SBIR Phase I SolicitationAbstract Archives

NASA 2016 STTR Phase I Solicitation


PROPOSAL NUMBER:16-1 T1.01-9784
SUBTOPIC TITLE: Affordable Nano/Micro Launch Propulsion Stages
PROPOSAL TITLE: Low Cost Upper Stage for Affordable Nano/Micro Launch

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TGV Rockets, Inc.
2519 Benning Road Northeast
Washiington, DC 20002-4805
(301) 913-0071

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Tennessee
1331 Circle Park Drive
Knoxville, TN 37916-3801
(865) 974-3466

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Earl Renaud
renaud@tgv-rockets.com
2519 Benning Rd., NE
Washiington,  DC 20002-4805
(613) 618-3940

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
TGV Rockets, Inc., in partnership with the University of Tennessee, Knoxville, proposes to develop a unique Low-Cost Upper Stage for Affordable Nano/Micro Launch. The stage will make use of a novel eutectic fuel blend that is thermally compatible with liquid-oxygen, unique low-cost lightweight avionics, and simple common-wall tanks. The projected production cost of the completed upper stage is approximately $100,000. TGV will build upon this technology to produce the system capability to launch 100 Lbs. to LEO for $1 Million.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
DoD has recognized military utility to payloads at or below 700 lbs and has funded several 150 lb class payloads. DoD views applications to launch small dedicated comms, timing, comms photo recon, weather. A number of small satellite constellations for commercial applications have been proposed including OneWeb, Planetlabs, UrtheCast and technical growth will allow service to existing customers such as ORBComm, Iridium and Globalstar.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
NASA has been looking at a series of small science and earth science missions using NanoSats and the potential for lunar missions using CubeSats. The Early Explorer, Vanguard and pioneer spacecraft were all built and flown under the 100 Lb. threshold. NASA STMD has been funding small and NanoSat missions. Small satellites, including CubeSats, are playing an increasingly larger role in exploration, technology demonstration, scientific research and educational investigations at NASA. These miniature satellites provide a low-cost platform for NASA missions, including planetary space exploration; Earth observations; fundamental Earth and space science; and developing precursor science instruments like cutting-edge laser communications, satellite-to-satellite communications and autonomous movement capabilities. They also allow educators an inexpensive means to engage students in all phases of satellite development, operation and exploitation through real-world, hands-on research and development experience on NASA-funded rideshare launch opportunities.

TECHNOLOGY TAXONOMY MAPPING
Fuels/Propellants
Launch Engine/Booster


PROPOSAL NUMBER:16-1 T1.01-9785
SUBTOPIC TITLE: Affordable Nano/Micro Launch Propulsion Stages
PROPOSAL TITLE: Low-Cost, Scalable, Hybrid Launch Propulsion Technology

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Purdue University
155 S. Grant Street
West Lafayette, IN 47908-2114
(765) 494-6204

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Prakash Joshi
joshi@psicorp.com
20 New England Business Center
Andover,  MA 01810-1077
(978) 738-8202

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Physical Sciences Inc. (PSI), in collaboration Purdue University, proposes to develop a novel launch propulsion technology for rapid insertion of nano/micro satellites (~ 5-50 kg scale) into low earth orbit, with the potential to lower the current state-of-the-art launch stage cost by a factor of two. The technology employs a propulsion scheme comprising a storable liquid oxidizer and a unique solid fuel with excellent mechanical and thermochemical properties. The propulsion scheme was initially developed by PSI under DARPA programs for applications to in-space thrusters integrated in a consumable-structure spacecraft. The proposed application of this scheme to launch vehicle stage technology will result in low-cost, mass-efficient launch systems and will reduce the technical development risk for NASA. The fuel used is commercially available as an inexpensive engineering material. The oxidizer is commercially available as a low-cost, industrial chemical. Both have high density, are green (halogen and nitrogen free), and their chemical reaction has a high specific impulse. The oxidizer storage, handling, transportation, and loading operations are simpler and safer compared to cryogenic or toxic propellants. These attributes of the fuel and oxidizer enable our proposed concept of a low-cost launch vehicle stage. The specific objective of Phase I is to develop and analyze low-cost launch stage and thruster design concepts, and to develop and build a scaled prototype thruster hardware that will be used in both Phases I and II to characterize thruster design and to obtain performance data for use in the launch stage and propulsion system design/analysis studies. At the end of Phase I, we will have demonstrated the operation of the subscale thruster system and measured its performance. A plan for Phase II work, involving approaches to subscale ground testing or sub-orbital flight testing, will also be developed.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The non-NASA applications for the proposed launch vehicle stage technology include Air Force, Navy, and National Reconnaissance Organization missions to insert nano satellites into LEO over a range of inclinations and to in-space propulsion, where high thrust at moderate impulse is required. The commercial sector and educational institutions would also benefit from a substantially lower cost access to low earth orbit. The superior thermomechanical properties of the fuel will produce lighter propulsion systems for all applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The NASA application for the proposed launch vehicle stage technology is for insertion of nano/micro satellites into LEO over a range of inclinations. Initial applications are likely to be upper stages of launch vehicles. However, the technology can also be applied to other stages and to in-space propulsion, where high thrust at moderate impulse is required. The superior thermomechanical properties of our fuel are attractive for lighter propulsion systems as structural containment requirements are lowered and additional liner/insulation materials are unnecessary.

TECHNOLOGY TAXONOMY MAPPING
Fuels/Propellants
Launch Engine/Booster


PROPOSAL NUMBER:16-1 T1.01-9835
SUBTOPIC TITLE: Affordable Nano/Micro Launch Propulsion Stages
PROPOSAL TITLE: Torch-Augmented Spark Igniter for Nanosat Launch Vehicle LOX/Propylene Rocket Engine

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Garvey Spacecraft Corporation
389 Haines Avenue
Long Beach, CA 90814-1841
(562) 498-2984

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
The University of Alabama in Huntsville PRC / OSP
301 Sparkman Drive, VBRH E-29
Huntsville, AL 35899-0001
(256) 824-6000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christopher Bostwick
cbostwick@garvspace.com
389 Haines Avenue
Long Beach,  CA 90814-1841
(661) 547-9779

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The technical innovation proposed here is the introduction of torch-augmented spark ignition for high performance liquid oxygen (LOX) / propylene rocket engines now in development for a future two-stage nanosat launch vehicle. Spark ignition is critical for reliably achieving multiple in-flight restarts of NLV upper stage engines. In addition, this new capability will generate immediate R&D benefits through the streamlining of ongoing LOX/propylene engine testing. By replacing pyrotechnic charges that are the current state-of-the-art method for LOX/propylene engine ignition, spark igniters eliminate the need to install fresh units after each test attempt (a manually intensive and tedious process). Additional operational benefits from eliminating a category of pyrotechnics and ordnance will accrue in logistics and safety.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A two-stage nanosat launch vehicle now in development by GSC which features LOX/propylene propulsion will benefit directly with the application of this spark ignition technology in both stages. Another candidate application is a derivative upper stage now in preliminary development for the DARPA XS-1 experimental space plane.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In the near-term, the application of this spark igniter technology to static fire testing to replace pyrotechnic devices will improve the efficiency of NASA-sponsored research investigating high performance LOX/propylene rocket engines. Subsequent application in the upper stages of nanosat launch vehicles will enable multiple in-flight engine restart, a necessity for optimizing orbit insertion for CubeSat-class payloads. Typical program users that will benefit from this capability include the CubeSat Launch Initiative and the Educational Launch of Nanosatellites (ELaNa) program.

TECHNOLOGY TAXONOMY MAPPING
Fuels/Propellants
Launch Engine/Booster


PROPOSAL NUMBER:16-1 T1.02-9703
SUBTOPIC TITLE: Detailed Multiphysics Propulsion Modeling & Simulation Through Coordinated Massively Parallel Frameworks
PROPOSAL TITLE: Efficient High Fidelity Computational Tool for Acoustically Driven Multiphysics Propulsion Modeling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tetra Research Corporation
420 Park Avenue West
Princeton, IL 61356-1934
(815) 872-0702

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Mississippi State University
P.O. Box 6156
Mississippi State, MS 39762-9627
(662) 325-2346

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Rex Chamberlain
rex@tetraresearch.com
420 Park Avenue West
Princeton,  IL 61356-1934
(815) 872-0702

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
It is widely recognized that detailed simulation of large combustors to assess combustion instability and water spray systems to suppress rocket launch and test stand acoustic energy require advances in two phase flow, combustion, unsteady flow and acoustics modeling efficiency and fidelity. With recent advances in computer science technology, turbulent multiphysics modeling and high fidelity algorithms, current applications are poised for coordinated integration into a computational framework that offers realistic simulation of propulsion system fluid dynamics. MSU has recently implemented a hybrid 4th order skew symmetric flux in the Loci/CHEM multiphysics CFD solver. The new scheme has exceptionally low dissipation properties for vortical and acoustic signal propagation on both structured and unstructured meshes and offers excellent potential for analysis of acoustically driven propulsion system combustion instabilities. Simulation of large scale systems, however, is further complicated by the need to model unsteady turbulence effects. MSU has also recently employed the very promising dynamic hybrid RANS/LES methodology with the new low dissipation scheme to demonstrate significantly improved resolution of fine scale unsteady turbulence structures. For highly stretched boundary layer meshes, however, both implicit and explicit time integration schemes are problematic for thin boundary layers. Fortunately, dramatic performance improvements are possible through a novel hybrid explicit-implicit time integration scheme that uses the implicit treatment for fluxes constrained by the explicit stability limit and the explicit scheme elsewhere. Since the explicit method is more than an order of magnitude cheaper than the implicit scheme, the potential speedup could be a factor of ten. Thus the proposed computer science, turbulent multiphysics and high fidelity integrated framework can realistically expect to enable propulsion system DDT&E and production cost reductions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The growing trend toward coupled multiphysics analyses is opening significant new markets as more difficult problems can be addressed using advanced computational techniques. The ability to robustly model acoustically driven combustion instability problems in propulsion will allow the commercial aerospace and defense industries to improve design and development of new products streamline ground testing and reduce flight risk. Our analysis software can also be applied to such varied commercial applications as coal, natural gas and food processing systems. The basic architecture of the modeling framework can remain the same while new plug-in modules are developed to address different physics and design requirements.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology will provide NASA with an efficient, robust multiphysics propulsion modeling and prediction tool that is built on coordinated advances in computer science, multiphysics modeling and high fidelity algorithms. The research product will provide enabling engineering and scientific technologies to model and predict acoustically driven propulsion related flow problems while reducing development, test, evaluation and production costs. Potential enhancements include improved two phase flow combustion models, enhanced droplet/turbulence interaction modeling, variable real fluids transport properties, expanded thermodynamic databases and extended model validation. The proposed computational tool is also applicable to water spray systems for suppression of rocket launch and test stand acoustic energy.

TECHNOLOGY TAXONOMY MAPPING
Analytical Methods
Models & Simulations (see also Testing & Evaluation)
Software Tools (Analysis, Design)
Launch Engine/Booster
Acoustic/Vibration
Simulation & Modeling


PROPOSAL NUMBER:16-1 T1.02-9827
SUBTOPIC TITLE: Detailed Multiphysics Propulsion Modeling & Simulation Through Coordinated Massively Parallel Frameworks
PROPOSAL TITLE: Prediction of Strutural Response and Fluid-Induced Vibration in Turbomachinery

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Mississippi State University
133 Etheredge Hall 449 Hardy Road, P.O. Box 6156
Mississippi State, MS 39762-6156
(662) 325-2346

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Harris
robert.harris@cfdrc.com
701 McMillian Way, NW, Ste. D
Huntsville,  AL 35806-2923
(256) 726-4997

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced turbomachinery components play a critical role in launch vehicle and spacecraft liquid rocket propulsion systems. To achieve desired efficiencies, extremely tight tolerances are often imposed between inducer blades and shrouds or other system components which sets up strong interactions that influence both the aerodynamics and the structural performance of blades and vanes. These transient interactions, including rotor-stator interactions (RSI), can deform the blades and significantly impact the vibrational and acoustic characteristics of the engine, greatly reduce the efficiency, and even lead to blade or vane failure. Current production design tools for turbomachinery do not account for the coupled fluid-structure interaction (FSI) physics associated with these phenomena. This STTR effort will develop and deliver a multidisciplinary design tool for advanced turbomachinery components to account for FSI phenomena and enable more accurate modeling of systems and subscale demonstrators. CFDRC will supplement the NASA massively parallel Loci framework with highly accurate and efficient integrated FSI capabilities to enable better understanding of critical turbomachinery problems in liquid rocket propulsion systems that defy conventional predictions. Loci will be enhanced to enable constrained deformations in moving overset grid systems to support prediction of structural response and fluid-induced vibration in rotating components. Phase I will demonstrate improved modeling fidelity and provide great insight into FSI phenomena in turbomachinery, and Phase II will bring the complete predictive capabilities to production for detailed investigations into advanced turbomachinery for liquid rocket propulsion systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The developed FSI analysis tool will provide accurate high-fidelity aerothermoelastic analyses for dynamic loads for turbomachinery, inducer, delivery pipes, and valves. Aerospace engineers will be able to utilize the technology to analyze early designs thereby reducing the dependence on expensive wind tunnel/water tunnel and flight tests. Benefits will be achieved in final performance, and enhanced structural integrity, prolonged structural life, and improved safety of vehicles. Direct applications include analysis of dynamic loads problems for aerospace vehicles; e.g. buffet, flutter, buzz, and control reversal; and noise, vibrations, and buffet suppression of rotorcraft and commercial air vehicles. Other applications include vortex-blade/control surfaces interaction for rotorcraft and fixed wing aircraft, heat exchanger vibration, strumming of cables and offshore pipelines, galloping of towers and masts, and fatigue of panels.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed development of a fully coupled fluid-structure interaction (FSI) tool provides a unique opportunity to optimize design, realize additional system efficiencies, reduce weight and/or cost, and increase part life in future generations of liquid rocket engine (LRE) designs. A fully-coupled FSI tool has a large number of other applications in the NASA launch vehicles propulsion systems including: (a) prediction of rocket launch-induced fluctuating pressure loads and structural response; (b) prediction of water suppression system interactions with ignition over pressure (IOP) accurate prediction of acoustic environment; (c) prediction of vehicle buffet during ascent, (d) fluid-thermal-structural coupling of rocket engine nozzles; (e) FSI in nuclear thermal rockets; (f) prediction of self-generated dynamics of fluid delivery pipes with deformable bellows; (g) liquid propellant tank breathing due to liquid interaction with the flexible tank shell; and (h) design of new generation POGO accumulators with bellows separating liquid and gas phases.

TECHNOLOGY TAXONOMY MAPPING
Tools/EVA Tools
Models & Simulations (see also Testing & Evaluation)
Prototyping
Software Tools (Analysis, Design)
Smart/Multifunctional Materials
Deployment
Structures
Hardware-in-the-Loop Testing
Simulation & Modeling


PROPOSAL NUMBER:16-1 T1.02-9828
SUBTOPIC TITLE: Detailed Multiphysics Propulsion Modeling & Simulation Through Coordinated Massively Parallel Frameworks
PROPOSAL TITLE: Unified In-Space Propulsion Framework for Prediction of Plume-Induced Spacecraft Environments

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Mississippi State University
133 Etheredge Hall 449 Hardy Road, P.O. Box 6156
Mississippi State, MS 39762-6156
(662) 325-2346

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ranjan Mehta
ranjan.mehta@cfdrc.com
701 McMillian Way Northwest, 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)
Chemical contamination of spacecraft components as well as thermal and force loading from firing liquid propellant thrusters are critical concerns for in-space propulsion applications. Gas molecular contamination and liquid droplet deposition due to incomplete combustion threaten to damage surface materials, sensitive instruments and optical sensors, and poses major risks for mission success. Liquid propellant thrusters operate in space at near-vacuum conditions, and contaminants traverse a complex mixed continuum-rarefied environment upon exiting the thruster nozzle. Current CFD modeling capabilities for in-space propulsion analysis have made great strides, but fall short of providing the fidelity required to simulate the contaminant transport around the spacecraft with sufficient efficiency and accuracy. This STTR will develop and deliver an innovative computational architecture for prediction of plume flow impingement and contaminant dispersal through mixed flow environments for in-space propulsion analysis. CFDRC will supplement the massively parallel Loci framework with a highly accurate unified solver for prediction of mixed continuum-rarefied flows with contaminant dispersal. This will enable better understanding and prediction of thermal and force loading and contamination of spacecraft components, and enable design of a new era of safer next-generation in-space propulsion systems. Phase I will demonstrate improved modeling fidelity and provide great insight into in-space thruster plume contaminant environments. Phase II will bring the complete predictive capabilities to production for detailed investigations into contaminant environments for full spacecraft configurations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA government and commercial applications include, assessment of thruster plume induced environments on commercial and military spacecraft, predicting the impact of particles scattered from thruster plumes on ballistic missile and missile interceptor signatures, and optimization of commercial satellite operational life through contamination minimization.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed computational architecture for prediction of plume flow impingement and contaminant dispersal through mixed continuum-rarefied flow environments combines multiple novel computational approaches into one unified simulation environment. This technology will be highly beneficial to NASA and its contractors for prediction and analysis of contaminants and particulate transport and interaction in near-vacuum conditions for in-space propulsion applications. Direct benefits include risk reduction through improved fidelity simulations of thruster plume molecular and droplet contamination reaching spacecraft surface insulation, optical sensors and sensitive instruments. Direct NASA applications include supporting spacecraft design with most advantageous thruster placement and design mitigation measures such as shielding through simulation based engineering. Other NASA applications include simulation of effectiveness of RCS thrusters in reentry capsule rarefied wake region.

TECHNOLOGY TAXONOMY MAPPING
Tools/EVA Tools
Models & Simulations (see also Testing & Evaluation)
Prototyping
Software Tools (Analysis, Design)
Smart/Multifunctional Materials
Deployment
Structures
Hardware-in-the-Loop Testing
Simulation & Modeling


PROPOSAL NUMBER:16-1 T3.01-9696
SUBTOPIC TITLE: Energy Transformation and Multifunctional Power Dissemination
PROPOSAL TITLE: 400 W Stirling Convertor for kW-Class Space Power System

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SCCAQ Energy, LLC
432 Heritage Hills Drive
Richland, WA 99352-7839
(509) 308-2702

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Temple University
1947 North 12th Street
Philadelphia, PA 19122-6077
(215) 204-8530

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Songgang Qiu
sccaqenergy@gmail.com
432 Heritage Hills Dr.
Richland,  WA 99352-7839
(509) 308-2702

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SCCAQ Energy, LLC (SCCAQ), in collaboration with Temple University and Infinia Technology Corporation (ITC), is pleased to propose a Stirling Kilopower Innovative Prototype (SKIP) that is ideally suited for use with fission-based Space Nuclear Power Systems (SNPS) and/or Nuclear Electric Propulsion (NEP) systems. SKIP adapts the ongoing development of a 400-W free-piston Stirling (FPS) engine for terrestrial applications to meet NASA needs for SNPS. This proposal is specifically addressed to STTR Topic T3 (Space Power and Energy Storage), with an emphasis on Subtopic T3.01. The proposed effort will be supported by Temple University SEEE lab personnel and will heavily leverage engineering support from Infinia Technology Corporation (ITC). This proposal is based on adapting newly developed 400-W engine at ITC to current NASA needs for an extremely reliable, robust, and high performance space power engine for Kilopower fission thermal conversion, among other potential power system heat sources. The key change that is needed to develop a SKIP demonstration unit is to modify the heater head to be suitable for interface with a space reactor system as a heat source.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed in the proposed SKIP system, however, has potential commercial applicability to the remote power and combined heat and power generator line that ITC/Qnergy is pursuing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The market for the SKIP-specific device will be initially focused on delivery of NASA space power systems.

TECHNOLOGY TAXONOMY MAPPING
Conversion
Generation


PROPOSAL NUMBER:16-1 T3.01-9697
SUBTOPIC TITLE: Energy Transformation and Multifunctional Power Dissemination
PROPOSAL TITLE: Innovative Stirling Convertor for Distributed Electric Power from Thermal Energy Recovery

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SCCAQ Energy, LLC
432 Heritage Hills Drive
Richland, WA 99352-7839
(509) 308-2702

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Temple University
1947 North 12th Street
Philadelphia, PA 19122-6077
(215) 204-8530

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Songgang Qiu
sccaqenergy@gmail.com
432 Heritage Hills Dr.
Richland,  WA 99352-7839
(509) 308-2702

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SCCAQ Energy, LLC (SCCAQ) in collaboration with Temple University and Infinia Technology Corporation (ITC) proposes to develop a Reliable Stirling Convertor (RSC) prototype free-piston Stirling (FPS) engine designed to address NASA needs for space power applications. This STTR proposal is specifically addressed to Topic T3 (Space Power and Energy Storage), with an emphasis on Subtopic T3.01 (Energy Transformation and Multifunctional Power Dissemination). The RSC offers multifunctional versatility that can efficiently convert thermal energy from a wide variety of heat sources into useful distributed electric power. Examples include capturing waste heat from a rocket exhaust, utilizing concentrated solar power, and conversion of nuclear heat energy from either radioisotope decay or fission energy. The reference design starting point will be the Technology Demonstration Convertor (TDC) that was developed by Infinia Corporation in the 1999 to 2006 time frame as a Radioisotope Power System (RPS). SCCAQ proposes to significantly upgrade the TDC design using newer technology and innovations to increase efficiency and robustness, while reducing size and weight. The proposed effort will be supported by SEEE lab of Temple University and will heavily leverage support from Infinia Technology Corporation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Terrestrial applications

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ultimate market for the proposed RSC is for application to radioisotope power systems. As such, the only clients are NASA/DOE and their system integration contractors. SCCAQ will support further development in accordance with client needs.

TECHNOLOGY TAXONOMY MAPPING
Conversion
Generation


PROPOSAL NUMBER:16-1 T3.01-9698
SUBTOPIC TITLE: Energy Transformation and Multifunctional Power Dissemination
PROPOSAL TITLE: Advanced Stirling Regenerator and Heat Exchanger Assembly for Radioisotope Stirling Space Power

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SCCAQ Energy, LLC
432 Heritage Hills Drive
Richland, WA 99352-7839
(509) 308-2702

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Temple University
1947 North 12th Street
Philadelphia, PA 19122-6077
(215) 204-8530

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Songgang Qiu
sccaqenergy@gmail.com
432 Heritage Hills Dr.
Richland,  WA 99352-7839
(509) 308-2702

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SCCAQ Energy, LLC (SCCAQ), in collaboration with Temple University and Infinia Technology Corporation, proposes to develop an Advanced Stirling Regenerator and Heat Exchanger Assembly to significantly increase the performance and durability of Stirling Power systems to address the need for an efficient and robust Radioisotope Power System for space applications. This assembly will be used to replace the heat exchangers and random fiber regenerator of Technology Demonstration Convertor developed by Infinia Corporation in 1999 to 2006. Proposed Principal Investigator, Dr. Songgang Qiu, was at that time PI and the principal designer for the Infinia Stirling Radioisotope Generator program, under which the TDC was developed. Dr. Qiu was co-PI for the micro-machined involute regenerator project under a NASA GRC contract. The integrated regenerator/heat exchanger assembly will be additively manufactured to increase the efficiency and durability, while reducing the size and weight. The major innovation is additively manufacturing the assembly to have outstanding figure of merit comparable to foil regenerator while improves reliability, better than mesh screen regenerator. The integrated assembly of heat exchangers and regenerator will provide uniform flow throughout the key components to minimize flow separation and flow losses in the plenums and to avoid jetting in the regenerator.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed in the proposed system, however, has potential commercial applicability to the remote power and combined heat and power generator line that ITC/Qnergy is pursuing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The market for the RSG with ReHX will be initially focused on delivery of NASA space power systems.

TECHNOLOGY TAXONOMY MAPPING
Conversion
Generation


PROPOSAL NUMBER:16-1 T3.01-9843
SUBTOPIC TITLE: Energy Transformation and Multifunctional Power Dissemination
PROPOSAL TITLE: Active Radiation Shield

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Gloyer-Taylor Laboratories, LLC
112 Mitchell Boulevard
Tullahoma, TN 37388-4002
(931) 455-7333

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Tennessee
University of Tennessee
Knoxville, TN 37996-0001
(865) 974-7870

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Gloyer
paul.gloyer@gtlcompany.com
112 Mitchell Blvd.
Tullahoma,  TN 37388-4002
(931) 455-7330

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
DEC-Shield technology offers the means to generate electric power from cosmic radiation sources and fuse dissimilar systems and functionality into a structural component to create a Multi-functional Structure (MFS). DEC-Shield integrated into MFS technology can be used to generate electric power and provide radiation protection in a space vehicle; even maximizing that protection by spreading the required systems and components across the structure. GTL will develop several DEC-Shield concept designs, fabricate test articles and test them in a representative radiation environment to demonstrate proof of concept. Further, GTL will analyze the test results and develop an optimized proof of concept DEC-Shield design. The Phase II effort will culminate with the design, fabrication and testing of DEC-Shield prototype Demonstration Panel that incorporates electrical power generation from GCR and solar wind sources.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The multi-functional aspects can also be used to reduce mass and parts count in satellites and launch vehicles (Commercial, DoD and NASA). Multi-functional technology could also be applied in commercial aircraft to increase capability, reduce parts count and cost.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
GTL's Multi-functional Structure, DEC-Shield and Adaptive radiation protection technology offers means to maximize the performance of a space vehicle structure providing electric power generation from cosmic radiation, radiation protection for astronauts in space stations, space vehicles, transfer vehicles and habitats. This capability supports NASA's space and exploration programs. The DEC-Shield has the potential to provide power from cosmic and solar wind sources adding a new option for NASA space missions. The multi-functional aspects can also be used to reduce mass and parts count in unmanned systems, which could reduce cost of NASA satellites and spacecraft.

TECHNOLOGY TAXONOMY MAPPING
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing & Evaluation)
Isolation/Protection/Radiation Shielding (see also Mechanical Systems)
Conversion
Distribution/Management
Generation
Organics/Biomaterials/Hybrids
Polymers
Smart/Multifunctional Materials
Structures


PROPOSAL NUMBER:16-1 T3.02-9793
SUBTOPIC TITLE: Self-Powered, Ultra-Miniature Devices
PROPOSAL TITLE: Innovative High Energy Density Storage in Nano Vacuum Tubes (NVTs) Designed for Small Leakage Curren

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Material Systems Engineering, Inc. (AMSENG)
2309 Pennsbury Court
Schaumburg, IL 60194-3884
(630) 372-9650

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
The Board of Trustees of the University of Illinois
1901 South First Street
Champaign, IL 61820-7406
(217) 333-2187

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alfred Hubler
a-hubler@uiuc.edu
University of Illinois
Urbana,  IL 61801-5824
(217) 552-0728

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's various Space Mission Directorate seek to develop technology to fulfill the technology gap and to enable missions with the unique high energy density charge storage technology. The overall goal of this STTR proposal is attempt to develop the novel energy storage technology to enable and enhance the capabilities of future NASA missions. The unique set of requirements for the power systems for various missions have emerged and they vary greatly, with advancements in components needed above the current State of the Art for high energy density, high power density, long life, high reliability, low mass/volume, radiation tolerance, and the wide temperature operation. For this STTR our first goal is evaluation of the concept of Nano Vacuum Tube (NVT) based charge storage device design that can provide High Energy Density storage with significant mass savings. The feasibility evaluation of design approaches are suggested to meet the desired special needs of charge storage in space. As a second goal, it plans to leverage IR&D done at UIUC and AMSENG to bring together unique experience base team to undertake the feasibility study to fulfill the identified technology gap through prototype development. Although the theory developed at UIUC predicts that storage of GJ/m3 charges is feasible in Nano Vacuum Tubes, the proposed experiments will decide what is feasible and which design options delivers the performance in space, when one uses the space stable heritage light weight materials. Finally, the suggested material designs and the devices need to meet reliability needs of the space mission environment for a typical ten year mission lifetime and conform to the mission space qualification needs and the requirements including high vacuum, microgravity, radiation, atomic oxygen, low out gassing, and high launch loads. The phase I - feasibility evaluation and the phase II - validation efforts suggested herewith can help us to fulfill the technology gap

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
DOD Applications: Many DOD space and avionics systems, including communications and navigation satellites, could benefit from increased availability of High Specific Power at High Power density and unique material design that can provide reliable power for the mission needs. Its unique applications in hardening can be of special appeal to the DOD needs. Commercial Application: Space, avionics and terrestrial commercial systems, including satellites, aircraft avionics and automobiles, could benefit from the developed charge storage systems. Success in charge storage concept may open various market sectors due to the appeal of device technology for light weight and ultra high charge storage density along with the involved very small charging & discharging times.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Many NASA science missions, avionics and terrestrial systems, including satellites, aircrafts, balloons and unmanned areal vehicle avionics could benefit from the developed charge storage systems. Success in charge storage concept with low mass may open up abundant power needs of many NASA missions due to the appeal of device technology for light weight and ultra high charge storage density along with the involved very small charging & discharging times

TECHNOLOGY TAXONOMY MAPPING
Distribution/Management
Storage
Characterization
Microfabrication (and smaller; see also Electronics; Mechanical Systems; Photonics)
Processing Methods
Ceramics
Coatings/Surface Treatments
Nanomaterials
Smart/Multifunctional Materials
Lifetime Testing


PROPOSAL NUMBER:16-1 T4.01-9721
SUBTOPIC TITLE: Dynamic Servoelastic (DSE) Network Control, Modeling and Optimization
PROPOSAL TITLE: Sensitivity Analysis for Design Optimization Integrated Software Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Linked Inc
3914 Deervale Drive
Sherman Oaks, CA 91403-4607
(805) 330-1650

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of California, Los Angeles,
11000 Kinross Avenue, Suite 200
Los Angeles, CA 90095-2000
(310) 794-0558

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Abdon Sepulveda
abdon.sepulveda@gmail.com
11121 Queensland St. #H49
Los Angeles,  CA 90034-5231
(424) 270-3506

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of this proposed project is to provide a new set of sensitivity analysis theory and codes, the Sensitivity Analysis for Design Optimization Integrated Software Tool set, to work within the existing NASA O3 Tool. In this Phase I effort, the sensitivity approach will be implemented for two basic types of analysis, namely static systems of equations (linear and non-linear) and eigen-problems. This implementation will focus on the elements most commonly used for aerospace design; beam, plate, and shell elements. The following specific goals are identified: 1 Integrated Multidisciplinary Sensitivity Analysis Toolset for Design Optimization (software) 2 Use of Advanced Algorithms to Maximize Computational Efficiency (analytic sensitivities) 3 Compatibility with Existing NASA Software Design Tools for computational integration to O3.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Sensitivity analysis is required for efficient optimal design and reliability analysis. Optimization is today widely used in the aerospace industry, automotive industry, sports equipment design and medical equipment design, just to mention a few. Building sensitivity analysis modules that can flexibly connect with analysis and finite elements has a tremendous potential for these industries since we can provide tailored solutions for their particular needs. Not only has the optimization become more efficient but also sensitivities provide guidance on determining the importance of variables by their effect on other system components.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Specifically at NASA we see direct application in the efficient integration into the optimization environment of analysis modules already built in the Object-Oriented Optimization Tool. At the conclusion of Phase I we see immediate benefit to optimizing for Weight or to determine sizing and shape for structural members of aircraft. Mechanical Deflection, Stress, and Strain analysis, and Buckling analysis codes will also benefit. Frequency and Mode Shape analysis and others future modules can then provide first order sensitivity. This information can then be fed directly to the optimizer or to an approximation concepts approach. Having standalone sensitivity modules will also provide NASA flexibility in evaluating constraints and responses not necessarily available in standard commercial codes.

TECHNOLOGY TAXONOMY MAPPING
Aerodynamics
Air Transportation & Safety
Spacecraft Design, Construction, Testing, & Performance (see also Engineering; Testing &