will transfer to increased length for temperature sensing, curvature sensing, and full 3-D distributed position sensing, expanding Luna?s penetration of those markets. Extended length strain sensing will increase the market in aerospace distributed strain sensing to be applicable to larger aircrafts.

TECHNOLOGY TAXONOMY MAPPING (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.)
Autonomous Control (see also Control & Monitoring)
Diagnostics/Prognostics
Fiber (see also Communications, Networking & Signal Transport; Photonics)
Lasers (Measuring/Sensing)
Nondestructive Evaluation (NDE; NDT)
Positioning (Attitude Determination, Location X-Y-Z)
Telemetry (see also Control & Monitoring)
Tethers

PROPOSAL NUMBER: 17-2 Z6.01-8473
PHASE 1 CONTRACT NUMBER: NNX17CP72P
SUBTOPIC TITLE: High Performance Space Computing Technology
PROPOSAL TITLE: Robust Multicore Middleware

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Troxel Aerospace Industries, Inc.
2023 Northeast 55th Boulevard
Gainesville, FL 32641 - 2786
(720) 626-0454

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Ian Troxel
ian@troxelaerospace.com
2023 Northeast 55th Boulevard
Gainesville, FL 32641 - 2786
(720) 626-0454

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Ian Troxel
ian@troxelaerospace.com
2023 Northeast 55th Boulevard
Gainesville, FL 32641 - 2786
(720) 626-0454

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

Technology Available (TAV) Subtopics
High Performance Space Computing Technology is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Emerging radiation-hardened and commercial space-capable processors are leveraging general-purpose multicore and niche-application cores to satisfy the ever increasing onboard processing demands required by planned NASA missions. Such architectures can provide increased processing bandwidth and power efficiency for onboard processing applications. However, these advantages come at the cost of increased hardware and software complexity and decreased fault tolerance in the case of commercial technology. As software development is a major cost driver for missions, this increased complexity has the potential to significantly increase cost for future missions. In addition, maintaining mission assurance and fault tolerance is critical.  To address these risks, Troxel Aerospace Industries, Inc. (Troxel Aerospace) proposes to continue develop and commercialize a robust middleware management technology for spacecraft heterogeneous multicore processing systems.  The middleware technology will enable a fault tolerant computing environment that is portable to different processors and is largely transparent to mission applications executing upon the middleware to provide a standardized, resource-aware, fault tolerant interface for configuration management and heterogeneous resource allocation.  This Phase II will include developing the remainder of the middleware, executing a representative application using it across two or three different processor architectures, undertaking a heavy-ion radiation test campaign to quantify its effectiveness in a relevant mission environment, and continuing the commercialization activities begun in Phase I.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The technology under development addresses NASA�s key avionics goals including improved reliability and fault tolerance, increased autonomy, reduced size, weight and power (SWaP), and commonality across spaceflight and ground processing systems put forth in the NASA Crosscutting Technology Roadmap. The technology also enables long-duration crewed missions, space-based observatories, and solar system exploration will require highly reliable, fault-tolerant systems. Communication delays, the challenging orbital dynamics of Near-Earth Asteroids (NEAs), and extreme science missions require increased autonomy for on-board decision infrastructures. Future robotic missions will involve greater complexity and reactivity, which will require increased reliance on autonomy (i.e. advanced onboard processing). Deep-space missions that target active, dynamic, or time-varying phenomena will need robots that can adaptively adjust their configurations and behavior to changing circumstances, and robustly handle uncertainty. Robotic missions to NEAs will require the decision-making and monitoring processes�currently performed by ground control�to be performed by onboard autonomous systems. Advanced avionics technologies and approaches are needed to support these challenging missions and are enabled by Troxel Aerospace�s Robust Multicore Middleware.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
All non-NASA government and commercial space customers will directly benefit from the technology by obtaining increased onboard processing capability at reduced budget and SWaP cost for such applications as autonomous operations, improved mission processing, and downlink bandwith management. These features will are enticing to a variety of spacecraft markets including telecommunications, commercial imagery, launch vehicles, ISS re-service vehicles and exo-planetary commercial ventures (e.g. asteroid mining). The small satellite market will be of great interest given their early adoption of modern multicore technology and desperate need to improve system fault tolerance. Also, non-space markets that require robust fault tolerance on high-performance multicore processors will also be served by the middleware including: radiation test facilities (e.g. CERN), medical radiation therapy facilities, and other critical performance markets where people�s lives or expensive equipment is at risk such as aircraft, automobile, public transportation, and advanced manufacturing where the same processors targeted by the proposed effort (e.g. ARM-based processors and GPU co-processors) are already deployed. Troxel Aerospace plans to capture all these markets by following its proven commercialization strategy, i.e. through partnerships with vendors and primes who already supply processors to these missions and customers.

TECHNOLOGY TAXONOMY MAPPING (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.)
Algorithms/Control Software & Systems (see also Autonomous Systems)
Autonomous Control (see also Control & Monitoring)
Diagnostics/Prognostics
Quality/Reliability
Recovery (see also Autonomous Systems)
Recovery (see also Vehicle Health Management)

PROPOSAL NUMBER: 17-2 Z8.03-9396
PHASE 1 CONTRACT NUMBER: NNX17CG63P
SUBTOPIC TITLE: Small Spacecraft Power and Thermal Control
PROPOSAL TITLE: Dynamically Reconfigurable Electrical Power System(EPS) with Integrated Thermal Management and High Voltage Capability for Small Spacecraft

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
QorTek, Inc.
1965 Lycoming Creek Road, Suite 205
Williamsport, PA 17701 - 1251
(570) 322-2700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr Gareth J Knowles
gknowles@qortek.com
1965 Lycoming Creek Road, Suite 205
Williamsport, PA 17701 - 1251
(570) 322-2700

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Cathy Bower
cbrooke@qortek.com
1965 Lycoming Creek Road, Suite 205
Williamsport, PA 17701 - 1251
(570) 322-2700

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

Technology Available (TAV) Subtopics
Small Spacecraft Power and Thermal Control is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

The proposed program addresses the fundamental issues of lack of commonality across SmallSat platform power management.  The DREPS aims to improve modularity, scalability, and efficiency of small spacecraft and CubeSat power systems (up to 100W) by implementing a novel reconfigurable architecture that integrates high reliability components and novel thermal management techniques to enable operation in extreme radiation and temperature environments.  Integration of state-of-the-art technologies such as Gallium Nitride MOSFETs, micro-channel oscillating heat pipes, and digital control systems will enable an unparalleled level of system control while providing a solution focused on extreme environmental conditions required for long duration space missions. The DREPS includes digitally controlled power architecture providing 20+ configurable switched output services that can be commanded by any desired space communication protocol (I2C, SPI, CAN, SpaceWire).

Compatibility with new electric propulsion technologies can be obtained by the addition of QorTek’s recent advances in high voltage piezoceramic-based power converter technology. Integration of cutting edge thermal management technology will enable adaptive retention or rejection of heat as a fully integral portion of the system’s packaging through a partnership with ThermAvant Technologies.  An array of configurable MPPT Battery Control Regulators will allow compatibility with industry standard solar and energy storage.  The goal of Phase II is to achieve a modular SmallSat power system based on matrix interconnectivity of small power converters (cells) that is universally applicable to small satellite platforms and missions. The work plan will exit with fully tested ½U solution that is immediately applicable to all three target markets of ruggedized COTS (LEO), Radiation Tolerant (MEO/GEO) and long duration High Reliability (High-Rel) as vendor projected product availabilities are realized.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
This power system is applicable to a wide range of MicroSat/SmallSat LEO/GEO missions in support of Earth sciences, planetary sciences and Heliosphere studies. Science missions such as Astrobiology (e.g. microorganisms), radiometrics, environmental monitoring (e.g. weather), relay communications, Lunar resources, planetary magnetometry. are increasingly under consideration by NASA to be implemented by SmallSats. As technology advances, these smaller spacecraft will become ever more viable to undertake these, and a wide range of other NASA missions, along with technology qualification missions. The proposed technology offers to be transformative in enabling a low cost but completely custom tailorable EPS solution that both streamlines the development cycle that offers distinct SWaP advantages (in many cases very substantial) and exemplary performance. NASA engineers will be able to rapidly select the necessary multi-phase converter DREPS modules (cells) corresponding to mission requirements.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Other organizations outside USA such as CSA and ESA are now pursuing many planned SmallSat missions and similarly looking to expand these mission capabilities to new areas science and space operation missions such as re-entry, debris removal, climate change monitoring and many more. Such organizations are also ready customers for the proposed new DEPS EPS solution. As such, QorTek sees this commercial SmallSat or CubeSat market as the growth industry for its proposed DREPS products. The proposed CubeSat/SmallSat power architecture represents a transformative change in size/weight/applicability/functional capability. At present, a 4U-6U mission satellite will have the EPS occupying as much as 2U-4U of available space ? leaving little for the science payloads. This potentially will become the foundation for many non-government and commercial Small Satellite Systems where there can be abrupt changes in electrical power demands and/or must have power re-routing capability in the event of a partial failure. This will include Multimission Payload Satellites; Communications Satellite Arrays; Ground & Observation & Tracking and more.

TECHNOLOGY TAXONOMY MAPPING (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.)
Active Systems
Avionics (see also Control and Monitoring)
Circuits (including ICs; for specific applications, see e.g., Communications, Networking & Signal Transport; Control & Monitoring, Sensors)
Conversion
Distribution/Management
Heat Exchange
Manufacturing Methods
Passive Systems
Prototyping
Storage

PROPOSAL NUMBER: 17-2 Z9.01-9957
PHASE 1 CONTRACT NUMBER: NNX17CM18P
SUBTOPIC TITLE: Small Launch Vehicle Technologies and Demonstrations
PROPOSAL TITLE: Additively Manufactured Bimetallic Combustion Chambers for Small Launch Vehicles

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Arctic Slope Technical Services, Inc.
289 Dunlop Boulevard, Building 300
Huntsville, AL 35824 - 1126
(256) 562-2191

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Joseph Sims
Joseph.Sims@asrcfederal.com
289 Dunlop Boulevard, Building 300
Huntsville, AL 35824 - 1126
(256) 562-2191

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Vivian Jacobs
vjacobs@asrcfederal.com
7000 Muirkirk Meadows Dr, Ste. 100
Beltsville, MD 20705 - 6351
(301) 837-3956

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

Technology Available (TAV) Subtopics
Small Launch Vehicle Technologies and Demonstrations is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Arctic Slope Technical Services, Inc. (ASTS) is pleased to propose to continue the development of an additive manufacturing (AM) approach for fabricating bimetallic combustion chambers.  Our chamber design, which is applicable to future NASA small launch vehicles, exploits the combined capabilities of selective laser melting (SLM) and magnetic pulse welding (MPW), in order to reduce manufacturing lead time and cost and to improve quality through ease of inspection.  The chamber will use a two-piece GRCop-84 liner that is inserted and MP welded into a one-piece Inconel 625 structural jacket.  The MPW step will be used to permanently join the two halves of the liner at the throat and the liner itself to the jacket in a structurally sound, watertight manner.  Our structural jacket design includes integral propellant manifolds, which eliminates the time and expense associated with machining or casting separate components and welding them in place.

The benefits of such a design are substantial.  First, it is well understood that for complicated components like a modern combustion chamber, an AM manufacturing approach can drastically reduce cost (by 50% or more) and lead time (weeks instead of months).  Second, our particular design overcomes weaknesses of other additive designs by enabling easy inspection of the printed parts that otherwise would have to undergo CT scanning or X-ray inspection, which has proven to be exceptionally difficult for complex internal geometries like regenerative cooling channels and propellant manifolds.  Third, our basic material and manufacturing approach is scalable to booster class combustion chambers at a rate controlled solely by scaling of the build volumes available in commercial SLM machines (which is occurring rapidly).  In fact, commercial MPW systems are already being used in the automotive industry that can instantaneously weld parts of several meters in length

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
An excellent potential NASA application for this technology is the Exploration Upper Stage Engine (EUSE), a high performance (461-s Isp) LOX/hydrogen upper stage engine that will replace the venerable RL10. Like that predecessor, we fully expect the EUSE to use a closed expander cycle, since it combines exceptional performance with benign turbine environments. Since that cycle is completely reliant upon increasing the enthalpy of the liquid hydrogen to power the turbopump, the main combustion chamber (MCC) lies at the very heart of success for the EUSE.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
One truly commercial opportunity has come to our attention, which we are pursuing with vigor. Specifically, Virgin Orbit is a commercial "new space" entrant that is developing a small two-stage launch vehicle that is sure to benefit from our technology. Specifically, their second stage engine is a pump-fed, LOX/RP-1 engine that provides 5,000-lbf of vacuum thrust. To maximize our opportunity to insert this technology, the chamber layout developed under this contract is intended to act as a drop-in replacement for that engine.

TECHNOLOGY TAXONOMY MAPPING (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.)
Atmospheric Propulsion
Joining (Adhesion, Welding)
Launch Engine/Booster
Metallics
Processing Methods
Spacecraft Main Engine
Surface Propulsion

PROPOSAL NUMBER: 17-2 Z10.02-9316
PHASE 1 CONTRACT NUMBER: NNX17CM14P
SUBTOPIC TITLE: Methane In-Space Propulsion
PROPOSAL TITLE: Spinning-Scroll Pump for Cryogenic Feed System

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Air Squared, Inc.
510 Burbank Street
Broomfield, CO 80020 - 1604
(303) 466-2669

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Bryce Shaffer
bryce@airsquared.com
510 Burbank Street
Broomfield, CO 80020 - 1604
(513) 238-9778

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Rob Shaffer
robert@airsquared.com
510 Burbank St.
Broomfield, CO 80020 - 1604
(513) 200-3787

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

Technology Available (TAV) Subtopics
Methane In-Space Propulsion is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

The proposed innovation is the world's first cryogenic spinning scroll pump (CSSP) capable of pumping liquid methane or oxygen at flows of 8-10 lbm/s. The primary goal is to develop a versatile proof of concept CSSP, capable of pumping liquid or two-phase methane or oxygen at a wide range of speeds (i.e. 1,000-8,000 RPM) and a wide range of differential pressures while maintaining high-reliability and a compact size. The pump will be configurable, to allow multiple pumps to be placed in series for high-pressure multi-stage operation. During Phase I, Air Squared successfully designed, fabricated and tested a prototype CSSP on liquid nitrogen.

For Cryogenic pumping, state of the art (SOA), consists of two vastly different technology options. Centrifugal turbopumps and positive displacement pumps. Turbopumps utilize an impeller-inducer combination that relies on high impeller speeds to create a differential pressure. While the high-speed operation makes turbopumps compact, it also limits bearing life, differential pressure, and they can't handle two-phase flow. Positive displacement pumps can handle larger pressure differentials and don't have issues with two-phase flow. However, they can't achieve speeds over 3,000 RPM without bulky and high-load bearings making them less desirable for aerospace applications.

The CSSP offers the best of both options. As a positive displacement pump, it can achieve high-pressures with minimal reduction in flow and pump saturated liquids at low net-positive suction heads. Due to the spinning motion of the pump, various centrifugal loads are eliminated allowing speeds over 8,000 RPM possible and making the design compact and lightweight. Additionally, the spinning motion of the scrolls eliminates the need for a counterbalance common in orbiting scroll designs. This further reduces weight by eliminating counterweights and eases bearing loads. Air Squared believes the proposed CSSP is a perfect fit in support of Methane In-space Propulsion.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
The CSSP delivers improved flow, pressure and two-phase flow capability of cryogenic pumping to achieve NASA�s goal of methane in space propulsion for scalably sized spacecraft. A single or linked CSSP could be integrated into satellites or a spacecraft�s reaction control system to increase fuel flow rates and pressure providing better flexibility and dexterity during docking and landing. RES systems allow for altitude, translation, and rotational control and the CSSP would allow such systems to be integrated on to potentially larger or smaller modules. The CSSP minimizes space and weight needs while significantly improving fuel flow rate and pressure, allowing better engineering optimization for NASA modular spacecraft.

The CSSP enables efficient, low or zero boil-off cryogenic systems by circulating cryogenic helium gas from a cryocooler to broad area thermal shields surrounding the tanks. This would eliminate the need for high-efficiency heat exchangers that are required with ambient temperature circulator pumps. The pump would also enable thermodynamic vent systems in which cryo propellants are dropped in pressure and temperature and heat exchanged with liquid pumped in a circulation loop within the tank. The development of a long life, variable speed, and low leakage pump would add flexibility to NASA satellite and surface to space spacecraft.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Hydrogen has been identified as a potentially game-changing fuel by the aerospace industry, however, the necessary heavy cryogenic fuel tanks and low-pressure pumps have handicapped successful research and development. Integration of CSSP in hydrogen aircraft and unmanned aerial vehicles would improve fuel delivery, reduce fuel tank size, and become a critical component of lightweight aircraft. The estimated weight savings of the proposed pump is over 400 pounds per aircraft. The scroll pump would be a significant contributor to increased aircraft endurance and payload. Several aerospace leaders, including Boeing and AeroViromnet, already partner with Air Squared and demonstrate a niche market for the CSSP for next-generation aircraft with both the Department of Defense and commercial research and development.

Another commercial application would be a liquid natural gas pump, for LNG rail transport. SOA offers only limited options for positive displacement LNG pumps of which the CSSP two-phase fuel delivery and variable pressure operations could be disruptive. Progress Rail has already contacted Air Squared about using a positive displacement LNG scroll pump for locomotive transportation and has invested in an Air Squared�s orbiting scroll type LNG pump prototype. The greater reliability and flexible scaling of the CSSP holds vast potential in the next generation cryogenic fuel economy.

TECHNOLOGY TAXONOMY MAPPING (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.)
Cryogenic/Fluid Systems

PROPOSAL NUMBER: 17-2 Z10.03-8922
PHASE 1 CONTRACT NUMBER: NNX17CS11P
SUBTOPIC TITLE: Nuclear Thermal Propulsion (NTP)
PROPOSAL TITLE: Multi-Physics NTR Safety Analyses

SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
Little Prairie Services
14 Dunkin Road
Edgewood, NM 87015 - 9798
(505) 220-8029

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr Roger Lenard
rxlenard@gmail.com
14 Dunkin Road
Edgewood, NM 87015 - 9798
(505) 220-8029

CORPORATE/BUSINESS OFFICIAL (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr Roger Lenard
rxlenard@gmail.com
14 Dunkin Road
Edgewood, NM 87015 - 9798
(505) 220-8029

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

Technology Available (TAV) Subtopics
Nuclear Thermal Propulsion (NTP) is a Technology Available (TAV) subtopic that includes NASA Intellectual Property (IP). Do you plan to use the NASA IP under the award?
No

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)

Nuclear Thermal Propulsion (NTP) offers high promise to reduce launch mass, decrease mission costs and increase mission effectiveness, particularly for crewed missions to the planets. However, NTP has been plagued with high uncertainties in cost, schedule and safety, particularly launch safety. To reduce programmatic uncertainty, an unambiguous approach to documenting NTP safety prior to, during and after launch needs to be made. Until recently, the multi-physics models and computing power were not available to perform compelling analyses, and testing is prohibitively expensive, and unrevealing in many cases. This proposal directly addresses programmatic uncertainty by providing benchmarked, definitive product capable of documenting the safety of a NTP system during all launch phases. The proposal takes work performed by the SBC under IR&D which has performed detailed hydrocode modeling of a NTP impacting an unyielding surface from heights of 50 and 150 meters. To initiate the effort, it is important to start with simple compaction model, which was accomplished in Phase I with the Taylor impact simulation.  Instead of a single neutronics code, LPS demonstrated viability with three codes to better insure reliable results.  Phase II will extend this work.  It will continue to update the SCCTE-2 NTR design and include any design modifications by NASA contractors.  The NTR model will be updated to include important peripherals suchs as turbooo pump assemblies, thrust vector control hardware, plumbing and a propellant tank.  These are essential items for a more realistic impact scenario.  Further, during Phase I, LPS determined there are a number of materials whose mechanical database is insufficient for unambiguous hydrocode simulations.  LPS will deliver a comprhensive test program plan, costs and schedule to resolve these deficiencies. The technical readiness will be improved so End to End Software elements are implemented and interfaced with existing system concepts.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
LPS is already working with NASA nuclear program managers to integrate the tools, methods, and capabilities of this SBIR into its nuclear launch and operations safety effort, including ground testing and handling. Indeed, this project, while being used primarily for launch safety analyses and documentation for nuclear thermal propulsion, is equally applicable to all nuclear payloads: nuclear thermal propulsion, nuclear electric power systems for in-space and surface operations and also radioisotope power sources. There are no current commercial entities capable of providing these services. At the end of Phase II, LPS will be in a singularly unique position to provide these commercially based, multi-physics modeling capabilities for nuclear safety to NASA, the Department of Defense and the Department of Energy. While primarily directed toward nuclear systems, this capability can be applied to other hazardous payloads, whether launched into space or involved in over-the-road transportation.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Because of the pioneering work performed by the NASA Marshall Space Flight Center, we now know some NTR configurations are feasible with Low Enriched Uranium (LEU). This will dramatically reduce security and development costs, and result in a more affordable system. Because of the LEU approach, commercial companies may be enticed to become involved, because the costs can be more well defined. The PI and other are looking to engage certain commercial space entities about becoming involved. Some entities which would benefit from this work include Lockheed Martin, Boeing Space Systems, and other defense contractors. The Missile Defense Agency has been contacted regarding the recrudescence of the neutral particle beam system for missile defense, and space nuclear power would provide the system with the requisite power and maneuverability for mission operations.

TECHNOLOGY TAXONOMY MAPPING (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.)
Analytical Methods
Knowledge Management
Models & Simulations (see also Testing & Evaluation)
Quality/Reliability
Simulation & Modeling
Software Tools (Analysis, Design)
Sources (Renewable, Nonrenewable)
Space Transportation & Safety
Spacecraft Main Engine
Structures

Form Generated on 04-26-18 12:25