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NASA 2007 SBIR Phase 1 Solicitation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Adherent Technologies, Inc.
9621 Camino del Sol NE
Albuquerque, NM 87111-1522

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrea Hoyt Haight
adherent@earthlink.net
9621 Camino del Sol NE
Albuquerque,  NM 87111-1522

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aging and durability of aircraft in both the military and civilian sectors are becoming major issues as the existing fleet continues to age. Additionally, the increased use of composite structures in the civilian fleet, such as in the Boeing 787 Dreamliner and the Airbus A380, make the understanding and/or improvement of composite durability, particularly durability of repairs, even more critical. Several areas have been identified as targets for improvement in composite aircraft repair. These include the development of rapid, low temperature repair methods and associated materials as well as development of the quality of repairs when they are made. Adhesion of bonded repairs is one area that needs to be addressed. Adherent Technologies, Inc. is proposing a novel moisture-resistant primer system for use in repairs of standard carbon/epoxy composites used in many subsonic aircraft. Our proprietary chemistry comprised of a reactive coupling agent and a carrier resin compatible with standard aerospace epoxy resins bonds directly to the prepared aircraft composite surface while retaining residual functionality that can be cured directly into the matrix of the repair leading to a covalently bound repair, thereby strengthening the repair interface. Proper selection of the coupling agent structure and carrier resin can serve to further enhance the moisture resistance and thereby durability of the composite repair.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This system is being designed to support the need for improvements in durability of repairs for subsonic aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed primer technology, which will improve the quality of composite bonded repairs as well as composite bonding in general, will used throughout the aerospace composite materials market as well as having potential applications in civilian infrastructure (e.g. CFRP bridge decks and the like). The civilian aircraft market is projected to be a particularly significant consumer.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Emerald Sky Technologies, LLC
6106 Hour Hand Court
Columbia, MD 21044-4702

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Fritz
steven.fritz@comcast.net
6106 Hour Hand Court
Columbia,  MD 21044-4702

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With aircraft automation increasingly able to control flight autonomously, situational awareness and engagement of the crew can suffer. To improve aviation safety further we need new paradigms to balance between exploiting increasingly powerful technologies and retaining and promoting aeronautical decision making (ADM) by the crew. This proposal explores integrating H-mode, a flight control system developed by researchers at the NASA Langley Research Center (LaRC) that shares workload with pilots to leverage the unique capabilities of human pilots and automated control systems, with OZ, a primary flight display system under development at eSky. OZ provides a single-screen display for IMC flight, mapping external objects such as airports, waypoints, air traffic, weather etc. onto the primary flight display. The hybrid system (H/OZ) will allow the pilot both to retain situational awareness and to monitor the flight and select alternative actions at critical points. H/OZ will marry the superior situational awareness capability of OZ with the superior cooperative flight control of H-mode. In phase 1, eSky will develop a design for H/OZ and explore the feasibility of key new design elements. eSky will map the user interface of H-mode into the OZ display and add functionality to both. In collaboration with LaRC, the Florida Institute for Human & Machine Cognition and the University of Maryland, eSky will identify specific areas critical to the performance of H/OZ and use rapid prototyping to evaluate the usability of the new design elements. New OZ functionality will be evaluated using an eSky OZ laptop simulator. H-mode prototyping will be done in the NASA LaRC H-mode simulator. Feasibility will be tested by demonstrating that the OZ display metaphor supports full H-mode functionality without compromising the usability of the H-mode user interface. Phase 2 will focus on creating an H/OZ simulator and on usability and performance testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
H/OZ will be suitable as an integrated avionics suite for any aircraft or winged spacecraft. All aircraft operated by NASA will find the innovative OZ display and the cooperative flight control of H-mode useful in flight in both Instrument Meteorological Conditions (IMC) and Visual Meteorological Conditions (VMC).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
H/OZ is being developed as an integrated avionics suite primarily general aviation. OZ has already been demonstrated to be superior to conventional instrumentation and the new "glass cockpit" technology such as the Garmin G1000 currently being supplied with general aviation aircraft. The hybrid H/OZ system will add cooperative flight control to maintain superior situational awareness on the part of pilots. This will be of primary importance during single pilot IFR flight when high workload and stress induced by external factors can compromise situational awareness and thus flight safety. H/OZ can also be successfully applied to air transport and military aircraft. In these aircraft types electronic displays are well-established but continue to rely on images of 1920's aircraft instruments and high levels of conventional flight control automation.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Intelligence
Attitude Determination and Control
Guidance, Navigation, and Control
Pilot Support Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ThinKom Solutions, Inc.
3825 Del Amo Blvd., Suite 200
Torrance, CA 90503-2168

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Henderson
billh@thin-kom.com
3825 Del Amo Blvd., Suite 200
Torrance,  CA 90503-2168

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed project will investigate the feasibility of utilizing ThinKom's low cost electronically scanned array (ESA) antenna concepts to enable affordable airborne hazard detection and avoidance radar systems with greatly enhanced performance relative to those currently deployed. This technology is comprised of a unique integrated feed/phase shifter/radiator topology that can be realized using very low cost manufacturing techniques and COTS electronics. Although it utilizes a densely spaced array of discrete radiators that allows the "grating lobe free" operation of traditional high cost phased arrays, the architecture is amenable to "quasi-monolithic" construction from a small number of inexpensive parts. It also enables the use of a highly reliable, low cost, low power consumption beam steering controller. The estimated total loss through the feed, phase shifter, and radiator is less than 1 dB at X-Band. The Phase I program will focus on creating a design for a small proof-of-concept (POC) ESA, and on doing a hardware demonstration of the phase shifter architecture. When fabricated under a Phase II program the POC unit will demonstrate the revolutionary cost reduction potential of this technology.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology is useful for a broad variety of radar and communication applications that are of interest to NASA. In addition to aviation hazard detection, other relevant radar applications include ground mapping, atmospheric studies, and launch range surveillance. Regarding RF communication, it is potentially useful whenever a highly directional steerable beam is required. This includes many distinct "on-the-move" communication systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Some of the potential Non-NASA applications include: 1. Radar systems for unmanned aerial vehicles (UAVs). 2. Active protection radar for military ground vehicles. 3. Landing aid radar for commercial and general aviation 4. Weather/collision avoidance radar for commercial and general aviation. 5. Automotive collision avoidance. 6. Point-to-Multipoint data links for LANs and MANs. 7. Self-aligning point-to-point data links and SatCom antennas. 8. Air-to-Air and Air-to-ground communication links. 9. SatCom on-the-move for both ground and airborne vehicles. 10. Perimeter surveillance radar (e.g. for homeland security or border control). 11. Long Range surveillance radar (e.g. for ballistic missile defense).

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Airport Infrastructure and Safety
Guidance, Navigation, and Control
Pilot Support Systems
Microwave/Submillimeter

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimal Synthesis, Inc.
868 San Antonio Road
Palo Alto, CA 94303-4622

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
P. K. Menon
menon@optisyn.com
868 San Antonio Road
Palo Alto,  CA 94303-4622

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Estimation of aerodynamic models for the control of damaged aircraft using an innovative differential vortex lattice method tightly coupled with an extended Kalman filter is proposed. The approach exploits prior knowledge about the undamaged aircraft to reduce the order of the estimation problem. Test maneuvers will be designed to improve the observability of the system dynamics. The derived performance model will then be used to determine the aircraft flight envelope, performance parameters and the maneuver limits. The objective is to develop an aircraft performance model online to permit the derivation of viable landing guidance laws for damaged aircraft. Phase I research will demonstrate the feasibility of the proposed concept using a NASA-supplied aircraft simulation. Complete aircraft performance estimation system will be developed during the Phase II research and evaluated in real-time, high-fidelity simulations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research will contribute towards NASA's Integrated Resilient Aircraft Control program.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed research will provide a systematic methodology for the guidance and control of damaged aircraft. Algorithms and software developed under the proposed SBIR work will contribute towards improving the safety of military, commercial and general aviation aircraft operations.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Scientific Systems Company, Inc.
500 West Cummings Park, Suite 3000
Woburn, MA 01801-6503

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jovan Boskovic
jovan@ssci.com
500 W. Cummings Park
Woburn,  MA 01801-6503

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The main objective of this project is to develop and test a novel innovative Integrated Reconfigurable Aero & Propulsion Control (IRAP) system that achieves flight safety improvement in commercial aircraft. The main feature of the proposed IRAP system is that it is well suited for uncertain plants containing actuators operating on different time scales. The focus under this project is on the flight control system design for aircraft with fast actuators moving the flight control surfaces, and engines characterized by a slower response. The IRAP system will be developed for operation under faults, failures, damage and other upsets. The technique that will be used to achieve the related reconfigurable control objectives is referred to as the Sequential Signal Filtering for Certainty-Equivalence Adaptive Control (SSF-CEAC). Specific Phase I tasks include: (i) Problem formulation; (i) Adaptive control design for the case of aero-only control; (ii) Adaptive control design for the case of propulsion-only control; (iii) Integrated reconfigurable aero & propulsion control design; and (iv) Performance evaluation of the IRAP system. In collaboration with Boeing Phantom Works, in Phase II we plan to pursue extensions of the proposed approach to MIMO nonlinear models, further development of control allocation strategies, pilot interface design, integrated adaptive control design for safe landing under severe failures and damage using engines only, and IRAP software toolbox development.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
One of the important problems under the NASA Flight Safety Program and one of the main goals of Integrated Resilient Aircraft Control (IRAC) component is to provide aircraft stability, maneuverability, and safe landing in the presence of adverse conditions. The proposed IRAP system addresses all three features by assuring aircraft stability under severe flight-critical faults, failures and damage, minimizing the effect of the failures on the flight control system, and assuring safe landing under upsets and external hazards. Hence the proposed work is expected to have important impact on safety improvements for aerospace vehicles arising within the framework of the NGATS and Space Exploration systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include Unmanned Aerial Vehicles (UAV) that are also characterized by fast flight control actuators and slow engines, commercial space vehicles, and other vehicle systems whose actuators operate on different time scales.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Scientific Monitoring, Inc.
8777 E. Via de Ventura Drive, Suite 120
Scottsdale, AZ 85258-3345

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Asif Khalak
asif@scientificmonitoring.com
8777 E. Via de Ventura Dr., Suite 120
Scottsdale,  AZ 85258-3345

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed effort will combine a low cost physical modeling approach with inductive, data-centered modeling in an aerosopace relevant context to demonstrate effective, low cost data mining. In particular Phase I will evaluate various hybrid architecture concepts on the basis of false positive and fasle negative rates. The approach will use domain decompostiition to partition the physical platform under consideration into regimes appropriate for either model based or inductive based apoproaches.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Scientific Monitoring, Inc already offers a physical model driven, proprietary product called i-Trend. The i-Trend product provides sophisticated diagnostic and trending analysis to high value physical systems. Specific application areas include aerospace vehicles of all types, gas turbine and rocket engines, and aerospace subsystems. Combining an Inductive Monitoring System with i-Trend will provide enhanced features that will enable the hybrid system to address high value physical systems that are not easily modeled using conventional, physics based models. Such systems will include advanced aerospace structures and systems with substantial human interaction, as well as human physical performance and health monitoring of astronauts and pilots.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Scientific Monitoring, Inc already offers a physical model driven, proprietary product called i-Trend. The i-Trend product provides sophisticated diagnostic and trending analysis to high value physical systems. The i-Trend product, originally developed under a USAF SBIR, has already found commercial application as it is used by a leading aerospace firm to provide diagnostic and maintenance support to major airframe subsystems. Specific Non-NASA application areas include various land based transportation vehicles of all types, power generating systems and industrial manufacturing systems. Combining an Inductive Monitoring System with i-Trend will provide enhanced features that will enable the hybrid system to address high value physical systems that are not easily modeled using conventional, physics based models. Such systems will include advanced manufacturing systems or new structures and systems with substantial human interaction, as well as human physical performance and health monitoring.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Airport Infrastructure and Safety
Pilot Support Systems
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Expert Systems

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Trenkle
jtrenkle@michiganaerospace.com
1777 Highland Dr., Suite B
Ann Arbor ,  MI 48108-2285

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In response to NASA SBIR topic A1.05, "Data Mining for Integrated Vehicle Health Management", Michigan Aerospace Corporation (MAC) asserts that our unique SPADE (Sparse Processing Applied to Data Exploitation) technology meets a significant fraction of the stated criteria and has functionality that enables it to handle many applications within the aircraft lifecycle. SPADE distills input data into highly quantized features and uses MAC's novel techniques for constructing Ensembles of Decision Trees to develop extremely accurate diagnostic/prognostic models for classification, regression, clustering, anomaly detection and semi-supervised learning tasks. These techniques are currently being employed to do Threat Assessment for satellites in conjunction with researchers at the Air Force Research Lab. Significant advantages to this approach include: 1) completely data driven; 2) training and evaluation are faster than conventional methods; 3) operates effectively on huge datasets (> billion samples X > million features), 4) proven to be as accurate as state-of-the-art techniques in many significant real-world applications. The specific goals for Phase 1 will be to work with domain experts at NASA and with our partners Boeing, SpaceX and GMV Space Systems to delineate a subset of problems that are particularly well-suited to this approach and to determine requirements for deploying algorithms on platforms of opportunity.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MAC's SPADE data mining system has a large potential market in both government and civil aviation as well as for other arenas with costly and complex vehicles such as marine craft. The need for next-generation data mining tools for aid in lifecycle issues for aircraft/spacecraft/satellites/ships is now widely recognized by both the private and public sectors, as exemplified by the scope of the solicitation for this program. The techniques used by MAC are amenable to deployment on any platform of opportunity including Clusters, airborne platforms, Laptops, FPGAs, Graphical Processing Units (GPUs), and others depending on the needs of the application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The data mining techniques embodied in MAC's SPADE system have a broad commercial market. Potential arenas include: data fusion approaches to computer network security, intelligence, and public health monitoring; real-time quality control and damage detection for continuous physical processes (chemical & pharmaceutical plants, manufacturing facilities); text stream monitoring for news, email, IMs; financial event detection – monitor accounting or investment portfolio management systems to detect unexpected classes of price or cost changes which may signify problems; sales opportunity/threat identification – detect inter-product sales relationships, fad identification, competitor's pricing changes, seasonal and geographic changes; insurance claim monitoring for fraud; micro-climate change monitoring using digital imagery; gene expression profiling for medical diagnosis and understanding of diseases; proteomic data analysis and pattern recognition for medical diagnosis and biomarker discovery, and numerous other high-profile segments in which this system could be invaluable.

TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data Management
Autonomous Reasoning/Artificial Intelligence

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Acellent Technologies, Inc.
835 Stewart Drive
Sunnyvale, CA 94085-4514

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Amrita Kumar
akumar@acellent.com
835 Stewart Drive
Sunnyvale,  CA 94085-4514

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
New engine fan blade containment structures are being manufactured with advanced composite structures such that they can withstand blade-out events. The use of advance composites requires the understanding of the possible effects of aging degradation on the performance of "hard wall" or "soft wall" composite fan containment structures to ensure durability in their use in jet engine applications. Acellent Technologies, Inc. proposes to develop an innovative, low-cost and reliable system for assessment of the integrity of composite fan containment structures that will automatically monitor in real-time the location and extent of damage in the containment structure. The system will utilize a network of miniature sensors integrated with the structure to scan the entire structural area for any impact events, resulting structural damage and monitor degradation due to usage. Phase I will focus on developing a prototype of the system and demonstrating functionality to detect damage both on the inner and exterior surface of the fan containment structure.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system directly the need for inspection of fan containment composite structures and it is expected that once developed, the proposed system will provide the following advantages over current inspection techniques: · Low-cost built-in reliable damage detection system for monitoring of containment structure integrity · Improved personnel safety · Improvement of fan containment structure reliability · Ease of installation · Reduction of labor time · Real-time convenience and automation of inspection during service

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Since nearly all in-service composite structures require some form of inspection and maintenance procedures to monitor their integrity and health condition to prolong life span or to prevent catastrophic failures, the potential applications of the proposed system are very broad. In the future, this system can potentially be used to monitor all types of composite structures on aircraft and spacecraft.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Perception/Sensing
Airframe
Spaceport Infrastructure and Safety
Thermal Insulating Materials
Structural Modeling and Tools
Tankage
Airport Infrastructure and Safety
Sensor Webs/Distributed Sensors
Ceramics
Composites
Multifunctional/Smart Materials
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Picometrix, LLC
2925 Boardwalk Drive
Ann Arbor, MI 48104-6765

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Zimdars
dzimdars@picometrix.com
2925 Boardwalk
Ann Arbor,  MI 48104-6765

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to demonstrate key elements of feasibility for a high speed automated time domain terahertz computed axial tomography (TD-THz CT) non destructive evaluation (NDE) system which would provide true three dimensional images of aerospace composite structures. Traditional time domain terahertz reflection tomographic imaging captures only a single view of an object, generating images of laminar structure similar to an ultrasound "B-Scan". This reflection tomographic imaging is limited, however, in revealing only the laminar structure which presents a clear specular reflection from each interface. Furthermore, traditional time domain terahertz reflection tomographic imaging has substantial difficulty in determining the layer index of refraction an absorption properties without ambiguity. We propose to overcome these limitations by utilizing true computed axial tomographic reconstruction of the images. This method acquires not one view, but many radial axial views, generating a sinogram which can be used to reconstruct images using a derivative of standard X-Ray CT filtered back-projection. The sinogram can be generated by the transmission absorbance, transmission time of flight, and, in principle, reflection measurements. The reconstructed TD-THz CT images are 3D maps of the absorption coefficients and/or the index of refraction of the subsurface material.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed TD-THz CT NDE imager will be valuable in characterizing the aging and durability of aircraft and spacecraft materials and components. Material examples include Kevlar, Zylon, and other non-conductive polymer matrix composites. Example NDE applications where these materials are used include inspection of soft shell fan containment, thermal protection systems, and composite overwrap pressure vessels. These materials are in systems in which the 3D internal examination of new construction for flaws (voids, disbonds, inclusions, improper geometry and dimensions, and incomplete curing) may be critical. It will be critical to periodically inspect systems for damage, fatigue and chemical degradation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Polymer matrix composites are used in automobile and ships and many other consumer and industrial products. TD-THz CT 3D imaging applications can include inspection of automobile dashboards, imaging inspection for delamination of printed circuit boards, inspection of pipe insulation, as well as with manufactured parts such as pure plastic and paper products. TD-THz CT imaging benefits homeland security applications under development such as personnel and luggage inspection for concealed weapons and explosives (in luggage, shoes, etc.). TD-THz CT imaging and spectroscopy can inspect items in shipment such as mail, cardboards packages, and plastic and wood crates.

TECHNOLOGY TAXONOMY MAPPING
Ablatives
Airframe
Airlocks/Environmental Interfaces
Controls-Structures Interaction (CSI)
Erectable
Inflatable
Kinematic-Deployable
Launch and Flight Vehicle
Thermal Insulating Materials
Modular Interconnects
Structural Modeling and Tools
Tankage
Portable Data Acquisition or Analysis Tools
Microwave/Submillimeter
Optical
Suits
Photonics
Ceramics
Composites
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Extreme Diagnostics, Inc.
2525 Arapahoe Avenue, Bldg. E4, #262
Boulder, CO 80302-6746

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Robert Owen
rowen@extremediagnostics.com
2525 Arapahoe Avenue / Bldg. E4 #262
Boulder,  CO 80302-6746

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR project delivers a single-chip structural health-monitoring (SHM) system that uses the impedance method to monitor bulk interiors and wave propagation methods to assess surfaces. This Three-Dimensional Health Monitoring (3DHM) unit supports nondestructive evaluation (NDE) systems and evaluates hard shell composites that include sandwich structures. Implications of the innovation Increasingly demanding weight and performance needs move manufacturers to the use of composite materials. New systems are needed to detect incipient damage in composites and identify aging-related hazards before they become critical. Three-dimensional health analyzers that actively examine both bulk interiors and large-scale surface areas address a major problem domain; however, no practical system exists. We address this deficiency by building on our existing SHM system. Technical objectives 3DHM leverages our previous NASA research in SHM. Our current prototype takes the form of a single custom printed circuit board, and is a TRL 5 unit. We have demonstrated bulk interior and limited surface area coverage in Boeing thermal protection system (TPS) tests and on wind turbine blades—both feature composite materials. We extend our surface coverage by adding wave propagation SHM. Our sensor validation includes computer modeling that generates virtual (simulated) data. Research description Phase 1 establishes feasibility for a single-chip approach that combines the impedance method and wave propagation, and demonstrates damage detection on a model composite. Phase 2 completes, validates and demonstrates single chip operation, and delivers an operational unit. Anticipated results Phase 1 establishes 3DHM feasibility by developing a detailed chip development and verification roadmap. Phase 2 delivers an operational unit that monitors and assesses bulk interiors and surfaces of hard shell composites that include sandwich structures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
3DHM directly supports NDE systems for safety assurance of future vehicles—specifically those making heavy use of composite materials and sandwich structures. There is a major effort within NASA, the FAA, and the military to develop integrated vehicle health management technology that utilizes SHM information for computer controlled recovery actions aimed at avoiding catastrophe. 3DHM provides enabling technology for this effort. 3DHM supports the NASA Engineering and Safety Center by providing tools for independent testing, analysis, and assessment of high-risk projects. 3DHM applications include on-wing SHM of various aircraft components including static structures (e.g., containment components, ducts, vanes, nozzles, etc.) as well as rotating components (e.g., disks, blades, and shafts). 3DHM in situ SHM technology is needed to improve aircraft safety and reliability by verifying structural integrity and nondestructively inspecting, monitoring, and assessing aircraft and aerospace propulsion systems for damage. 3DHM is applicable to the next generation of turbine engines. These advanced propulsion systems will use revolutionary materials and structures. Structures based on such materials must withstand severe stresses and hostile aero-thermo-chemical environments, while weighing less and operating at higher temperatures than current engines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications include Homeland Security structural analysis to mitigate threats (preparedness) and assess damage (response), smart structures, and SHM of civil infrastructures, land/marine structures, medical devices, and military structures. Civil infrastructure includes bridges, highway systems, buildings, power plants, underground structures, and windmills. Land/marine structures include automobiles, trains, submarines, ships, and offshore structures. Medical devices include implants and health monitoring devices. Military structures include helicopters, aircraft, unmanned aerial vehicles (UAV) and others. SHM is an emerging industry driven by an aging infrastructure, malicious humans, and the introduction of advanced materials and structures. SHM applications are also driven by a desire to lower costs by moving from schedule-based to condition-based maintenance. Government customers include NASA and the Departments of Defense, Transportation, and Energy. Non-government customers include energy companies, and other crucial-structure custodians. Westinghouse Electric Company (Nuclear Services Division) is our civilian commercialization partner. WEC sees 3DHM applications in nuclear power plant SHM, and provides engineering and marketing support at no cost.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Structural Modeling and Tools
Airport Infrastructure and Safety
Pilot Support Systems
Autonomous Reasoning/Artificial Intelligence
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Composites
Power Management and Distribution
Aircraft Engines

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Roemer
mike.roemer@impact-tek.com
200 Canal View Boulevard
Rochester,  NY 14623-2893

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Impact Technologies, in cooperation with Raytheon, proposes to develop and demonstrate an innovative prognostics approach for aircraft digital electronics. The proposed non-invasive prognostic approach consists of advanced software and a minimal sensing, focused on incipient fault detection, isolating failure modes and predicting remaining useful life using improved prognostic models. The innovations will include development and validation of physics of failure models, applicable to a broad range of CMOS digital systems; associated damage accumulation models; and a signal processing and feature extraction approach for detecting and isolating VLSI failure modes. In this approach, cradle-to-grave health state awareness is achieved through the use of model-based assessments in the absence of fault indications, and by updating these model-based assessments with sensed information. The PowerPC MPC7447 microprocessor will be used for validation testing during this program based on its use in such systems as the F-35 fighter Integrated Core Processor (ICP) and the fact that it is representative of the wide spread CMOS technology found in modern digital devices. Finally, a commercialization path beginning with testing of the technologies within Raytheon's Labs will be presented along with the team's vision of how e-Prognostic technologies can be transitioned into safety critical commercial and military digital.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA systems, ranging from flight controls to data and signal processing systems will benefit from these technological advancements. Any digital system incorporating Very Large Scale Integrated (VLSI) and Large Scale Integrated (LSI) CMOS technology can benefit from the developed technologies. These digital systems are used in computing, communications, data transport, and digital control systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of e-Prognostics for aircraft digital electronic boards will provide multiple benefits including: improved safety associated with system operations, reduced life cycle or total ownership costs, and increased availability of commercial and military systems. Furthermore, the work will contain many generic elements that are readily applicable to a wide range of related applications. The integrated e-Prognostic approaches, techniques, and specific algorithms could also be implemented in a wide range of ground-based and naval military applications, as well as in civilian commercial aviation applications (passenger aircraft, cargo transports, business jets, private aircraft, etc.).

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Computer System Architectures
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Extreme Diagnostics, Inc.
2525 Arapahoe Avenue, Bldg. E4, #262
Boulder, CO 80302-6746

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Robert Owen
rowen@extremediagnostics.com
2525 Arapahoe Avenue / Bldg. E4 #262
Boulder,  CO 80302-6746

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR project delivers an on-board structural health-monitoring (SHM) system with embedded sensors that sense mechanical impedance deviations to flag incipient damage in time to recover from or prevent in-flight failures. This Component Damage Mitigation (CDM) system integrates early damage detection with failure recovery measures such as self-healing fasteners. Implications of the innovation Next Generation Air Transport Systems bring increasingly demanding weight and performance needs that encourage aircraft to operate relatively close to their design limits—minor structural failure can mean rapid catastrophe. On-board sensing, diagnostic, and damage mitigation capabilities are needed for early correction of incipient damage. However, no practical system exists. We address this deficiency by building on our existing SHM unit and incorporating damage mitigation. Technical objectives CDM leverages our work in impedance-based SHM. Our current prototype consists of a single custom electronics board, and is a TRL 5 unit. We have demonstrated field operation in Boeing launch simulation tests and on full-scale wind turbine blades. We propose to integrate our current approach with damage mitigation measures and to create a practical single-chip solution. We include computer modeling that generates virtual data in our sensor validation. Research description Phase 1 establishes feasibility for a single-chip approach based on the impedance method, and demonstrates damage mitigation on a model self-healing fastener. Phase 2 completes and validates single chip development, integrates damage detection and mitigation, and delivers an operational unit. Anticipated results Phase 1 demonstrates damage detection/mitigation integration and provides a detailed chip roadmap. Phase 2 delivers an operational unit that performs integrated damage detection, monitoring, and mitigation in crucial propulsion system and airframe components.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There is a major effort within NASA, the FAA, and the military to develop Integrated Vehicle Health Management (IVHM) technology that utilizes SHM information for computer controlled recovery actions aimed at avoiding catastrophe. CDM provides enabling technology for this effort. CDM supports the NASA Engineering and Safety Center by providing tools for independent testing, analysis, and assessment of high-risk projects. CDM applications include on-wing SHM and damage mitigation of various aircraft components including static structures (e.g., containment components, ducts, vanes, nozzles, etc.) as well as rotating components (e.g., disks, blades, and shafts). CDM in situ SHM technology is needed to improve aircraft safety and reliability by verifying structural integrity and nondestructively inspecting, monitoring, and assessing airframes, aircraft systems, and propulsion elements for damage and health. CDM is integrated with damage mitigation and is applicable to the next generation of turbine engines. These advanced propulsion systems will use revolutionary materials and structures. Structures based on such materials must withstand severe stresses and hostile aero-thermo-chemical environments, while weighing less and operating at higher temperatures than current engines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications include Homeland Security structural analysis to mitigate threats (preparedness) and assess damage (response), smart structures, and SHM of civil infrastructures, land/marine structures, medical devices, and military structures. Civil infrastructure includes bridges, highway systems, buildings, power plants, underground structures, and windmills. Land/marine structures include automobiles, trains, submarines, ships, and offshore structures. Medical devices include implants and health monitoring devices. Military structures include helicopters, aircraft, unmanned aerial vehicles (UAV) and others. SHM is an emerging industry driven by an aging infrastructure, malicious humans, and the introduction of advanced materials and structures. SHM applications are also driven by a desire to lower costs by moving from schedule-based to condition-based maintenance. Government customers include NASA and the Departments of Defense, Transportation, and Energy. Non-government customers include energy companies, and other crucial-structure custodians. Westinghouse Electric Company (Nuclear Services Division) is our non-government commercialization partner. WEC sees CDM applications in nuclear power plant SHM, and provides engineering and marketing support at no cost. We are also working with Boeing and the United Space Alliance.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Tankage
Airport Infrastructure and Safety
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Reasoning/Artificial Intelligence
Sensor Webs/Distributed Sensors
Composites
Multifunctional/Smart Materials
Aircraft Engines

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced microcontrollers having digital signal processing features have enabled the capability to distribute on-board computation for remotely operated vehicles (ROVs). Distributed processing can result in a lighter weight avionics suite with improved performance, by locating data conversion units adjacent to the sensors and control actuators, and reducing EMI through minimization of the amount of interconnection wiring. The proposed work will leverage CDI's and AMDI's substantial prior experience in the development and operation of flight control avionics for ROVs in the design of a new system for supporting advanced research using these systems. The avionics suite to be developed consists of serially interconnected distributed nodes that may be programmed through a Matlab graphical interface to perform control and sensing functions in support of custom requirements from the research community. The flexibility of custom-configured distributed computing nodes for use in a research context ensures that "just enough" instrumentation and control is provided for the specific test requirements at hand. Phase I will provide risk reduction by demonstrating the operation of the subcomponent technologies, culminating in a simplified flight test of the avionics system. Phase II continuation will develop the complete system to support testing activities at a NASA research center of interest.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's use of small remotely operated vehicles, particularly unmanned aircraft, in research applications would benefit from the use of a lightweight, low-power avionics system for vehicle control and data collection. Use of the proposed distributed sensing and control network would reduce overall avionics system weight, permitting the use of additional sensors, alternate control features, or better performance of the vehicle from reduced weight operation. Having a convenient, user-friendly interface for system configuration control would expedite the planning and execution of experiments using the avionics suite installed in these vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed system to be developed here could support a variety of instrumentation and control needs for both commercial industry and defense applications. The ability to custom tailor the required control and instrumentation components would allow the system to optimize weight and power requirements to permit its use on a host of lightweight robotic systems and devices.

TECHNOLOGY TAXONOMY MAPPING
Integrated Robotic Concepts and Systems
Teleoperation
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Sensor Webs/Distributed Sensors
Highly-Reconfigurable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Coherent Technical Services, Inc.
46655 Expedition Drive, Suite 101
Lexington Park, MD 20653-5120

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ian Gallimore
Ian.Gallimore@goCTSi.com
46655 Expedition Drive, Suite 101
Lexington Park,  MD 20653-5120

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The use of UAVs has increased exponentially since 1995, and this growth is expected to continue. Many of these applications require extensive Research and Development; however, the need to fund development of the UAV often competes with funding intended for the end-user application. Therefore, off the shelf, low cost, easily configurable integrated avionics systems will significantly reduce the budget impact for UAVs yet will support the wide range of applications for their use. CTSi and Virginia Commonwealth University are proposing the use of an integrated VCU developed avionics package with a user configurable autopilot system that will meet the needs of a wide range of experimental test bed UAVs. The system will include: 1. The ability for the safety pilot to take direct control of the aircraft using an on-board fail-safe control switch 2. A built-in autopilot to provide return-to-home capability upon failure of the RF links, safety/ground pilot assistance in performing research maneuvers, and limited upset recovery 3. An open-architecture hardware design enabling customer upgrade of sensors, actuators, and data links 4. An open-architecture software design enabling push-button auto-coding of control algorithms direct from Simulink 5. A flexible architecture allowing customer-developed control laws to be executed on ground-based computers via uplink and downlink telemetry or onboard the aircraft using an optional Advanced Adaptive Flight Control Processor.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has many applications for Unmanned Vehicles as Research and Development tools. Our proposal describes one use as part of the NASA AirStar System. In this application our ASROV system provides NASA with an integrated avionics system that allows NASA to focus on their experimental research in flight dynamics, vehicle state assessment and automatic flight control. ASROV will allow NASA to quickly and easily update control laws, without tedious hand coding of the new software. The CTSi/VCU ASROV system is a modular, open-architecture hardware and software design that allows the customer to change or upgrade the avionics as needed depending on the specific application. This architecture can be used throughout NASA as an avionics/auto-pilot system that allows maximum flexibility for the user quickly and easily update components of the system, to meet the data quality requirements for their specific application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Government agencies such as DoD, DoT, NSA, and civil research and development entities such as Universities and defense contractors are all heavily invested in using UAVs for Research and Development. Companies such as Northrop Grumman, and Universities such as Virginia Commonwealth University and the University of Texas at Arlington have expressed interest in a low cost, reconfigurable open architecture UAV avionics system. Each of these entities have specific interest in the ability to rapidly change the platform control laws to meet the requirements of their specific application without having to request changes from the autopilot manufacturer. ASROV provides the ability to go from SIMULINK models to C/C++ code on an ASROV platform without ever having to go back to the autopilot manufacturer. This capability allows UAV operators to focus their funding and their development efforts on their application, instead of on developing a UAV Testbed.

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

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dario Baldelli
dario@zonatech.com
9489 E. Ironwood Square Dr.
Scottsdale,  AZ 85258-4578

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel approach is proposed for the suppression of the aircraft's structural vibration to increase the resilience of the flight control law in the presence of the aeroelastic/aeroservoelastic (AE/ASE) interactions. Currently aircrafts with non-adaptive control laws usually include roll-off or notch filters to avoid AE/ASE interactions. However, if changes in the aircraft configuration are significant, the frequencies of the flexible modes of the aircraft may be shifted and the notch filters could become totally ineffective. With the proposed approach, the flexible modes can be consistently estimated in real-time via system identification algorithm. The identified flexible modes information is sought to be injected to the adaptive control algorithm to update a set of pre-chosen basis functions, These are the key elements for the effectiveness of the proposed method. As a result, undesirable effects of elastic modes will be suppressed while the whole system stability being maintained. Two case/analysis scenarios will be considered. First, the feedforward filter topology will be mainly used to reduce any atmospheric induced structural vibration of the aircraft. Second, the adaptive feedback control is triggered to suppress any AE/ASE interactions, and prevent any possible Flutter/Limit Cycle Oscillation (LCO) of the actual flexible aircraft.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Being capable of on-line estimation/monitoring of the elastic modes of the aircraft, the proposed adaptive control technology can be automatically adjusted to attenuate any potential adverse aeroelastic/aeroseroelastic effects of an aircraft before a sustained limit cycle and vehicle damage are encountered. Hence, the proposed project will assist NASA in its goal to achieve an integrated flight control system resilient to failures, damage, and upset conditions unforeseen during the development of the aircraft's original control law.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed adaptive feedforward/feedback control framework will have extensive application in non-NASA commercial applications. Firstly, due to the potential Flight Control System (FCS) benefits from avoiding notch filters, the proposed methodology can be used by military and commercial aircraft manufacturers for new aircraft designs, modifications and upgrades. Secondly, it brings a variety of applications in other industries. Among others it can be mentioned: (1) Acoustic noise cancellation in headphone devices; (2) Reduction of the noise level for rotating fans in computer servers; (3) Suppression and/or attenuation of vibrations in large satellite structures; (4) Cabin noise reduction for the next generation executive transport aircraft, such as the Marcel Dassualt's Falcon 7X. The noise source can be associated with engine or gust noise; (5) Vibration suppression across the automotive industry, such as vehicle's engine vibration, adaptively tuning of the suspension in formula 1 racing cars, and so on.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Structural Modeling and Tools
Guidance, Navigation, and Control
On-Board Computing and Data Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CSA Engineering, Inc.
2565 Leghorn Street
Mountain View, CA 94043-1613

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Keas
paul.keas@csaengineering.com
2565 Leghorn Street
Mountain View,  CA 94043-1613

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
CSA Engineering proposes the design of an adaptive aeroelastic mode suppression for advanced fly-by-wire aircraft, which will partition the modal suppression function from the rigid-body Flight Control System (FCS). CSA is recognized as having world-class expertise in the areas structural dynamics, vibration control, and control-structure interaction. Phase 1 will leverage expertise in structural dynamics and system-identification to develop adaptive filtering algorithms which operate in both the spatial and time domains to identify/estimate key aeroelastic generalized (modal) DOF and suppress aeroservoelastic interactions while minimizing the degradation of phase margin with respect to the FCS. During Phase 1, CSA will develop an end-to-end aeroelastic aircraft dynamic model of appropriate complexity as well as related sensors and measurement systems which will support the adaptive mode suppression effort. Sensors and measurement systems will be evaluated concurrently with adaptive filtering algorithms with regard to convergence, stability, and robustness. Filter architecture parameterization and constraints will be investigated. The goal of this development is to partition the suppression of aeroservoelastic interactions separate from the rigid body FCS, enabling FCS design and configuration/adaptation to be independent of aeroservoelastic considerations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology will be applicable to manned and unmanned vehicles and will enable safe operation in the presence of large uncertainties, component failures and system changes. This research will enable the R&D of others who are working with NASA on adaptive flight control by addressing the area of aeroservoelasticity and allowing others to focus on other core flight control aspects.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ability to field adaptive fault-tolerant flight control systems will undoubtedly be of interest to developers of civil transport aircraft from the standpoint of improved ride quality and safety, especially if such technologies can readily be certified for such applications. Advances in adaptive flight control will serve future growth in air traffic in the US, continuing to reduce the fatal accident rate over time. Potential customers for CSA's algorithms, sensor subsystems and control systems are aerospace and defense companies with government often being the upstream customer.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Reasoning/Artificial Intelligence
Expert Systems

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced diagnostic systems have the potential to improve safety, increase availability, and reduce maintenance costs in aerospace vehicle and a variety of other mechanical system. Numerous recent research efforts have produced a variety of diagnostic algorithms that show significant promise, but to date advanced diagnostic approaches have seen rather limited use in operational air vehicle systems. One of the major hurdles to transitioning such systems to fleet vehicles is the lack of adequate verification and validation (V&V) approaches. Barron Associates and MUSYN propose a Phase I research effort to develop a V&V framework for diagnostic systems that combines novel analysis approaches with experimental techniques to provide high confidence in the performance of diagnostic techniques. Performance evaluation of diagnostic systems is currently based primarily on numerical testing approaches, which may be applied to both simulation results and actual experimental data. While such testing is extremely important and should form a key component of the overall V&V strategy, it is not adequate alone. This is because it is impossible to collect sufficient test data or even sufficient Monte Carlo simulation data to exhaustively cover the space of potential test conditions. To achieve reasonable confidence in the coverage of the V&V procedures, it is necessary to intelligently select Monte Carlo or experimental test points to target the regions of the test space that are most likely to reveal problems. The team will work to develop analysis approaches that can help to identify combinations of conditions (flight conditions, uncertainties, external disturbances, vehicle configuration, etc.) that are most likely to lead to inadequate performance of diagnostic algorithms. The team will also extend the existing CAESAR software tool for control law V&V to automate V&V of diagnostic systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed V&V approaches will be applicable to diagnostic algorithms applied to a wide variety of systems developed and operated by NASA. Many future air vehicles can be expected to employ diagnostic algorithms to monitor systems including actuators, sensors, engines, gearboxes, and structural components. Examples of such vehicles include commercial transports, unmanned observation and communications platforms, and research aircraft. Diagnostic algorithms will be particularly important in commercial transport aircraft, where safety is of the utmost importance, and in long endurance unmanned vehicles, which lack human operators to recognize and respond to failure conditions. In the unforgiving environment of space travel, diagnostic algorithms will also offer significant benefits. Even in orbital flight, providing assistance to a damaged vehicle is extremely difficult and the problem will only be compounded on journeys to the moon and mars. Diagnostic algorithms will be critical to timely identification and isolation of fault conditions so the appropriate corrective actions can be initiated promptly.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed V&V approaches will be applicable to diagnostic algorithms applied to a wide variety of systems developed and operated by NASA. Many future air vehicles can be expected to employ diagnostic algorithms to monitor systems including actuators, sensors, engines, gearboxes, and structural components. Examples of such vehicles include commercial transports, unmanned observation and communications platforms, and research aircraft. Diagnostic algorithms will be particularly important in commercial transport aircraft, where safety is of the utmost importance, and in long endurance unmanned vehicles, which lack human operators to recognize and respond to failure conditions. In the unforgiving environment of space travel, diagnostic algorithms will also offer significant benefits. Even in orbital flight, providing assistance to a damaged vehicle is extremely difficult and the problem will only be compounded on journeys to the moon and mars. Diagnostic algorithms will be critical to timely identification and isolation of fault conditions so the appropriate corrective actions can be initiated promptly.

TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aptima, Inc.
12 Gill Street, Suite 1400
Woburn, MA 01801-1753

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jamie Estock
jestock@aptima.com
1726 M Street, N.W., Suite 900
Washington,  DC 20036-4526

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The runway safety issue has been on the Most Wanted list of the National Transportation Safety Board since the list's inception in 1990. The FAA has responded by implementing two ground surveillance technologies at major U.S. airports to reduce the risk of runway incursions. However, both technologies route information through air traffic control (rather than directly to pilots), which significantly delays safe responses. Several flight deck technologies that communicate information directly to pilots are currently in development. However, there is a need for tools to rapidly test the technologies early in the design process and measure their impact on pilot performance prior to implementation. The Aptima/George Mason University team proposes to develop two technologies that can be used together or independently to evaluate performance of flight deck technologies aimed at improving runway safety. We will deliver a computational cognitive model (Adaptive Control of Thought-Runway Safety; ACT-RS) that realistically emulates pilot performance, thus reducing the need for human pilots early in the design process. In addition, we will deliver a measurement tool (Performance Measurement Engine) that can measure the impact of the flight deck technology on the performance of ACT-RS and human pilots, making it useful across the technology lifecycle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
ACT-RS and the PM Engine will be useful to NASA researchers within the Aviation Safety Program as tools that will allow them to: (1) assess the impact of flight deck technologies aimed at improving runway safety throughout the design lifecycle, (2) identify the underlying factors driving experience-based effects of technology implementation on pilot performance, and (3) assess performance in different conditions and scenarios by providing flexible modeling and software frameworks.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ACT-RS and the PM Engine will appeal to customers who are developing flight deck technologies aimed at improving runway safety and those who develop and conduct training for pilots on new flight deck technologies. Avionics developers can benefit by using the proposed tools to collect and provide objective data that is evaluative in terms of FAA regulations, policies, and standards. Airline Training Directors can also benefit by using ACT-RS and the PM Engine to understand the effects of new runway safety technologies and to develop training curriculum that prepares pilots for these changes.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
M4 Engineering, Inc.
2161 Gundry Avenue
Signal Hill, CA 90755-3517

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Myles Baker
myles.baker@m4-engineering.com
2161 Gundry Ave
Signal Hill,  CA 90755-3517

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
M4 Engineering proposes to develop a method of incorporating several analyses into one process and then optimizing the structure. This method will allow for significant weight savings of structural compoents by incorporating analyses for damage tolerance, and durability in the design phase. Damage tolerance analyses, especially, have been difficult to iterate on since it has been time consuming to create models of each damage condition. The proposed method will be a highly efficient and useful method in reducing weight of structures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA will find great use for this method as they deal with applications that are highly sensative to weight. This method is suitable for both aviation and spacecraft applications of which is NASAs buisness.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This proposed method is suitable for application outside of the NASA network. Aircraft manufacturers such as Boeing, Lockheed-Martin, and Airbus will find great use for this tool in applying weight savings techniques to their structures. In addition, the automotive industry will find significant use for this tool since structures with weight concern are also developed.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Composites
Metallics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Materials Research and Design
300 E. Swedesford Road
Wayne, PA 19087-1858

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Sullivan
brian.sullivan@m-r-d.com
300 E. Swedesford Road
Wayne,  PA 19087-1858

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The fatigue life of CMCs must be well characterized for the safe and reliable use of these materials as integrated TPS components. Existing fatigue life prediction models for composite materials may be classified into three different categories: a) fatigue life model (S–N curves), b) residual strength or residual stiffness model, and c) progressive damage model. Recently, a damage index and accumulation model has been developed by Liu and Mahadevan based on Tsai-Hill static strength failure criterion. Using this approach as a framework, MR&D is proposing to develop and verify a relatively simple and computationally manageable approach to the fatigue life prediction of fabric reinforced C/SiC composites for hypersonic vehicle load bearing thermal protection system designs. A combined experimental and analytical program is proposed to achieve the objective of the proposed Phase I effort. At the conclusion of Phase I, a TRL of 2 will have been achieved and progress towards achieving a TRL of 3 will have been made.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The technology developed here will directly support the design of existing and future NASA space exploration vehicles. A working model which successfully predicts the thermal and mechanical fatigue life of coated C/SiC components will enable confident predictions of the structural life of CMC TPS components. Such a tool would also enable inspection and maintenance schedules to be generated for C/SiC materials, using actual data from flown mission environments collected from integral health monitoring sensor systems. Thermal protection system (TPS) elements, ranging from thick leading edges to doubly-curved acreage TPS panels, to hot structure control surfaces, will all benefit from the proposed program, if successful. Additionally, the fatigue life prediction tools developed in the Phase I program, if successful, may support the development of any hot structure materials used on the Crew Exploration Vehicle and subsequent airframes required for the Mission to Mars.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed Phase I program will result in enhanced design expertise that ultimately can be used by Government agencies and other companies to design and manufacture high temperature composite thermal protection system (TPS) components. Additionally the high temperature composite TPS design knowledge gained by MR&D from the Phase I program will open new opportunities to provide design and analysis services. An example of this growth path is provided by a Naval Air Warfare Center CMC Repair Phase I SBIR that grew into a Phase III SBIR, which was responsible for $1,288,521 of MR&D sales for CMC design and development services as of January 2006.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Structural Modeling and Tools
Ceramics
Composites

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Todd Quackenbush
todd@continuum-dynamics.com
34 Lexington Avenue
Ewing,  NJ 08618-2302

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent advances have strengthened interest in supersonic cruise aircraft, though achieving economic viability for these vehicles will require dramatic improvements in cruise efficiency without excessively penalizing off-design performance. Optimization of inlet design offers a potent method for achieving these goals, and a range of flow control concepts are available that can provide an adaptive ability to minimize blockage, reduce boundary layer bleed, and mitigate adverse effects of flow distortion on inlet/engine stability. By exploiting high temperature smart materials technology, these concepts can be mechanized in robust, compact, and lightweight devices, enabling actuators suitable for the environment of supersonic powerplants. This effort will demonstrate the feasibility of applying High Temperature Shape Memory Alloy (HTSMA) technology to this problem, focusing initially on design and demonstration of variable geometry flow control devices for use in supersonic mixed compression inlets. The project will build on prior successful development of smart materials actuators, and will extend earlier work by incorporating new HTSMA materials as well as by exploiting recent insights into microramp and vortex generation devices. The project will include refinement and characterization of actuator-ready HTSMAs, development of design tools for aero/thermo/structural analysis of flow control concepts, and experiments on demonstrator-level implementations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
By providing foundational research on innovative concepts for propulsion system components for supersonic transport aircraft, the proposed effort will directly support a wide range of fundamental NASA goals in aeronautics. One key result of the effort will be extended development and characterization of highly promising HTSMA materials, a resource of great potential for high speed and/or high temperature applications in subsonic, supersonic, and hypersonic aircraft. In addition, the Phase I effort will lay the groundwork for enabling technology to provide integrated inlet/engine control to ensure safe, stable, and efficient operation for continuous flight above Mach 2. Also, the projected integrated aero/thermo/elastic models of actuator performance to be assembled and validated will assist the development of concurrent engineering tools for analysis and design of smart-materials-based propulsion flow control systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A successful Phase I/Phase II effort will open the door to prototype testing and eventual implementation of a HTSMA-driven adaptive flow control system. The most direct beneficiary would be next generation supersonic aircraft that could incorporate these robust, low-profile, low-power flow control devices to permit an optimal balance of improved engine/inlet performance and enhanced engine safety. Successful implementation in this application would also lead to spinoff developments in a number of actuation tasks, including follow-on control concepts for compressor and turbine stages in subsonic or supersonic engines that would directly benefit both civil and military systems. Supersonic cruise technology is also of interest to the U.S. Department of Defense agencies and the developments projected here would directly benefit numerous missile designs as well as both manned and unmanned aircraft systems.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Structural Modeling and Tools
Metallics
Aircraft Engines

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Wendell Rhine
wrhine@aerogel.com
30 Forbes Road, Building B
Northborough,  MA 01532-2501

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The push to hypersonic flight regimes requires novel materials that are lightweight as well as thermally and structurally efficient for airframes and thermal protection systems to increase safety and decrease system weight. The materials required must maintain their performance throughout the lifetime of the system, without degrading over time or with use. A critical component of the system is the thermal protection system required to maintain internal temperatures compatible with the airframe. Currently available thermal protection system (TPS) designs and materials are not capable of providing the level of protection required by NASA without a significant increase in TPS weight and volume. In addition, current concepts for insulation utilize approaches that add nothing to the structural efficiency of the vehicle, or are made from materials that add unnecessary weight to achieve the required thermal performance. Therefore, NASA needs new TPS concepts for hypersonic vehicles that will provide the highest level of thermal performance and can also be structurally integrated with the airframe rather than just add parasitic weight. For this SBIR effort, Aspen proposes to develop a multifunctional aerogel that could be used in structurally integrated thermal protection systems to improve vehicle safety and decrease system weight.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The multifunctional aerogel-based materials developed during this project will have applications as high temperature insulation and as lightweight structural components for integrated thermal protection systems for hypersonic aircraft and reusable launch vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The aerogels developed in this project would find applications for military hypersonic vehicles and as the insulation used for high temperature industrial processes. Lightweight structural aerogels would find applications as a component of composite sandwich panels that are both lightweight and insulating. Such panels could find many applications including uses in as fire barriers in buildings. Carbon aerogel also have applications such as catalyst supports and fuel cell electrodes.

TECHNOLOGY TAXONOMY MAPPING
Thermal Insulating Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
UES, Inc.
4401 Dayton-Xenia Road
Dayton, OH 45432-1894

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Young-Won Kim
ywkim@ues.com
4401 Dayton-Xenia Rd
Dayton,  OH 45432-1894

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary material and manufacturing limitations of gamma TiAl alloys include processing difficulties, requiring costly non-conventional processing requirements, and large lamellar grains, which reduces damage tolerance. We have developed a new class of TiAl-based alloys, called beta gamma, which would remove such barriers. Unlike existing gamma alloys, beta gamma alloys are designed such that the ductile â phase is adequate at elevated temperatures (for processing) but negligible at the anticipated use temperatures (for performance). The alloys also feature significant grain refinement and compositional homogeneity. This program is aimed to utilize such beneficial beta-phase distribution and microstructure features observed in small (0.7kg) samples into forged disks from medium size (25kg) ingots. The process-ability will be validated by employing a conventional forging process, and refined lamellar microstructures will be generated through usual alpha treatments. The significance of this innovation is that beta gamma alloy disks can not only be produced by conventional forging, but also show improvements in RT strength and ductility and may retain other attributes (density, creep and oxidation) of conventional gamma alloys.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Due to their low density (only 50% of those of superalloys), high temperature capability (up to 800<SUP>o</SUP>C for long-term use), and expected damage tolerance improvements, once the premised process-ability and engineering microstructures achieved, beta gamma alloys will eventually find their potential applications for rotational components, such as compressor rotors and disks, and other hot structures in future NASA advanced engines. With some adjustments of processing parameters and conditions, these alloys can be rolled into thin sheets relatively readily, which then can be used for thin-section hot structures such TPS and nozzle components.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
For the same reasons described above, there exist near future application opportunities for beta gamma in LPT components (blades and others) in future commercial aero engines and for high-pressure compressor (HPC) blades and vanes in advanced engines. These blades made of conventional gamma alloys are on the verge of being implemented in spite of their inferiority in processing and microstructure to those of beta gamma alloys. The rotors in future missile engines are a viable application area for beta gamma alloys. Some commercial automotive engines have used turbochargers made of conventional gamma alloys and a cost reduction is the only issue for exhaust valve applications. These are the ideal application areas for beta gamma alloys.

TECHNOLOGY TAXONOMY MAPPING
Metallics

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Durable, creep-resistant ceramic composites are necessary to meet the increased operating temperatures targeted for advanced turbine engines. Higher operating temperatures result in improved performance, fuel savings (higher efficiency) and reduced pollution. Silicon melt infiltrated ceramic composites have been identified as having a 2400F maximum use temperature, which does not take advantage of the highest temperature capability of the newest generation of near stoichiometric SiC fibers. Conversely ceramic composites containing a SiC matrix derived from chemical vapor infiltration have sufficient stability to take full advantage of the creep resistance of the fibers. For many applications, no existing matrix system for SiC-reinforced composites has sufficient through-thickness thermal conductivity at elevated temperatures to result in low thermally induced stresses; such that longer service life at higher temperatures can be achieved. This Phase I work will demonstrate a higher temperature melt infiltrated matrix that is stable to 2950F, and thus allows the full temperature capability of the latest generation SiC fiber reinforcements to be used. This higher temperature capability is combined with a significantly higher predicted elevated temperature thermal conductivity for the ceramic composite, which will reduce the thermally induced stresses on the material that often dominate the stress state on the material. The Phase I effort will produce ceramic composites with this higher temperature melt infiltrated matrix and perform both thermal and mechanical property evaluations at ambient and elevated temperatures to demonstrate the benefits of the system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Commercial applications for NASA include application in the hot gas path of turbine engines for supersonic aircraft. Specific components include turbine shrouds, combustor liners, and turbine vanes. Other applications for silicon carbide fiber reinforced composites include applications for advanced air-breathing propulsion systems for hypervelocity vehicles, hot structure, and actively cooled hot structures, as well as high temperature heat exchangers that can benefit from the higher operating temperatures and high temperature thermal conductivity.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial applications include application in military and potentially commercial turbine engines for aircraft, and land-based turbine components for power generation. Other applications that can benefit from the higher operating temperatures and high temperature thermal conductivity are catathermal combustion devices, heat exchangers, and radiant burners.

TECHNOLOGY TAXONOMY MAPPING
Launch and Flight Vehicle
Ceramics
Composites
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Reaction Systems, LLC
1814 19th Street
Golden, CO 80401-1710

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bradley Hitch
rxnsys@comcast.net
1814 19th Street
Golden,  CO 80401-1710

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Simulations of reacting flow in applications such as scramjet engines are currently limited in their utility or accuracy by the chemistry sub-models employed. Accurate chemistry models for hydrocarbon fuels are particularly problematic since the detailed kinetic mechanisms can be highly complex, essentially prohibiting obtaining a timely solution. Simpler global chemistry models, while tractable, are notoriously inaccurate except over narrow ranges of conditions. Reactions Systems therefore proposes to explore a new approach to capturing the detailed chemistry in a reduced multi-dimensional format that could combine the advantages of ISAT with recent RSLLC proprietary innovations in species reduction.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Increased accuracy and productivity of reacting flow CFD codes using realistic RP-1 type fuels would materially enhance the efficiency of the design process and ultimate performance of new hydrocarbon-fueled airbreathing engines and rocket engines for space access. If successful, the proposed innovation could also be applicable to modeling many other reacting flow situations such as rocket plumes or chemically-reacting endothermic fuels used for cooling of hypersonic vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Detailed chemical kinetic models are applicable to a wide range of gas phase chemical processes such as fuel autoignition, formation of toxics and air pollutants in combustion processes, modeling of catalytic processes, tailoring of industrial chemical processes, and in jet and rocket propulsion systems. Furthermore, these chemistry models are often run as subsets of models that describe flow and/or time dependent processes. While a number of problems in chemical kinetic modeling can be solved using global kinetics and simple thermodynamics, many require the use of detailed chemical kinetic models involving a large network of elementary reaction steps. These large networks of simultaneous elementary reactions are computationally expensive, and follow-on codes such as CFD codes are even more burdened by having large numbers of species to consider. Dramatically reducing the time and cost required to obtain accurate reacting flow simulations could allow much better optimization of the design and operation of many types of commercial equipment.

TECHNOLOGY TAXONOMY MAPPING
Chemical
High Energy Propellents (Recombinant Energy & Metallic Hydrogen)
Monopropellants
Database Development and Interfacing
Software Tools for Distributed Analysis and Simulation
Combustion
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Combustion Research and Flow Technology
6210 Keller's Church Road
Pipersville, PA 18947-2010

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Calhoon
calhoon@craft-tech.com
3313 Memorial Parkway S, Suite 108
Huntsville,  AL 35801-5375

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This effort entails the validation of a RANS turbulent scalar transport model (SFM) for high speed propulsive flows, using new experimental data sets and accompanying large-eddy simulation (LES) solutions. The SFM has been used to predict local values of the turbulent Prandtl and Schmidt numbers and also provides the rms scalar fluctuation values that are used with assumed PDF models for turbulent combustion. Performing the experimental work in unison with LES studies ensures that the two sets of data will be fully compatible, and may be used to support SFM model validation. Work to date indicates some deficiencies in the present SFM model for high speed mixing problems where the two streams have very different densities, which we will attempt to resolve in this program. PIV data for the transverse injection of hot air and helium/nitrogen mixtures into a Mach 3.5 stream will be obtained in unison with LES studies to yield scalar fluctuation data not readily obtained in experiments. SFM upgrades will be performed using this unified data. Experiments will be performed by Dr. Seiner and coworkers at U. Miss using a new 12"x12" trisonic tunnel and existing slot/round jet injector models.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A validated scalar fluctuation model (SFM) has potential post applications to support design optimization and concept evaluation for scramjet fuel injection systems, where use of current models does not provide the accuracy required, typically underestimating fuel/air mixing. Use of the SFM alleviates the need to somewhat arbitrarily specify values of Prandtl and Schmidt number, whose values have a first-order effect on predicted performance and hence on optimizing designs, and also provides the fluctuations needed to include in assumed PDF turbulent combustion models. Other NASA applications entail use of the SFM in improving the design of launch vehicles for thermal protection where plume heating effects in the base region are a major design issue, as well as many other applications involving fuel/air mixing and plume effects.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
From a DoD perspective, we are involved in Army and Air Force sponsored scramjet propulsive system design programs focusing on fuel injector optimization. Having a more reliable SFM will lead to better designs since the fuel/air mixing will be predicted more accurately. We are also involved in interceptor missile design activities supported by the Missile Defense Agency, where plume heating effects are problematic and are requiring the use of ablative shields. We require accurate estimates of plume afterburning which is directly related to plume/air entrainment rates and thus to turbulent Prandtl and Schmidt numbers. This work will provide us with a more accurate tool to support DoD, and, it will enhance our code licensing and prime contractor support activities since a validated SFM provides improvements in predictive capabilities for a broad variety of high speed mixing problems.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Fundamental Propulsion Physics
Simulation Modeling Environment
Testing Facilities

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aerodyne Research, Inc.
45 Manning Road
Billerica, MA 01821-3976

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Hsi-Wu Wong
hwwong@aerodyne.com
45 Manning Rd
Billerica,  MA 01821-3976

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this proposed SBIR project, we seek to implement the Adaptive Chemistry methodology in existing CFD codes used to investigate the emissions performance of gas turbine engine combustors. We will demonstrate the feasibility of integrating Adaptive Chemistry algorithms to current CFD codes. We will also further develop the Adaptive Chemistry method to take advantage of species reduction enabling even larger CPU speedups. The value of the technique is enhanced predictive capability and computational efficiency of existing CFD codes for reacting flows such as gas turbine engine combustion systems. The successful completion of this project will produce the first CFD numerical code that is able to model detailed chemical kinetics as well as fluid dynamics. The end results allow the user to easily and transparently control the balance between computational efficiency and solution accuracy.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
As a result of this project, an interface of Adaptive Chemistry to any generic reacting flow solver will be constructed. The techniques developed in this project offer a combination of high efficiency, low computational cost, and enhanced accuracy on the reacting flow simulation. The interface developed in this work will complement NASA's combustion research, and NASA's in-house combustion codes can be integrated with the techniques developed to enhance its efficiency and simulation capability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA application includes implementing Adaptive Chemistry into other commercial CFD codes. The technique developed in this project will potentially provide significant CPU speedups to current CFD codes. The predictive capability of existing CFD software will also be greatly improved to facilitate flow field simulations with more detailed chemistry included.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Combustion
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Energy Plus Ltd.
23342 South Pointe Drive, Suite E
Laguna Hills, CA 92653-1422

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vincent McDonell
mcdonell@erc-ltd.com
23342 South Pointe Drive, Suite E
Laguna Hills,  CA 92653-1422

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
For many applications involving liquid injection, the ability to predict the details of the breakup process is often limited due to the complexity of the two-phase phenomena. Likewise, the ability to experimentally characterize these phenomena is also limited due in part to the need to rely upon visualization tools which are inherently qualitative. As a result, the ability to validate predictions using these diagnostic tools is also limited. In recent years, visualization diagnostics have evolved substantially in terms of spatial and temporal resolution. The advancements, coupled with a tool to conveniently quantify the results obtained relative to the breakup process offer the potential for a marked increase in understanding of this phenomenon. The proposed effort will develop such a tool that will be applied initially to the problem of liquid injection into a crossflow. The typical characteristics associated with this type of liquid breakup, such as column flattening, bending, fracture point, dynamics, etc. will be automatically quantified using the tool proposed. The project will utilize existing results obtained with state-of-the-art high speed imaging.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The project will result in a novel experimental technique that can be applied to existing and new imaging based diagnostic available at NASA. As applied to various two-phase flow problems, the tool developed will facilitate CFD validation as well as increased understanding of the breakup of liquids for a variety of applications. The tool is particularly well suited for quantitative comparison of experimental results with predictions from advanced simulation techniques such as LES and/or VOF or other high fidelity phase interface tracking methods. ERC will work closely with NASA to focus the Phase I efforts on areas/imaging problems of immediate interest to NASA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The product produced by the proposed project will be of interest to end users of advanced high speed imaging systems that are currently being applied to liquid injection problems. It will also be of interest to those using CFD calculations coupled with experiments. As a result, the potential for deployment of the product within software provided by vendors of advanced imaging systems as well as CFD vendors is significant. The understanding provided through this efficient analysis tools can potentially lead to breakthroughs in models for liquid breakup phenomena which can then be applied in a wide variety of applications involving liquid injection/application.

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
Simulation Modeling Environment
Portable Data Acquisition or Analysis Tools
Software Tools for Distributed Analysis and Simulation
Combustion
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Energy Plus Ltd.
23342 South Pointe Drive, Suite E
Laguna Hills, CA 92653-1422

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vincent McDonell
mcdonell@erc-ltd.com
23342 South Pointe Drive, Suite E
Laguna Hills,  CA 92653-1422

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As air-breathing combustion applications advance, increased use of fuel for cooling, combined with cycle advancements, leads to a situation where the fuel can become superheated. While this can lead to potential benefit in terms of the eventual fuel injection process, with enhanced atomization and evaporation, it creates a significant challenge relative to any computational design tools that might be used in these systems. Dealing with the superheat behavior in the injection of a liquid fuel requires substantially more physical phenomena to be accounted for compared to a subcooled system. As a result, detailed data and models for this behavior as encountered in practical fuels are needed in order to validate and evolve the models needed. In the work proposed, emphasis will be given to the injection of a plain liquid jet under superheated conditions. In Phase I the behavior of the liquid internal to the injector will be addressed, with both models and experiments carried out. The models evolved will be incorporated into an existing simulation environment developed by ERC for atomization of liquid jets. In addition, data will be available for CFD validation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
For Aerospace applications, development of fuel injection schemes that involve fuel superheat will be enhanced by model construction and validation resulting from the proposed project. Both standalone modeling tools and models for incorporation into a CFD environment will result from the project. NASA design tools will be enhanced in general and any simulation platforms needing to incorporate superheated fuel behavior will benefit in particular.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The project outcomes will be applicable to any application in which superheated fuels are involved. The main products in this regard are data and models which can be incorporated into larger design tools for these liquid injection systems. The standalone design tool can be used for assisting design of liquid injection systems using superheated fuels.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Feed System Components
Portable Data Acquisition or Analysis Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Combustion
Aircraft Engines

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryan Bergeron
bergeron@psicorp.com
20 New England Business Center
Andover,  MA 01810-1077

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Physical Sciences Incorporated (PSI) and United Technologies Research Center (UTRC) propose to develop, characterize, and evaluate the performance of innovative nanocatalysts that are homogeneously dispersed (0.01 % - 0.1 % by wt.) within a synthetic endothermic hydrocarbon fuel for ramjet, scramjet, and Rocket-Based Combined-Cycle (RBCC) applications. Coke build-up will be significantly reduced since the catalyst will be expelled with the product gases and liquids from the cracking system into the combustion zone. Increased cracking efficiencies will result using the nanocatalyst due to the higher surface area/volume and dramatically enhanced settling times compared to conventional microcatalysts. As a result, higher heat sinks due to endothermic cracking will be obtained. The reaction product distribution and efficiencies of the nanocatalytic hydrocarbon cracking reaction will be measured using standard chromatography methods. Use of the alternative synthetic fuel is advantageous due to its low sulfur content, high thermal stability, high endotherm, and production through a non-petroleum based reaction. In Phase II, new nanocatalysts will be synthesized, characterized, and tested. Catalytic efficiency will be optimized. The implications of the nanocatalyst on combustion performance will be evaluated. This program comprises TRLs 1 through 3 within Phase 1.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
We believe that the proposed nanocatalysts will lead to significant improvement for propulsion systems that rely upon cracking of synthetic endothermic fuels. The novel catalyst may also act as a reaction site for liquid propellant combustion in air-breathing and conventional systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
DoD and DoE could benefit significantly from advances in hydrocarbon cracking. For example, AF has complementary ongoing programs using synthetic endothermic fuels, and is currently positioned to test the new X-51 WaveRider. Homogeneously dispersed catalysts in crude and processed bio-oil could yield new approaches to produce alternative energy for DoE/DoD, particularly in commercial markets such as the automotive and heating industry.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Renewable Energy
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ATA Engineering, Inc.
11995 El Camino Real
San Diego, CA 92130-2566

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Parthiv Shah
parthiv.shah@ata-e.com
11995 El Camino Real, Suite 200
San Diego,  CA 92130-2566

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel quiet engine air-brake is proposed in response to NASA's solicitation for concepts for active and passive control of noise sources for conventional and advanced aircraft. The air-brake concept is applicable to 1) next-generation, conventional tube and wing aircraft (current generation +1) and 2) advanced integrated airframe/propulsion system configurations (current generation +2), and could enable system level noise reductions of several decibels at the ground observer during approach by quietly generating drag equivalent to up to three turbofan-sized bluff bodies per powerplant. Such drag generation could enable slower, steeper approach trajectories with reduced need for drag generators such as flaps, slats and undercarriage. Proposed research tasks build upon a rigorous understanding developed by the investigating team on the aero-acoustics of drag generating, swirling exhaust flows. The objectives are to 1) create an engine air-brake design specification to constrain the design and identify and address issues and challenges associated with implementation, 2) perform trade studies on two aircraft/powerplant combinations in current generation +1 and +2 configurations to identify the attributes of suitable devices installed on such aircraft and 3) develop a candidate design for model scale aerodynamic and aeroacoustic validation in an experimental facility. The deliverable will be a written report presenting a conceptual design of a model-scale engine air-brake and proposed test plan for Phase II validation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The most immediate opportunity for this system is to assist NASA in the development of next generation quiet aircraft, including tube and wing (current generation +1) and integrated airframe propulsion system configuration (current generation +2). These aircraft are likely to have noise sources from the engine and airframe that have comparable levels at approach. A quiet air-brake device will allow noise reduction by creating drag without the associated unsteady flow structures of devices such as flaps, slats, and undercarriage. In addition these devices will enable steep approaches, thereby locating the noise source further from the affected communities. An additional application for swirling exhaust flows is in the area of wake vortex avoidance and induced drag management. For example, swirling outflow devices placed on wing tips could be used to swirl in the opposite or same direction to the bound vortex that is shed by a finite wing, resulting in potential induced drag reduction or increase (possibly of value in a quiet drag sense).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial potential for this system extends beyond NASA's development programs related to next-generation quiet aircraft. The larger, shorter term market potential relates to engines which are currently being developed for commercial deployment in the next five to ten years by large-engine manufacturers where there is potentially still an opportunity to incorporate features of this concept into the final design. Another significant commercial opportunity is the development of a version or versions of the concept proposed here which can be retrofitted to existing or legacy engines to allow them to continue to operate under the more stringent future noise requirements.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Aircraft Engines
Aerobrake

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
There are several ongoing challenges in non-contacting blade vibration and stress measurement systems that can address closely spaced modes and blade-to-blade variations (mistuning). Traditional NSMS systems are applicable but have limitations due to the undersampling that is inherent in time-of-arrival data processing and the uncertainty that is introduced by inferring, as opposed to calculating, the mode of vibration. Based on Navy SBIR research, MSI is developing a radar-based blade vibration measurement system with the following capabilities: •Provides a continuous time series of blade displacement data over a portion of a revolution (solving the undersampling problem). •Includes data reduction algorithms to directly calculate the blade vibration frequency, modal displacement, and vibratory stress (solving the mode inference problem). •Uses a single sensor per stage to monitor all of the blades on the stage. The goals for the proposed project are to design and construct an innovative blade vibration measurement system with resolution capable of characterizing mistuning parameters and closely spaced modes of vibration. Development and demonstration of such a system will provide substantially superior capabilities to current blade vibration technology. Phase I demonstration testing will be conducted in MSI's laboratory with an existing instrumented compressor rig.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Improvements in blade vibration measurement capability will significantly reduce the cost and risk of development and operation of gas turbine engines. The potential applications include any turbine engine ranging from gas turbine propulsion engines to industrial steam turbines used for power generation. However, commercialization to existing NSMS users is the most direct and near term path. The costs associated with maintenance, downtime, and readiness are already well established and understood by both military and industrial users, so an improved NSMS would be attractive to many types of customers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Successful project completion addresses two of the commercialization hurdles that face current NSMS technology especially for new users – physical complexity and technical complexity. By characterizing closely spaced modes and mistuning parameters, and needing only a single sensor per stage, this project will lower the barrier to entry for new NSMS users. This will serve to widen the user base and help insure the successful commercialization of this technology for both civil and military aircraft as well as for industrial turbomachinery.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
On-Board Computing and Data Management
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
M4 Engineering, Inc.
2161 Gundry Avenue
Signal Hill, CA 90755-3517

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kevin Roughen
kroughen@m4-engineering.com
2161 Gundry Avenue
Signal Hill,  CA 90755-3517

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
M4 Engineering proposes to develop a generalized reduced order model generation method. This method will allow for creation of reduced order aeroservoelastic state space models that can be interpolated across a range of flight conditions. This development will be a significant advance to the process of control law development, especially in the design of control systems required to provide flutter suppression, gust load alleviation, and ride quality enhancement. The proposed technique will be an excellent compliment to modern linear and nonlinear aeroservoelastic analysis methods.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The first NASA application is the ASM program, which is currently a subject of ASE control law development at M4 Engineering. It is also expected that this technology will be directly applicable to the research projects planned in the Aeronautics Research Mission Directorate (ARMD). The multidisciplinary nature of the technology makes it an ideal candidate for use any time a very high performance vehicle is designed, where interactions between components, disciplines, and the control system are important. Examples include future high efficiency subsonic aircraft, quiet supersonic aircraft, high-altitude, long-endurance aircraft, hypersonic aircraft, and next-generation launch vehicles (either airbreathing or rocket powered).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
M4 Engineering has active relationships with several prime contractors who are likely users of this technology. These include Boeing Phantom Works, Northrop Grumman, and Raytheon. These provide excellent commercialization opportunities for the technology. Active marketing to prime contractors and other specialty airframers (e.g., Aerovironment, General Atomics, etc.) will follow these applications. The framework software is expected to find wide application to many aerospace and non-aerospace products, as model reduction for control system development is a widely applicable concept. Examples include the medical engineering field, automotive, aerospace/defense, and alternative energy applications.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Structural Modeling and Tools
Attitude Determination and Control
Autonomous Control and Monitoring

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Flutter is a potentially explosive phenomenon that is the result of the simultaneous interaction of aerodynamic, structural, and inertial forces. The analytical prediction of flutter in the transonic regime requires high fidelity simulation models that are computationally expensive. Due to the computational demands, traditional uncertainty analysis is not often applied to flutter prediction, resulting in reduced confidence in the results. This Phase I research is aimed at exploring methods to reduce the previous computational time limitations of traditional uncertainty analysis. To dramatically reduce the computational burden of uncertainty analysis, Systems Technology, Inc. proposes to investigate both the coupling of Design of Experiment (DOE) and Response Surface Methods (RSM), and the application of robust stability techniques, namely ƒÝ-analysis. Using Reduced Order Models (ROM), the DOE/RSM and ƒÝ-analysis approaches will be compared to traditional Monte Carlo based stochastic simulation. The result of the Phase I program will be to demonstrate the utility of the core elements of the Aeroelastic Uncertainty Analysis Toolbox (AUAT). AUAT will contain multiple methods for addressing flutter uncertainty analysis, coupled with a state-of-the-art nonlinear aeroelastic code.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Enhanced predictive flutter boundaries using the Aeroelastic Uncertainty Analysis Toolbox will decrease the likelihood to test beyond the flutter boundary, thus decreasing the risk of unexpected flutter that may lead to catastrophic failure and thereby increasing flight safety. The software will be developed with the intent of being used for flight test planning. Rapid uncertainty analysis capability will be highly beneficial during aeroservoelastic flight tests to more accurately predict the flight envelope prior to testing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Applying the uncertainty analysis early in the design process will enable manufacturers to design high performance aircraft with expanded flight envelopes that are robust to uncertainties pertaining to aeroelastic phenomena such as flutter. Rapid uncertainty analysis capability will enable designers to evaluate a larger design space in less time, decreasing the amount of incremental flight testing, thereby reducing the cost of development.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Simulation Modeling Environment
Structural Modeling and Tools
Expert Systems
Portable Data Acquisition or Analysis Tools
Software Tools for Distributed Analysis and Simulation

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Danny Liu
danny@zonatech.com
9489 E. Ironwood Square Dr.
Scottsdale,  AZ 85258-4578

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA Technology proposes to develop an innovative nonlinear structural reduced order model (ROM) - nonlinear aerodynamic ROM methodology for the inflatable aeroelasticity of a clamped modeled ballute system. The proposed ROM-ROM methodology tightly couples a nonlinear-FEM based structural ROM with CFD based neural-net aerodynamic ROM to achieve a high computational efficiency. Indeed, the computing time for a typical wing flutter/LCO analysis is reduced from hours (direct) to minutes (ROM-ROM). The structural ROM enables a seamless time-integration of the ROM-ROM and could be coupled with other aerodynamic ROM methods like Volterra or POD. A time-accurate GasKinetic BGK method (BGKX) is adopted to generate the aerodynamic ROM for rarefied hypersonic unsteady aerodynamics/aeroelasticity applications to a ballute in atmospheric entry. With a natural boundary condition, BGKX is superior to continuum methods for unsteady flow simulations, and unified in transition to continuum flow regimes covering the peak dynamic pressure range in Earth/Martian entries. It can provide flow pressures and heat flux in one step. In Phase I, we will consider both a 2D membrane-on-wedge system and a modeled ballute system and investigate their static aeroelasticity as well as the feasibility/efficiency of the ROM-ROM approach for their dynamic aeroelastic responses (flutter/LCO). These capabilities are necessary for the development of inflatable aeroelasticity in NASA space program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
With the ROM-ROM methodology fully developed in Phases I/II, ZONA will have in place an efficient nonlinear aeroelastic tool (called NANSI) that could support NASA for its space program in entry Ballute design among the following - NASA could direct aeroelastic applications to the aeroassist/aerocapture inflatable space vehicles such as various Ballute designs, and many innovative inflatable vehicle design concepts for civilian aerospace and aeronautical purposes. - NASA could use ROM-ROM/NANSI technology to support its nonlinear aeroelastic programs for: i) transonic transport, morphing wing and high altitude airship/airframe designs; ii) launch vehicles for aerothermoelasticity of reusable TPS; iii) compliment various flight testing programs at Dryden; iv) extend it to turbomachinery aeroelasticity methodology at Glenn. - NASA could adopt its aerodynamic ROM methodology or the proposed one-step BKGX-based ROM for rapid ROM-ROM aerothermodynamic/aerothermoelastic applications. - Potential NASA customers include LaRC, ARC, Dryden and Glenn.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ZAERO is the flagship software of ZONA supporting aeroelasticity/aeroservoelasticity technology of the aerospace industry worldwide. The developed nonlinear NANSI module will be merged into ZAERO, and it should share ZAERO existing market. Potential applications of NANSI falls into the following: - Rapid flutter/LCO analysis by ROM-ROM can support many ongoing ZONA projects with industry including HALE (Boeing), Sensorcraft /OFW (Northrop Grumman), and the Streamline Store Configurations program (LM Aero/ AFRL/ Eglin AFB). - Support many current new designs in civil transports, inflatable airships, sensorcraft, morphing aircraft, micro aerial vehicles (MAV), etc. The unique feature of the structural ROM and ROM-ROM methodology can render NANSI a popular software for its preferred expediency in nonlinear aeroelasticity analysis. - Aerodynamic ROM is a computationally efficient tool for CFD-based (e.g., FUN3D, BGKX) aerodynamic/aerothermodynamic simulation. - Potential customers/users of ROM-ROM/NANSI should include engineering, design/analysis and R&D arms of AF/DoD, defense/civilian aerospace industries.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Inflatable
Kinematic-Deployable
Launch and Flight Vehicle
Simulation Modeling Environment
Reuseable
Structural Modeling and Tools
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corporation
215 Wynn Drive, 5th Floor
Huntsville, AL 35805-1926

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Essam Sheta
sxh@cfdrc.com
215 Wynn Drive, 5th Floor
Huntsville,  AL 35805-1926

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
CFDRC proposes to develop, validate and demonstrate a comprehensive aeroservoelastic analysis framework for aerospace vehicles by enabling coupled interactions between multi-physics simulation modules with variable fidelity for flexible structures, aerodynamics, flight dynamics, and embedded smart materials. In Phase I, a nonlinear electrodynamics finite-element model for smart materials, capable of handling different materials and FEM mesh elements, will be developed. An interface model capable of handling different mesh densities and types for the smart materials FEM model and the structural dynamics (CSD) model will also be developed. A novel grid deformation technology, developed by CFDRC, using Solid Brick Analogy will be enhanced by nonlinear strain theory for large deformations and generalized for mixed elements computational grid systems. The feasibility of the proposed technology will be demonstrated for a fighter aircraft model in buffet mode. In Phase II, the modeling technologies identified in Phase I will be developed and implemented into the framework, with emphasis on developing an advanced data management procedures to increase the efficiency of the simulation framework. Additionally, an interface model between the aeroservoelastic framework and a general control design toolbox will be implemented to facilitate designs of complex control systems to command the smart materials. The developed technologies will then be extensively validated and demonstrated for typical aeroservoelastic simulations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology will provide accurate and comprehensive analysis tool for truly coupled aeroservoelastic simulations of aerospace vehicles. Aerospace engineers will be able to utilize the proposed predictive analysis framework to predict aeroelastic instabilities, aerodynamic characteristics, performance of controlled flying vehicles, and analyze early designs of aerospace systems. Direct NASA applications of the technology are in prediction and control of aeroelastic and aeroservoelastic phenomena, such as buffet, flutter, buzz, limit cycle oscillations, gust response, and control reversal. Programs like active aeroelastic wing, active twist rotors, and controlled micro air vehicles will also benefit from the technology. Ultimately, the framework will significantly reduce the dependence on flight tests and wind tunnels, and hereby reduce the time required to certify new military and commercial aircraft, and improved safety of aerospace vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
General applications of the technology include general fluid-structure interaction problems such as vortex-blade interaction of rotorcraft, trailing vortices dynamics of commercial aircraft, heat exchanger vibration, strumming of cables and offshore pipelines, galloping of towers and masts, and fatigue of panels.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Simulation Modeling Environment
Testing Requirements and Architectures
Structural Modeling and Tools
Software Tools for Distributed Analysis and Simulation
Ceramics
Computational Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Intech Software Solutions, Inc.
5655 Peachtree Parkway, Suite 202
Norcross, GA 30092-2828

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Salil Gulve
salil@intechsw.com
5655, Peachtree Pkwy, Suite 202
Norcross,  GA 30092-2828

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA code OVERFLOW is used extensively by academia, government institutions, and industry for a wide range of applications. Successful completion of Phase 1 and 2 efforts will enhance the solver and provide more accurate computations. These computations can be used to better understand the underlying physics of stalled and unsteady flow. Specifically, the advanced model can be used to test a variety of configurations that can reduce the drag of commercial transport aircraft. It can also increase the understanding of dynamic stall in rotor blades and other highly unsteady complex flows. This model has shown improved Turbulence modeling for stall prediction for UH-60 Blackhawk in the NASA solver OVERFLOW. More validation will allow inclusion into official OVERFLOW code released to industry and government partners. Industry can use this advancement to current and future advanced aerospace designs. Improved stall prediction and more accurate drag calculations increase the use of CFD, improve designs, and reduce the need for expensive experiments

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The improved turbulence modeling can be used for future aerospace designs for a variety of NASA commercial applications. It is applicable for both aviation and space applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The improved turbulence modeling is equally applicable for non NASA Commercial Applications.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Training Concepts and Architectures
Software Development Environments
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Fluidics, LLC
4217 Red Bandana Way
Ellicott City, MD 21042-5928

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
SURYA RAGHU
sraghu@advancedfluidics.com
4217 RED BANDANA WAY
ELLICOTT CITY,  MD 21042-5928

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of the proposed research is to design, develop and demonstrate fluidic actuator arrays for aerodynamic separation control and drag reduction. These actuators are based on a compact design of low mass-flow fluidic oscillators that produce high frequency (1-5 kHz) oscillating or pulsing jets. Our preliminary experiments on separation control over trailing edge flaps, cavity tones and jet thrust vectoring show great promise for these actuators, the main advantage being that these have no moving parts and hence mechanically robust with a high degree of reliability. The control authority of these actuators is also high as measured from the velocity amplitude of the exiting jets. In Phase I of the proposal, we will determine the geometric and dynamic scaling parameters of the fluidic actuators and explore the system integration issues for embedding them into airfoil shapes. Based on the results from this phase, in Phase II, we will design and develop integrated fluidic actuator systems for 1/10 scale to full-scale testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work on flow control can be implemented in the next generation of the Crew Exploration Vehicle designs being developed by NASA. Such arrays can also be used for de-icing systems using either hot air or de-icing liquids since the fluidic jets work with both liquids and gases.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aerodynamic flow control has a large number of applications in the commercial and military aerospace industry. We foresee applications of our technology to separation control over leading and trailing edge of airfoils for high lift and minimum drag configurations for aircraft wings, control of jet exhaust noise in aircraft engines, intake flow control, and internal flows in gas turbines. One other area of application we are exploring is the flow control and de-icing over wind turbine blades.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Renewable Energy
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
VorCat, Inc.
1370 Piccard Drive, Suite 210
Rockville, MD 20850-4333

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jacob Krispin
jacob@vorcat.com
1370 Piccard Drive, Suite 210
Rockville,  MD 20850-4333

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Turbulent flows associated with advanced aerodynamic designs represent a considerable challenge for accurate prediction. For example, the flow past low-speed wings requires the representation of complex physics involving separation onset/progression (both leading-and trailing-edge), vortex/viscous interactions, merging shear layers with strong curvature, juncture flows and jet-exhaust flows – all phenomena that are not amenable to robust modeling and simulation by traditional grid-based techniques. Recent advances in the technology of gridfree turbulent flow simulation via vortex methods, most notably as manifested in the VorCat code, has raised the possibility of efficiently and accurately capturing the behavior of aerodynamic flows for use in design and performance analysis. The goal of this SBIR phase I proposal is to demonstrate the effectiveness of VorCat in simulating high lift airfoil flows – both in regards to computational speed and accuracy. This will form the basis for developing a tool able to well model arbitrary aerodynamic flows past finite wings including complicating features such as flow control devices in the Phase II study. Upon completion of Phase II, a validated technology will be ready for use by industrial and governmental users.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This project brings to NASA a means for circumventing the persistent limitations of traditional turbulence modeling and simulation techniques that have delayed or prevented progress across a spectrum of innovative flow technologies. With this project NASA will be able to more freely and effectively pursue true design innovations and make better use of corroborating physical experiments. Some particular examples where VorCat can have high impact for NASA include supplying transient pressure data for evaluating noise generation, vehicle design optimization, and safety.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The tools derived from this research are of direct benefit to airplane manufacturers faced with difficult design problems as well as numerous companies engaged in fluids engineering in the automotive and shipbuilding industries, among many others. The VorCat technology that will be perfected in this project can also form the basis for studies including heat and mass transfer and thus have an impact on countless more companies in such fields as electronic cooling, chemical process industry, pharmaceuticals and so forth.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Operations Concepts and Requirements
Airport Infrastructure and Safety
Expert Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Jabiru Software and Services
3819 Sunnycroft Place
West Lafayette, IN 47906-8815

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sanjay Mathur
srmathur@gmail.com
3819 Sunnycroft Place
West Lafayette,  IN 47906-8815

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA aerocapture missions require an accurate evaluation of radiative thermal transport in order to simulate the aerothermal environment around space vehicles. However, present day computation of radiative transport in this complex multi-dimensional environment is frequently done using simple one-dimensional tangent-slab approximations or optically-thick approximations which compromise the accuracy of predictions and which cannot be generalized to new vehicle configurations. In this Phase I proposal, we seek to develop an efficient and accurate unstructured solution-adaptive finite volume solver for participating radiation in complex geometries to address the aerothermodynamics of realistic space vehicles. A number of innovations are proposed to significantly accelerate solver performance over conventional implementations: (i) a spectral line weighted sum of gray gases model for property computation which is significantly faster than conventional line-by-line techniques, (ii) algorithmic improvements based on coupled algebraic multigrid and multiplicative correction techniques, and (iii) parallel implementations on both distributed and shared memory platforms, including new multicore architectures. The proposed framework is fully compatible with computational fluid dynamics (CFD) methods for flow, heat transfer, turbulence and chemistry, and coupling to these is proposed for Phase II. The project team consists of Drs. Sanjay Mathur of Jabiru Software and Services, and Prof. Jayathi Murthy of Purdue's School of Mechanical Engineering. The team is highly experienced in the development of large-scale commercial finite volume solvers, radiative heat transfer, and algorithm development, and has over two decades each of experience in the development and commercialization of large-scale CFD codes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The solver developed during Phases I and II of this project will find wide applicability in NASA. Efficient and accurate flow solvers based on unstructured meshes addressing compressible and incompressible flows will find use in NASA's aerodynamics, aerothermodynamics, space entry, internal fluid mechanics, turbomachinery, microgravity, propulsion and materials processing programs. Efficient solvers for thermal radiation will find application in NASA's National Combustor Code, as well as other applications in propulsion and power-generation, and in materials processing applications such as chemical and plasma vapor deposition.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Thermal radiation plays a central role in a variety of applications in the automotive, aerospace, power generation and materials processing sectors. In the automotive arena, in-cylinder combustion requires the computation of participating radiation. Propulsion applications similarly require the computation of thermal radiation combined with models for hydrocarbon combustion, as do applications in the commercial power generation arena, where coal/oil/natural gas combustion burners and furnaces form the mainstay. In the materials processing area, our opportunity would lie in the area of glass and ceramics processing, where band-radiation in semitransparent media govern the physics. Applications include the manufacture of plate glass, automotive wind shields, fiber-glass for home insulation and ceramics processing for semi-conductor applications. The Phase II extensions, including the coupling of fast solvers for non-equilibrium chemistry, will find application in a variety of combustion applications, and also in emerging materials processing applications such as plasma chemical vapor deposition (CVD).

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
Simulation Modeling Environment

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
AeroSoft, Inc.
1872 Pratt Drive, Suite 1275
Blacksburg, VA 24060-6141

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Applebaum
applebau@aerosft.com
1872 Pratt Drive, Suite 1275
Blacksburg,  VA 24060-6141

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
AeroSoft proposes to develop a full featured CFD toolkit for analysis of the aerothermal environment and its effect on space vehicles. In Phase I, AeroSoft proposes to implement multi-component ablation along with material response into AeroSoft's structured and unstructured CFD solver GASP. In Phase I, GASP's internal thermal solver will be augmented to include the effects of ablation. In Phase II, AeroSoft proposes to implement radiation heat flux and radiation transport into GASP.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The direct benefits to NASA are the ability to analyze the interaction of ablating materials with the gases in the shock layer, and the ability to analyze radiation heat transfer and radiation transport that occurs in shock layers for reentry applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The work performed under Phase I and Phase II will have significant application to directed energy research. AeroSoft's GASP is currently being used to perform laser-target interaction. Much of the physics that occur during reentry also occur during laser-target interaction. Potential customers include NASA, Lawrence Livermore National Labs, Sandia National Labs, and their subcontractors performing reentry design and analysis or COIL related research.

TECHNOLOGY TAXONOMY MAPPING
Ablatives

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
D&P, LLC
3409 N. 42nd Place
Phoenix, AZ 85018-5961

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Lei Tang
tanglei@d-p-llc.com
3409 N. 42nd Place
Phoenix,  AZ 85018-5961

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR Phase I project explores two gas-kinetic computational algorithms for simulation of hypersonic flows in both continuum and transitional regimes. One is the gas-kinetic BGK-Burnett solver and the other is the gas-kinetic BGK solver with the regulated particle collision time. Different from the macroscopic Burnett approach, the proposed gas-kinetic BGK-Burnett solver is unconditionally stable for all Knudsen numbers. Whereas it is almost impossible to correctly set up boundary condition for the Burnett equations, this can be easily done in the proposed BGK-Burnett solver with the Maxwell boundary condition, re-emitting the particles from the boundary according to the accommodation coefficient. More importantly, this BGK-Burnett solver not only allows a single algorithm for both continuum and transitional flow regimes but also is more suitable for integration with either DSMC or direct Boltzmann solver in the rarefied flow regime. The gas-kinetic BGK solver with the regulated particle collision time can further reduce the computational costs over the BGK-Burnett solver. The focus of Phase I work is to determine the validity Knudsen number range of these two algorithms.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA current mission focuses on human lunar and martian exploration. The design of crew exploration vehicles requires the proposed computational tool, which is able to handle the flows beyond the continuum regime and thereby accurately predict shock stand-off distances, peaks in thermal loads, skin friction drag, forces and moments on the vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed gas-kinetic computational algorithms can significantly enhance the capability of aerospace industry to predict the aerothermal loads on a space vehicle. It can also be used to MEMS and nanotechnology applications.

TECHNOLOGY TAXONOMY MAPPING
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Combustion Research and Flow Technology
6210 Keller's Church Road
Pipersville, PA 18947-2010

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Wilmoth
wilmoth@craft-tech.com
124 Burnham Place
Newport News,  VA 23606-2611

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new chemical kinetics model and database will be developed for aerothermodynamic analyses on entry vehicles. Unique features of this model include (1) the ability to model chemical kinetics in highly nonequilibrium flows at high altitudes, (2) the ability to predict nonequilibrium dissociation without reliance on traditional continuum kinetic rate equations, and (3) the ability to model complex reactions from fundamental molecular quantum models. The model will permit analyzing high-speed, nonequilibrium flows about entry and aeroassist vehicles based on extensions to Direct Simulation Monte Carlo (DSMC) codes, and a new database will be developed for these extensions. The new approach offers potential for treating other complex nonequilibrium flow physics including ionization and radiation in a more direct manner than has been previously use and therefore offers potential improvements in accuracy. These tools will provide essential data for assessing the aerothermodynamic performance of a broad variety of vehicle designs over a wide range of vehicle attitudes and flight conditions. The improved accuracy offered by our proposed chemical kinetic modeling approach provides significant benefits in the design of vehicles for both unmanned planetary missions and manned missions to the Moon and Mars.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed chemical kinetics model has potential application to the design and analysis of a broad class of NASA vehicles that experience flight through Earth or other planetary atmospheres under extreme heating conditions. Examples of these vehicles include those being designed to use aerocapture to achieve a low-cost orbit around Neptune and Titan. The model has particular relevance to the design of manned vehicles for return to Earth from lunar and Mars missions that will likely experience extremely high-velocity, nonequilibrium environments such as the proposed Crew Exploration Vehicle.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed chemical kinetics model has potential application to design and analysis in a variety of fields concerned with nano-processes, with DOD interest in missile detection and tracking and RV discrimination, and, with various processes that occur in an gaseous environment including (1) solid state materials processing involving low-density deposition, (2) environmental sampling analysis through plasma spectrochemistry, and (3) nonequilibrium chemical kinetics occurring in higher altitude plumes and divert/control jets.

TECHNOLOGY TAXONOMY MAPPING
Fundamental Propulsion Physics
Simulation Modeling Environment
Cooling
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optimal Synthesis, Inc.
868 San Antonio Road
Palo Alto, CA 94303-4622

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
V. V. S. Vaddi
vaddi@optisyn.com
868 San Antonio Road
Palo Alto,  CA 94303-4622

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Guidance and control system design for hypersonic vehicles is more challenging than their subsonic and supersonic counterparts. Some of these challenges are (i) coupling between the aerodynamic, structural and propulsion sub-systems (ii) uncertainty involved in modeling these couplings and (iii) state-space constraints. Proposed research seeks to address these challenges using advanced robust control system design techniques. Key components of the proposed research are (i) hypersonic vehicle modeling, (ii) uncertainty representation, (iii) robust controller designs, and, (iv) robustness evaluation tools. Personnel at OSI have extensive experience in the area of flight control system design and flight vehicle modeling. Phase I research will demonstrate the feasibility by using existing longitudinal hypersonic vehicle models. Phase II research will pursue three dimensional modeling of the hypersonic vehicle alongside advancing the control system design. A complete version of the control system design software will be developed and provided to NASA by the end of Phase II work.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed control system design is directly applicable to reusable launch vehicles and can also be used for the Mars reentry vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Hypersonic vehicle development is being actively pursued by NASA and the DoD for several missions. The control system architecture developed in this research will be applicable to global strike missions involving hypersonic missiles and different space access vehicle designs being pursued by space tourism companies.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Rolling Hills Research Corporation
420 N. Nash Street
El Segundo, CA 90245-2822

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Kerho
Mike.Kerho@RollingHillsResearch.com
420 N. Nash Street
El Segundo,  CA 90245-2822

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is a self-contained, self-powered, robust flight test sensor array for the determination of separation. The proposed system uses off the shelf, currently available technology to create a reusable distributed sensor array, which requires no external wiring or power source. The system is based on a novel instrumented tuft technology. A distributed array of tuft sensors are embedded in a flexible, self-adhesive backed sheet of polymide substrate. The proposed separation sensor array will provide real-time, accurate determination of separation across a wide range of flight conditions. The self-contained blanket array can be quickly and easily applied to aircraft surfaces in question. No wiring, external power, or remote viewing is required for acquisition. After testing is complete, the system can be quickly removed and reused. Additionally, the system could be miniaturized for use in ground test facilities or applied to other types of vehicles. The proposed separation sensor array promises to provide a realizable, accurate, efficient, and cost effective measurement system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced sensing technology in the form of a robust separation detection system for both flight and ground test facilities has significant potential application at several NASA centers and across a wide range of NASA facilities. With the current high costs of flight and ground testing, coupled with reduced design and test schedules, the proposed technology will be highly desirable. The technology developed by RHRC under this program will allow the accurate, efficient, and cost effective detection of separation on aerodynamic/hydrodynamic surfaces across a wide range of conditions. NASA centers and facilities will be eager to exploit the proposed technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed separation detection technology will be highly desirable in military, government, and civilian testing markets. The technology developed by RHRC under this program will allow the efficient and cost effective detection of separation on vehicles across a wide range of applications other than aircraft. These include automobiles, hydrodynamic, and civil engineering applications. Any external surface where aerodynamic separation is a concern is a potential application of the technology.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Rolling Hills Research Corporation
420 N. Nash Street
El Segundo, CA 90245-2822

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Kerho
Mike.Kerho@RollingHillsResearch.com
420 N. Nash Street
El Segundo,  CA 90245-2822

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of Micro Air Vehicles (MAVs) has received considerable attention in recent years for both military and civilian uses. MAVs typically suffer from operation in an extremely low Reynolds number flight regime. At these very low Reynolds numbers, the aerodynamic flow features can be nonlinear and are dominated by laminar separation and separation bubble effects, which can be a source of poor performance from both an aerodynamic and stability and control standpoint. If a stable platform is required for sensor effectiveness, or the vehicle is to be controlled by a relatively inexperienced operator, controllability of a vehicle operating in this very low Reynolds number regime can be a critical factor in determining the success or failure of a design. Flight control systems implemented on this class of vehicles are severely constrained in size and available power. They suffer from inadequate knowledge of the vehicle state, both statically and dynamically. Rolling Hills Research Corporation proposes to use a simple and robust biologically inspired air data system capable of providing instantaneous vehicle state information, including rates, to provide revolutionary stability, control, and performance for these ultra low Reynolds number vehicles.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed MAV air data system has significant potential application in several NASA programs. The robust and simple sensing technology could be fielded in several NASA aircraft unmanned systems, from MAVs to Mars exploratory aircraft. NASA designers will be eager to exploit the advantages of the proposed air data system on vehicles requiring augmented control and stability in space constrained, low power environment. The technology will allow controllability and performance levels for this class of aircraft previously unobtainable.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Advanced sensing technology in the form of a robust MAV air data sensor and flight control will provide RHRC with a unique and highly marketable product. The market for MAVs is expected to grow substantially in the coming years. The technology developed by RHRC under this program will allow controllability and performance levels for this class of aircraft previously unobtainable. A robust, cost effective, and low power system would be highly desirable in all classes of MAV vehicles. Considering the recent proliferation of small UAVs and MAV designs, the commercialization potential for the technology is excellent. RHRC will be able to provide complete MAV air data/flight control systems. The technology can also be easily licensed.

TECHNOLOGY TAXONOMY MAPPING
Attitude Determination and Control
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MetroLaser, Inc.
2572 White Road
Irvine, CA 92614-6236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Drew L'Esperance, Ph.D.
dlesperance@metrolaserinc.com
2572 White Road
Irvine,  CA 92614-6236

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This is a proposal to develop an electronic, focusing schlieren system for flight research based on electronic cameras and spatial light modulators as dynamic programmable masks. Schlieren methods are widely used to visualize turbulence and shock phenomena. Focusing schlieren systems are ideal for applications requiring a large field of view, and are the preferred methods for outdoor schlieren systems. One schlieren technique for large field studies is the use of focusing schlieren with background grids. Recently, schlieren systems that use the sun as a background source have been developed for studying shock waves for aircraft in flight. The application of both schlieren techniques is restricted by the capabilities of fixed schlieren cut-off masks. Liquid crystal spatial light modulators afford greater flexibility, as the correct cut-off mask can be programmed and updated electronically. Since the spatial light modulators can be updated at video rates or faster, there is also the possibility of using the SLMs to correct for changes in the background. In addition, we will incorporate state of the art electronic cameras.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Flight testing is often used as a final critical check of the aerodynamic designs developed by computational and wind tunnel methods because the amount of reliable information obtainable in wind tunnels is somewhat limited and subject to interference. Outdoor schlieren systems using naturally available or dynamically changing backgrounds make it possible to examine shock waves and other phenomena from aircraft in flight. Applications exist in all forms of research and development associated with turbulent flow fields, including aero optics, flow control, drag, boundary layer transition, and flow separation. The proposed developments could be extremely important in flight testing, where few such instruments can perform in a flight environment.

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

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
M4 Engineering, Inc.
2161 Gundry Avenue
Signal Hill, CA 90755-3517

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Myles Baker
myles.baker@m4-engineering.com
2161 Gundry Avenue
Signal Hill,  CA 90755-3517

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
M4 Engineering proposes the development of an adaptive structural mode control system. The adaptive control system will begin from a "baseline" dynamic model of the system, which will be updated as the system is operated. This allows the control inputs to be tailored to the observed behavior of the system across a range of flight conditions, weight conditions, and failure conditions, while accounting for uncertainty in structural dynamics and aerodynamics. The development of the adaptive control system involves a selection of a set of adaptive control algorithms, which will then be implemented and tested on a set of example problems. The performance of the algorithms will be evaluated and additional development and enhancements will be subsequently recommended.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are numerous potential NASA applications. The first is the ASM wind tunnel test being funded under the supersonics task of the ARMD program. This provides a unique opportunity to validate the SBIR technology on a realistic configuration, and also provides a much-needed control law design to the ASM test program. Applications of this technology to future flight test programs and future vehicle development efforts are also anticipated.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Development of ASE control laws for flight vehicles using conventional methods is frightfully expensive. If adaptive methods can be shown to be robust, reliable, and to offer good performance without the extensive aerodynamic/ASE database development and the complex gain scheduling required of conventional flight control systems, this offers a dramatic reduction in development costs. As such, if successful, this technology will result in extensive application to commercial vehicles ranging from small UAV's to commercial airliners to military weapon systems. M4 Engineering has active relationships with several prime contractors who are likely users of this technology. These include Boeing Phantom Works, Northrop Grumman, and Raytheon. These provide excellent commercialization opportunities for the technology. Active marketing to prime contractors and other specialty airframers (e.g., Aerovironment, General Atomics, etc.) will follow these applications.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Structural Modeling and Tools
Attitude Determination and Control
Autonomous Control and Monitoring

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Michigan Engineering Services, LLC
2890 Carpenter Road, Suite 1900
Ann Arbor, MI 48108-1100

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jim He
jim_he@miengsrv.com
2890 Carpenter Road, suite 1900
Ann Arbor,  MI 48108-1100

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aircraft design is a complex process requiring interactions and exchange of information among multiple disciplines such as aerodynamics, strength, fatigue, controls, propulsion, corrosion, maintenance, and manufacturing. A lot of attention has been paid during the past fifteen years in the Multi-disciplinary Design Optimization (MDO) nature of the aircraft design process. However, a consistent void in aircraft design is the ability to integrate high-fidelity computational capabilities from multiple disciplines within an organized MDO environment. Integrating high fidelity simulation technology (that has been developed over the years though significant investments) within a MDO environment will constitute a disruptive technological development in aircraft design. Currently, each high fidelity simulation is rather compartmentalized, and at best a sequential interaction process is exercised. Integrating the high-fidelity computational capabilities from multiple disciplines within an organized MDO environment will provide the ability to capture the implications that design changes in a particular discipline have to all other disciplines. It will also be possible to share design variables among disciplines and thus identify the direction that design variables should follow based on objectives and constraints from multiple disciplines. During the Phase I effort the feasibility of utilizing high fidelity CFD simulations for shape optimization and combining them with a structural finite element simulation for strength considerations within a multi-discipline design optimization environment will be demonstrated. A wing configuration will be analyzed for showcasing the different steps of this development and the benefits.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Aerodynamics, strength, fatigue, controls, propulsion, corrosion, maintenance, and manufacturing concerns are present in aircraft structures, launch vehicles, and spacecraft. In all of these areas simulations are utilized during design. High fidelity simulation methods have been developed under significant investment in the different disciplines. However they remain rather compartmentalized, and at best only a sequential interaction process is exercised. Therefore engaging available high fidelity simulations within a multi-disciplinary design optimization environment will bring new technology to all NASA groups interested in reducing weight and cost when designing aircraft, launch vehicles, and spacecraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The marketing effort will target companies and organizations within the aerospace field (NASA, space vehicles, aircraft manufacturers, rotorcraft applications, launch vehicle industries), the shipbuilding, the automotive, the military ground vehicle, and the heavy construction equipment. In all of these industries CFD simulations are heavily utilized either for simulating aerodynamic or hydrodynamic performance, or for cooling and pipe flow calculations; all use multi-physics simulation models for assessing the performance of their products during design; and they all have needs for designing products based on economic viability and making the complex design optimization process easy to use. Thus, there is a great market potential for the outcome of this SBIR project.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Simulation Modeling Environment
Structural Modeling and Tools
Composites
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Dynamics, Inc.
1500 Bull Lea Road, Suite 203
Lexington, KY 40511-1268

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Patrick Hu
patrick.g.hu@advanceddynamics-usa.com
1500 Bull Lea Road ,Suite 203
Lexington,  KY 40511-1268

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
CFD modeling and simulation has been heavily invested in decades of manpower by a large community of researchers. However, the excessive numerical diffusion inherently caused by discretization errors plus the possibly largest/finest grid requirement for rotor wake modeling prevents CFD to be routinely used in practical engineering calculations. The proposed Gradient Transport Correction (GTC) method provides an innovative artificial compression that can serves as a general confinement for greatly enhancing the resolution of rotor wake capturing while significantly reducing the grid requirement. In this proposal, we have demonstrated the great potential of GTC method to counteract the numerical dissipation and absolutely preserve the wake vortical structure with a small number of grid cells. Phase I will develop an initial capability, and the capability to be established in Phase I will be developed into a general engineering tool that has engineering analysis accuracy as well as transparent set-up for a broad range of important engineering calculations, such as computing hover performance, high-lift and separation flows, as well as various types of multiple rotors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The major beneficiary of the proposed research program will be NASA centers. It has been demonstrated that the proposed Gradient Transport Correction (GTC) method has the great potential for enhancing the resolution of a wide range of engineering calculations with significant grid reduction, particularly for rotor wake capturing that affects almost every aspect of rotorcraft analyses and evaluation. The resulting performance improvement is, therefore, an important asset for various types of rotorcraft development and upgrades in NASA centers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting methods and software ability will, of course, benefit other DoD components, such as Army, Navy and Air Force. The US aviation and rotorcraft industries, including Boeing, Pratt & Whitney, General Electric, General Dynamics, Lockheed Martin, Textron, and others, will be the major non-military potential customers. Moreover, improvement of computational accuracy and efficiency is common interest in CFD community, thus is highly demanded. The aviation and rotorcraft industries in Europe, China and Japan represent another large potential marketing of the resulting methods and software. Advanced Dynamics will promote the international sales through resale partners of local companies abroad. Therefore, the methods and software abilities gained from this SBIR project will be additional to Advanced Dynamics' existing commercial offerings.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Materials Technologies Corporation
57 Maryanne Drive
Monroe, CT 06468-3209

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Serkan Ozbay
sozbay@aboutmtc.com
57 Maryanne Drive
Monroe,  CT 06468-3209

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The lead-lag motions of rotor blades in a helicopter require damping to stabilize them. In practice, this has necessitated the use of external hydraulic dampers which suffer from a high maintenance cost. This high operational cost has prompted the rotorcraft industry to use elastomeric lead-lag dampers that result in ``dry'' rotors. However, complex behavior of elastomers provides challenges for the modeling of such devices, as has been noted by rotorcraft airframers. Analytical models have tended to oversimplify the complexity of the operational environment and make radical assumptions about operating parameters that, at best, lead to simple, and often unreal, device models. In spite of costly and time consuming experiments to construct them, these first order device models do not directly relate to neither material characteristics nor geometric configuration. Example: the device model approach leads to the erroneous identification of "physical phenomena" such as dual frequency effect. We propose a fundamentally radical approach wherein elastomeric dampers are derived from first-principle-based modeling rather than device model based analysis. First we propose to develop a finite element based simulation tool for modeling the response of complex components made of elastomeric materials. When integrated with a finite element based, multibody dynamics analysis code, this innovative tool will accurately simulate the dynamic response of vehicles such as rotorcraft using elastomeric components using true material properties and damper geometry. This tool will be unique because it will capture both dissipative and geometric nonlinearities causing damping loss at dual frequency excitations typically observed in elastomeric devices. When fully developed and validated, our first principles based formulation for the modeling of elastomeric devices will be available for robust component design.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Elastomers are used in many vehicles for applications from vibration isolation to stability augmentation. For NASA, the immediate application would be in integration of the process into a robust rotorcraft design environment. Moreover, the generic nature of the formulation would make it amenable to modeling any electrometric material application

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
First, Commercial rotorcraft industry - provide considerable cost reductions in the design process. Secondly since any device based on elastomers can be modeled. Final product would find quite large range of application in the automotive as well as tracked vehicle industry.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Kinematic-Deployable
Launch and Flight Vehicle
Operations Concepts and Requirements
Simulation Modeling Environment
Spaceport Infrastructure and Safety
Structural Modeling and Tools
Composites
Computational Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Materials Technologies Corporation
57 Maryanne Drive
Monroe, CT 06468-3209

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Serkan Ozbay
sozbay@aboutmtc.com
57 Maryanne Drive
Monroe,  CT 06468-3209

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In a rotorcraft, optimized camber change not only reduces vibratory hub loads and noise but also increases available thrust and improved flight control augmentation. Therefore, the ability to dynamically change airfoil camber is a significant technology advancement leading to improved overall rotorcraft performance. Research efforts in recent years have led to the application of active material actuation for rotorcraft blades in order to dynamically change blade camber. Small-scale bench top system validations have been successful. However, when scaled-up to full-scale aircraft, the performance of current actuation systems in a demanding rotor blade environment gets significantly degraded by operational factors including friction, free play, and, aerodynamic and inertial loads. We propose a unique three dimensional concept wherein the typically closed section blade is cut open to create a torsionally compliant mechanism that acts as its own amplification device; the deformation of the blade is dynamically controlled by out-of-plane warping. Our innovative approach for camber control is a radical departure from the current techniques. The proposed development and engineering effort will lead to a new camber control technology suitable for full-scale aircraft that would result in improved operational efficiencies at lower costs. Concept feasibility will be demonstrated both analytically and through experiments on blade sections of a Sikorsky Blackhawk. A Phase II program will follow for technology scale-up and optimized full blade testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NA

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
- All commercial rotorcraft manufacturers. Improving overall rotorcraft performance as well as safety at a lower operational cost would be a major motivation for the rotorcraft industry to implement this technology. - Worldwide Wind Turbine industry for power generation. An effective camber change is needed to benefit most from the dynamic airflow through wind turbines. The potential for this rapidly growing "green" power generation industry is enormous.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Structural Modeling and Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sukra Helitek, Inc.
3146 Greenwood Road
Ames, IA 50014-4504

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Angela Lestari
nappi@sukra-helitek.com
3146, Greenwood Road
Ames,  IA 50014-4504

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Rotorcraft engineers traditionally use the wind tunnel to evaluate and finalize designs. Insufficient correlation between wind tunnel results and flight tests, have been often attributed in part to uncertainty in blockage corrections. Estimation of rotor blockage is significantly more complex than bluff body blockage as the correction depends on operational characteristics such as rotor RPM and thrust produced. This proposal offers to develop a design tool, which can simulate a complete rotorcraft inside a wind tunnel including all the facility effects. At the heart of the innovation are: 1. An automated hybrid grid generator. 2. A robust and economical incompressible flow solver for the grid system. 3. Momentum source based rotor model that is suitable and economical for simulating multiple rotors including the drive fans of the wind tunnel. Phase I will develop the proof-of-concept and will use unstructured Cartesian grid for the model and wind tunnel. The wind tunnel will be modeled with the diffuser, test section and nozzle. In phase II, the tool will be extended to hybrid grid with viscous grid near solid surfaces and will include drive fans of the tunnel.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The design tool to be developed under this initiative will find wide usage throughout NASA where wind tunnel testing is integral to any design study. The tool can be effectively used for rotorcrafts and V/STOL aircrafts where quantification of blockage effects is complex.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The computational wind tunnel to be developed will be an asset to other government agencies including ARMY, NASA and AIR FORCE and industry where wind tunnel testing of rotorcraft and V/STOL aircrafts is routine. In short, the tool is a compliment to all wind tunnel testing.

TECHNOLOGY TAXONOMY MAPPING
Simulation Modeling Environment
Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Lawrie Technology, Inc.
227 Hathaway E
Girard, PA 16417-1552

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Duncan Lawrie
duncan@lawrietechnology.com
227 Hathaway E.
Girard,  PA 16417-1552

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An all-composite driveshaft incorporating integral flexible diaphragms is described and proposed for further refinement. An approach is explored which obsoletes the split lines and associated fasteners required to attach metallic flex elements and either metallic or composite spacing tubes in current solutions. Sub-critical driveshaft weights half that of incumbent technology are projected for typical rotary wing shaft lengths. Spacing tubes are described, which comprise an integral part of the initial tooling but which remain part of the finished shaft and control natural frequencies and torsional stability. A concurrently engineered manufacturing process and design for performance is proposed which competes with incumbent solutions at significantly lower weight and with the probability of improved damage tolerance and fatigue life. This phase I proposal seeks to further remove manufacturing cost and to produce test articles suitable for concept verification and, subsequently, flight qualification during phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The rotary wing subtopic 2.10 includes both materials & structures and propulsion components requiring lower weight and higher performance in power transmission components. These include tail rotor drives, tilt-rotor cross-over drives, and tandem rotor connection shafts. Current technology has not changed in decades as it concerns motion accomodating, high torque density driveshafts. Enhanced mission availability and cost reduction can be obtained via the reduced part count and improved fatigue performance already established by this fully integral, all-composite driveshaft technology. Further refinement and preparation of flight qualification test articles is proposed and, once fielded, NASA and NASA partners will also benefit from increased payload.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial benefits are similar to NASA benefits in improving rotary wing performance across government agencies and the commercial helicopter market.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Composites
Aircraft Engines

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrei Vakhtin
avakhtin@swsciences.com
1570 Pacheco Street, Suite E-11
Santa Fe,  NM 87505-3993

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Monitoring and controlling blade tip clearance of high pressure turbines are important for maintaining the integrity of the engine during its operating points and life cycle. Operating the engine with minimum tip clearance provides several benefits, such as increased turbine efficiency, reduced emissions, and extended service life. Southwest Sciences proposes an innovative technology based on optical Fourier domain reflectometry for near real-time tip-clearance measurement with an accuracy of 10 micrometers or better. A simple and robust optical sensor will withstand temperatures of up to 2000 F; therefore, the method can be applied for tip-clearance measurements in turbine hot sections. The system will allow controlling multiple sensors acquiring data from different locations in the turbine with a single main unit. The Phase I effort will provide experimental evidence of the feasibility of this approach and outline the design of the Phase II prototype instrument.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed turbine blade tip clearance sensor meets the needs of NASA's Fundamental Aeronautics Program in the areas of experimental capabilities for a broad range of air vehicles covering subsonic through supersonic flight regime. In particular, this sensor specifically addresses the need for a turbine tip clearance system for applications to rotary-wing aircraft engines. The sensor system developed under this research program will provide a new tool for engine manufacturers to study and optimize blade tip clearance with high accuracy without the need for repetitive and cumbersome calibration procedures. Moreover, engine health monitoring and control systems will benefit from this sensor system for real-time implementation of active tip clearance control mechanisms in gas turbine engines. The envisioned compact, low weight, low-cost, high-temperature capable, self-calibrating sensor heads can be easily integrated into engine casings at several physical locations with minimal or no disturbance to the engine internal flow paths; thus, a flight-version of this sensor system is certainly within reach as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
For optical turbine tip clearance monitoring, customers include Air Force, Navy, Army, and also aircraft manufacturers, jet engine manufacturers, and military groups that inspect and maintain the aircraft engines. The new optical monitoring technology will also be useful for maintenance of commercial aircraft engines and industrial turbines.

TECHNOLOGY TAXONOMY MAPPING
Optical
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nanosonic, Inc.
1485 South Main Street
Blacksburg, VA 24060-5556

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mike Bortner
mbortner@nanosonic.com
1485 South Main Street
Blacksburg,  VA 24060-5556

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of this Phase I NASA SBIR program is to develop high performance multifunctional nanostructured materials that can be used to fabricate icephobic multifunctional appliqués with enhanced erosion resistance for rotorcraft leading edges. The proposed technology offers integrated multifunctionality that results in reduction of weight, system complexity, maintenance, and cost over current systems. Prevention of ice buildup will facilitate mission critical operations in icing conditions, as well as mitigate concerns of vibration transmission and shudder that are associated with ice buildup. Integration of additional erosion resistant composites may also result in reduced maintenance costs. Electrothermal systems are currently used for anti-icing systems in rotorcraft, but are prone to failure due to system complexity. To mitigate the problems associated with current anti-icing systems, NanoSonic proposes to develop multifunctional adhesive backed appliqués with integrated hydrophobicity and enhanced erosion resistance. High performance tapes are currently applied to rotorcraft leading edges to help improve erosion resistance. Integrating multiple functionalities into a high performance nanocomposite appliqué would result in reduction of weight and system complexity, facilitate operation in icing conditions, and reduce maintenance on the rotorblades. For minimal maintenance and application cost, a new appliqué can be readily placed on the rotorblade leading edge when the existing appliqué has exhausted its functionality.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications include any application where water repellency, minimization of water ingress, or reduced frictional drag is desired. Water repellency provides anti-icing functionality useful in nearly any vehicle or structure for missions where icing or the risk of ice formation inhibits progress. Water repellency also suggests minimized water ingress. The proposed hydrophobic materials may be transitioned to coating application suitable for corrosion resistance. Minimization of corrosion on metallic surfaces would minimize maintenance and reduce concerns of potential structural integrity damage resulting from corrosion. Hydrophobic materials can also significantly reduce frictional drag, which may be particularly useful for operation of small exploratory vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed nanocomposites will significantly benefit both military and civilian applications. For the military, commercial applications include any application where water repellency, minimization of water ingress, or reduced frictional drag is desired. Examples include corrosion protection on military vehicles, frictional drag reduction on underwater vehicles, and water repellant materials for nearly any military platform metallic surface. Commercial applications are also nearly limitless, including corrosion protection and frictional drag reduction for higher performance, cost and energy saving commercial aircraft and automobiles.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Launch and Flight Vehicle
Composites
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Peregrine Power, LLC
27350 SW 95th Avenue, Suite 3030
Wilsonville, OR 97070-7709

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dallas Marckx
dmarckx@peregrinepower.com
27350 SW 95th Avenue, Suite 3030
Wilsonville,  OR 97070-7709

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Variable speed rotors will give helicopters several advantages: higher top speed, greater fuel efficiency, momentary emergency over-power, resonance detuning capability and a reduction in noise. The applicant proposes to develop such a system using a doubly-fed planetary gear box with advanced SiC-based power electronics and motors. The new components enabling variable speed will be rated at a fraction of the total helicopter power rating, thus reducing weight dramatically. The resulting hybrid mechanical/electrical power system also gives, in addition to greater fuel efficiency, smooth continuous speed variations with electronics, inherent starting capability (e.g., elimination of the existing starter motor), simplification of the tail rotor system, and the ability to enhance power to the main rotor with batteries and the APU. Feasibility will be determined in Phase I by the applicant with the assistance of a major helicopter manufacturer.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The specific variable speed rotor system proposed would improve helicopters, which are not directly supplied by NASA. Although some helicopters are used by NASA, far and away the majority are used by others. However, the improvement of helicopters is part of the NASA mission to improve flight craft which operate within the atmosphere.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The specific variable speed rotor system proposed is unique to helicopters, but it can be scaled for use in all civilian and military helicopters from small unmanned versions to the largest heavy lift versions. Variations of the approach and technologies can also be used in many other types of hybrid electric vehicles, such as ships, autos, trucks, tanks and other armored vehicles.

TECHNOLOGY TAXONOMY MAPPING
Controls-Structures Interaction (CSI)
Simulation Modeling Environment
Cooling
Highly-Reconfigurable
Semi-Conductors/Solid State Device Materials
Energy Storage
Power Management and Distribution
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron Aviation, Inc.
131 Elden Street, Suite 200
Herndon, VA 20170-4758

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Rafal Kicinger
Kicinger@MetronAviation.com
131 Elden St., Ste 200
Herndon,  VA 20170-4758

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We will develop a Coevolutionary Decision Support Tool (CDST) that explicitly incorporates weather uncertainty (non-probabilistically) into strategic Traffic Flow Management (TFM) and automatically generates robust rerouting strategies for the National Airspace System (NAS) operating in inclement weather. The CDST will utilize coevolutionary algorithms (CEAs) (an emerging class of algorithms extending traditional genetic algorithms) to concurrently search the solution spaces of aircraft routing strategies and hazardous weather scenarios. By using the tool, Airline Operations Control (AOC) and Air Traffic Control System Command Center (ATCSCC) Traffic Management Unit (TMU) personnel can achieve two key strategic TFM objectives: 1. Identification of robust aircraft rerouting strategies, i.e., strategies which perform well against a large spectrum of hazardous weather scenarios, and 2. Discovery of vulnerabilities of the NAS with respect to certain weather conditions. The CDST will employ new theoretical and conceptual (non-probabilistic) methods of incorporating weather information into strategic TFM planning, also developed a part of this project. These methods will be subsequently utilized to create efficient computational representations of weather scenarios and aircraft rerouting strategies which can be manipulated by CEAs. In addition, a set of metrics for assessing the quality, or fitness, of produced solutions (both weather scenarios and rerouting strategies) will be developed as well as a metric for measuring the improvement of achieved TFM robustness. The CDST will be implemented in a prototype system which will be subsequently used to demonstrate feasibility of the proposed approach. This technology will be developed to Technology Readiness Level (TRL) 2 by the end of Phase I, and TRL 4 prototype system by the end of Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool offers a R&D capability that enables NASA researchers to investigate new techniques for TFM for the future. When used in conjunction with the Future ATM Concept Evaluation Tool (FACET), the CDST can be utilized to study new TFM procedures that create robust strategies in weather constrained airspaces. It can also be combined with the Airspace Concept Evaluation System (ACES) simulation tool, to study future policies and procedures for TFM and to investigate the benefits of robust TFM strategies in severe weather type days.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool has application to other Government agencies which involved with the development of NGATS, i.e., FAA, and the Departments of Defense, Commerce, and Transportation. Each of these agencies faces the need to properly address weather uncertainties in their strategic planning phase and use advanced decision support tools to discover robust strategies to improve the efficiency and predictability of TFM. It should also be useful to aviation-related commercial firms of all types (airlines, airports, aerospace companies, consultants, etc.) that need access to a methodology and algorithms that will help them identify and mitigate the effects of hazardous weather.

TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and Safety
Guidance, Navigation, and Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron Aviation, Inc.
131 Elden Street, Suite 200
Herndon, VA 20170-4758

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jimmy Krozel
Krozel@MetronAviation.com
131 Elden St., Ste 200
Herndon,  VA 20120-4758

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We design and develope a Decision Support Tool (DST) that supports On-Demand Special Use Airspace (SUA) scheduling and flight plan optimization around SUA between Airline Operations Control (AOC), Military, Air Traffic Control System Command Center (ATCSCC), and Air Route Traffic Control Center (ARTCC) personnel. The tool allows AOC and ARTCC Traffic Management Unit (TMU) personnel to coordinate strategic and tactical plans, with a strategic look ahead time from days to less than 2 hours, and tactical plans up to the minute centered locally around an ARTCC airspace. The tool coordinates aircraft movement though vs around SUA. The tool allows for asynchronous communication of priorities associated with flight plans and flight plan amendments (contingency plans) between the AOC and ARTCC TMU specialist, allowing the ATCSCC and Military to view these priorities and TMU responses to them at any time. This technology will be developed to Technology Readiness Level (TRL) 2 by the end of Phase I, and TRL 4 prototype system by the end of Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool has application in Air Traffic Management Research to study Dynamic Airspace Configuration (DAC) changes due to SUA usage, and automated Traffic Flow Management (TFM) solutions. The tool may be included into NASA's FACET or ACES simulation environment for benefits studies, or in real-time simulations to study how the Military and Air Traffic Control may collaborate in the future.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed tool has application to military operations for wartime and non-wartime activity. In wartime, the competition for airspace resources can be controlled in a collaborative solution by our tool. In non-wartime civilian airspace, the proposed tool has an application in the management of SUA activity in the NAS, allowing the military to coordinate the activation and de-activation of SUA in collaboration with the FAA.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Guidance, Navigation, and Control
Pilot Support Systems

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The Innovation Laboratory, Inc.
2360 SW Chelmsford Avenue
Portland, OR 97201-2265

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joseph Krozel
kreierk@aol.com
12475 Meadowgreen Place
Crevecoeur,  MO 63141-7431

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We build a software tool which enables the user (airline or Air Traffic Service Provider (ATSP)) the ability to analyze the flight-level-by-flight-level permeability of airspaces constrained by weather-hazards (turbulence, icing, and convection). The Airspace Analyzer automatically determines the space-time boundaries where weather hazards constrain capacity. The solution approach is based on an algorithm using computational geometry techniques for estimating the directional permeability of an airspace given the direction of the dominant demand flow on an airspace and the safety requirements of aircraft passing through the airspace. Phase I will result in theory, software, and examples that demonstrate proof of concept, and Technology Readiness Level (TRL) 3. Phase II will produce a prototype that demonstrates benefit to the airline and ATSP customer at TRL 4.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
For NASA, the proposed software product enables NASA researchers to investigate future NGATS concepts. Used in conjunction with a NAS-wide simulator like FACET or ACES, our software can be used to study Dynamic Airspace Configuration (DAC) adjustments in the NAS triggered by automated Flow Constrained Area (FCA) algorithms that we provide. DAC can potentially maximize capacity in highly constrained hazardous weather regions given our recommended FCAs and airspace usage results. DAC has a need to study where critical boundaries must transition from relatively unconstrained flight into capacity-constrained FCAs. Super Dense Operations (SDO) research also needs to evaluate the capacity around an airportal, and our Airspace Analyzer can be used to identify how SDO operations may be constrained by severe weather. Human factors investigations may be studied at NASA to evaluate further benefits and tradeoffs of this new approach to DAC and Traffic Flow Management (TFM) planning.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed software has application to military systems as well. In wartime, the constraints are very dynamic and automated airspace usage planning is required to support the pilot and the mission. The airspace may be constrained by weather, but also by hostile threats, both moving and stationary. With minor modifications, our solution approach for estimating the capacity of an airspace can be used to evaluate for a military a risk assessment for the threat level, possible avenues of approach, and estimates of total troop movement.

TECHNOLOGY TAXONOMY MAPPING
Guidance, Navigation, and Control
Pilot Support Systems
Autonomous Reasoning/Artificial Intelligence

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aerotech Research
11836 Fishing Point Drive, Suite 200
Newport News, VA 23606-4507

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Robinson
paulrobinson@atr-usa.com
11836 Fishing Point Drive, Ste 200
Newport News,  VA 23606-4507

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Every day, turbulence has an adverse effect on aircraft operations and capacity of the NAS, costing the airline industry at least $100 million annually in delays, operational inefficiencies, and injuries. There is a need to research and develop traffic flow and ATM methods that mitigate the turbulence impact to NAS operations, but turbulence is poorly represented in current airspace simulation and planning tools. AeroTech proposes to improve these tools and therefore airspace operations by developing and integrating an ATM Turbulence Impact Module (ATM-TIM) into FACET and/or ACES. The module will enable researchers and planners to identify and assess the impact of actual turbulence in the NAS and examine performance capability of new ATM methods with turbulence present. A key enhancement will be the incorporation of a turbulence dimension into the ATM Weather Impact Model that enables the modeling of the impact of convective and clear air turbulence. Phase I will develop the enhanced ATM weather impact model, investigate the integration of ATM-TIM components into the simulation tools, and perform a proof of concept study. By Phase III, the integrated ATM-TIM will improve planners understanding of turbulence's impact on ATM and assist in evaluating new TFM ideas in a turbulent NAS.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
When the goals of the proposed R/R&D are met, the ATM Turbulence Impact Module will be supportive of NASA's NGATS Airspace program's goal to "develop methodologies and techniques to minimize or solve the demand/capacity imbalance problem in the NGATS future." The ATM-TIM will support level 1 and 2 research areas in Traffic Flow Management, Separation Assurance, Performance Based Services, and System-Level Simulation Tools by improving traffic flow simulation tools through integration of turbulence information and ability to assess the impact of convective turbulence and CAT, enabling the assessment of new NGATS technologies and trajectory based operations principles against an ATM Weather Impact Model that incorporates turbulence, enabling the exploration of performance based operations based on aircraft equipped with improved turbulence detection and awareness systems, and enabling the development and testing of new TFM techniques within a NAS that includes turbulence constraints.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
AeroTech's ATM Turbulence Impact Module for FACET and/or ACES will provide the FAA and Joint Planning and Development Office a capability to examine NextGen capacity and throughput issues due to turbulence within the NAS, and assess the requirements for future turbulence detection and forecasting capabilities. Additionally they will be able to investigate and assess performance-based operations in NextGen based on new turbulence detection and awareness systems. The addition of the turbulence dimension to the ATM Weather Impact Model will provide higher educational institutions and research organizations the opportunity to revise and develop new TFM techniques and research convective and clear air turbulence impacts on NAS operations. Real-time application of the ATM-TIM in FACET could assist ATCSCC and airline operations centers in optimal flight planning and routing through improved turbulence awareness. The improved routing could result in reductions in delays and fuel savings, improved safety, and overall smoother NAS operations.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Requirements and Architectures
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Optical Scientific, Inc.
2 Metropolitan Court, Suite 6
Gaithersburg, MD 20878-4003

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ting-i Wang
tingwang@opticalscientific.com
2 Metropolitan Ct, Ste 6
Gaithersburg,  MD 20878-4003

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
OSI proposes to develop a wake vortex detection system including a group of double-ended and single-ended optical scintillometers properly deployed in the airfield to measure ground and near ground crosswind, turbulence, and wake vortex using atmospheric turbulence-induced optical scintillations. As part of efforts, OSI also proposes to develop a single-ended optical scintillometer, together with a retro-reflector, for the measurement of near ground real-time crosswind and wake vortex. OSI will perform system analysis and design of the proposed system to detect occurrences, location, magnitude, and persistence of wake turbulence. With the simultaneous measurements of crosswind and turbulence, the sensor system is also able to forecast the arrival time of the airplane generated wake vortex drifting to a nearby runway. In the Phase I effort, OSI will determine the optimum siting criteria of deploying the double-ended and single-ended sensors on the airport. This includes combinations of parallel to runway, cross the runway, and retro-reflector on high towers installations. The goal is to form a network of sensors to cover essential areas of airport field to provide wake vortex data for the predictive modeling of wake vortex hazard. As a side benefit, the vortex detection system could measure downdraft by deploying two sets of scintillometers on both sides of the runway. The line-averaged crosswind measured by the two sets will provide real-time continuous measurements of convergence and divergence of the wind field between the two optical paths. Vertical winds, and hence the downdraft, can be derived from the measured divergence. The proposed vortex detection system will also be able to provide critical large area wind information. By incorporating this valuable information into the low-level wind shear modeling, it will greatly enhance the performance of the present airport low-level wind shear systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA Airspace Systems (AS) Program has identified that advanced technologies to detect and avoid wake vortex hazards is critical for performing safe, closely spaced and converging approaches at closer distances than are currently allowed. One of the primary interests is Wake Vortex Hazard Solutions that include wake avoidance procedures for airports with closely spaced runways; characterization of wake vortex and atmospheric hazards to flight; and wake vortex alleviation/mitigation technologies. The proposed optical scintillometer and wake vortex detection system will provide critical real-time information that will increase throughput of an airport runway complex and achieve the highest possible efficiencies in the use of airportal resources. Super-density operations will entail reduced aircraft wake vortex separation standards. The proposed effort will lead to the development of wake vortex detection system that provides critical information relevant to NASA's NGATS-Airportal effort.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The FAA may require the vortex detection system successfully developed in this SBIR to be incorporated in the NGATS. The vortex detection and avoidance system will improve airport throughput and efficiency. More tests may be required and system may further improved in Phase 3 with FAA that will lead the system to TRL level 9 -the Actual system (flight) proven through successful mission operations. A TRL-9 system certainly has many market opportunities in domestic and international airports. To further expose OSI's products, OSI may team up with a large airport equipments vendor, such as the one with Airport Surface Traffic Configuration Management System. The team-up will lead to the large scale deployment of wake vortex detection systems at airports around the globe.

TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and Safety
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mosaic ATM, Inc.
1190 Hawling Place
Leesburg, VA 20175-5084

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryan Wood
wood@mosaicatm.com
801 Sycolin Road, Suite 212
Leesburg,  VA 20175-5686

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The complexity and interdependence of operations on the airport surface motivate the need for a comprehensive and detailed, yet flexible and validated analysis and modeling capability. This modeling and analysis can be used to identify the most beneficial areas of research for the Next Generation Air Transportation System (NGATS) -ATM Airportal Project. It is essential, therefore, that the modeling approach properly considers all operational activities and possible capacity constraints in the entire airport surface and terminal operation as a complete system. To accurately model airport surface operations with detail and accuracy, we propose that it is necessary to consider techniques and strategies used to determine the flight's taxi route, and to determine the sequence to be used whenever two or more flights have contention for a taxiway or runway resource. This proposed effort will produce tools to support fundamental research of the concept and requirements for airportal operations in the NGATS by providing microscopic airportal surface modeling components that provide higher fidelity and greater validity of modeling than previously available. Through this effort we will also enhance the Surface Operations Data Analysis and Adaptation tool to provide the analysis capabilities required to support this microscopic airport surface model.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work will support NASA's Airportal research and is highly relevant to NASA's Strategic Goals and Outcomes, as described in the 2006 NASA Strategic Plan. The project will produce tools to support fundamental research of the concept and requirements for airportal operations in the Next Generation Air Transportation System (NGATS) by providing microscopic airportal surface modeling components that provide higher fidelity and greater validity of modeling than previously available. In this way, the work supports NASA Strategic Goal 3E, "Advance knowledge in the fundamental disciplines of aeronautics and develop technologies for safer aircraft and higher capacity airspace systems."

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Aviation delays and the associated costs will continue to motivate research and development to improve air transportation efficiency and the airport surface domain has been largely neglected in the past, leaving substantial opportunities. The availability of advanced surface surveillance data is a new, enabling many novel applications for the data. In fact, this data is currently only available at a few airports. Much of the industry has not yet had access to this data and, therefore, has not started planning how it can be used. Still, the data will revolutionize the airport surface in ways not yet imagined. The enhancements to the SODAA technology provides a tool that can be used by airlines or airports for detailed analysis or standard reporting capabilities to analyze the efficiency of their airport's operations

TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and Safety
Data Acquisition and End-to-End-Management
Expert Systems
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mosaic ATM, Inc.
1190 Hawling Place
Leesburg, VA 20175-5084

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryan Wood
wood@mosaicatm.com
801 Sycolin Road, Suite 212
Leesburg,  VA 20175-5686

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal addresses the concept of Collaborative Outbound Taxi Metering (COTM), which provides environmental benefits without sacrificing throughput. In current operations, departure flights must block out of their parking gates to claim their first-come, first-served departure slot. When departure demand exceeds capacity, flights experience delay in departure queues near the runway. The need for flights to make incremental steps in the queue significantly increases the engine emissions produced because of the number of times aircraft must apply 'break-away' power, only to stop again after moving just a short distance. Under the COTM concept, metering techniques assign and maintain departure slots for all departure flights even if aircraft remain at their parking gates. Mosaic ATM has conducted initial analysis using historical operational data demonstrating the potential environmental benefits even in the presence of arrival flights requiring parking gates. This concept has already been applied and shown significant benefits during over-night operations of air cargo carriers. Implementing the concept across the entire NAS has not been possible due to the requirement to coordinate departure metering amongst multiple airport users. We propose to further demonstrate the feasibility and benefits of the COTM concept at large hub airports.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential applications for the research results beyond Phase 2 include uses by NASA for continued research and by the FAA and airports/air carriers. Moreover, research results may guide other airportal management projects by providing valuable understanding of environmental issues and how surface management decisions effects them. The proposed SBIR is focused primarily towards answering a research question of interest to NASA. The problem being studied is an example of the basic research needed into the interaction of airportal management and environmental metrics. The project will leave NASA with a new capability to study airportal environmental issues within the SODAA tool which NASA already uses for other airportal research. With environmental considerations becoming increasingly important to the FAA, airports, air carriers, and internationally, this capability will allow NASA to remain at the forefront of airportal research and provide relevant and valuable research results to guide NextGen development.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
FAA, university, and airport authorities may be equally interested in the developed airportal environmental analysis capability. Other potential Non-NASA applications are centered on the evolution of the research into a NAS-wide (or NextGen) system. The FAA is the most likely customer to continue this work beyond Phase 2. Commercialization and Phase 3 activities involve further development of the COTM implementation begun in Phases 1 and 2 and the conduct of field trials at one or more airports where the operational concept and procedures may be refined and actual benefits may be measured. Mosaic ATM has conducted field trials of this type previously with other automation tools and concepts. Airport authorities are expected to be interested in this technology, both domestically and internationally.

TECHNOLOGY TAXONOMY MAPPING
Airport Infrastructure and Safety
Data Acquisition and End-to-End-Management
Expert Systems
Software Tools for Distributed Analysis and Simulation

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michel Santos
msantos@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville,  MD 20855-2737

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation in this effort is the development of a simulation testbed for identifying dynamic air corridors that can increase aircraft throughput in and around the terminal airspace. In this proposal, an air corridor is a three-dimensional region of space that is intended to safely isolate a stream of aircraft from other aircraft outside the corridor. Air corridors/routes effectively exist today in two forms: static and dynamic. Static air corridors exist in the form of published standard arrival routes (STAR) and standard instrument departures (SID). Dynamic air corridors are effectively created when air traffic control (ATC) issues vector and speed instructions to aircraft. The proposed testbed would identify dynamic air corridors that provide ATC with more options that are optimized to provide greater throughput than is currently available with today's static air corridors. The testbed would continuously identify dynamic air corridors in order to adapt to changing hazards, changing queues of arriving and departing aircraft, and changing runway configurations. We further propose integrating the simulation testbed with NASA's Airspace Concept Evaluation Software (ACES) in order to assess the impact of dynamic air corridors on the entire U.S. national airspace.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Our initial target for the product developed in this effort is the modeling and simulation community within NASA that is focusing on the Joint Planning and Development Office's Next Generation Air Transportation System (NextGen). IAI is currently involved in developing and extending both ACES and CybelePro, which is currently used as the core modeling and simulation infrastructure for ACES. Given our intimate knowledge of our customer requirements, our partnership with the industry leaders such as ACSS Raytheon and SAIC, and fact that the need for a simulation environment for NGATS concepts have been identified by the JPDO, we are extremely confident of transitioning this technology into these markets.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Another target for the product developed in this effort is the modeling and simulation community within FAA that is focusing on NextGen concepts and operations. Another target is the modeling and simulation community within the Department of Defense that is focusing on crisis operations/First Responders. IAI is currently actively involved in each of these markets, and CybelePro is currently being used as the core modeling and simulation infrastructure in several of these efforts. Given our intimate knowledge of our customer requirements, our partnership with the industry leaders such as ACSS Raytheon and SAIC, and fact that the need for a simulation environment for NGATS concepts have been identified by the JPDO, we are extremely confident of transitioning this technology into these markets.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Waddan Systems
8801 Encino Avenue
Northridge, CA 91325-3228

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mahendra Singh
mahendra@waddansystems.com
8801 Encino Ave
Northridge,  CA 91325-3228

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of an Aircraft Nodal Data Acquisition System (ANDAS) is proposed. The proposed methodology employs the development of a very thin (135&#61549;m) hybrid microminiature sensor assembly (MSA) incorporating a micro-electro-mechanical-sensor (MEMS) array, a short-haul radio transceiver, a data mux, memory, power management module, a replaceable battery cartridge, and an antenna. Various MSA packaging concepts will be evaluated using modified MEMS and commercially available ICs (in die form). A final packaging design for batch fabrication in Phase II will be developed. The MSA would be designed as a cement-and-forget-device (except for the battery). A cpomactPCI modular host would manage the MSA nodes as a part of a scatternet/piconet arrangement. The host will be almost entirely made up of COTS hardware and software. Cost estimates for MSA and the host system will be provided.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
By adding real time aircraft dynamic modal assessment, real-time correlation and control algorithms, the MSA could be utilized in controlling light weight, flexible and even unstable flight subsystems. It can also be used in hard to access or remotely located nodes.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The MSA can be employed for monitoring of power plants, vehicle engines, or any other hard to access structural components. The monitoring concept can be employed for monitoring medically implanted devices in human body.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Launch Assist (Electromagnetic, Hot Gas and Pneumatic)
MHD
Integrated Robotic Concepts and Systems
Manipulation
Perception/Sensing
Airframe
Controls-Structures Interaction (CSI)
Testing Facilities
Testing Requirements and Architectures
Spaceport Infrastructure and Safety
Telemetry, Tracking and Control
Large Antennas and Telescopes
Modular Interconnects
Airport Infrastructure and Safety
On-Board Computing and Data Management
Pilot Support Systems
Biomolecular Sensors
Waste Processing and Reclamation
Autonomous Control and Monitoring
RF
Instrumentation
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Expert Systems
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Manned-Manuvering Units
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics
MHD and Related Conversion
Nuclear Conversion
Aircraft Engines
Aerobrake

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Research Support Instruments, Inc.
4325-B Forbes Blvd.
Lanham, MD 20706-4854

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Kline
kline@researchsupport.com
4325-B Forbes Blvd.
Lanham,  MD 20706-4854

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Research Support Instruments, Inc. (RSI) proposes to develop the Friction-Sensing Retroreflector Array Patches (FRAP), a technology that will measure the shear stress distribution on aerodynamic surfaces in ground test facilities with high resolution, sensitivity, and bandwidth. Unlike the oil-film interference method, FRAP patches will not be thinned as a function of time during a test. No knowledge of the streamlines of the flow will be needed in order to calculate the local stress distribution; this will avoid the tracers needed with the oil-film interference approach. Flexible patches of FRAP arrays, inexpensive due to simple, mass-production-compatible microfabrication techniques, will be interrogated using a light source and camera. FRAP will be independent of the flow species and applied as a very thin, flexible, adhesive material. The Phase I goals will be to design sensors, develop a microfabrication technique and use it to fabricate prototype units, demonstrate feasibility, and select the most promising design for Phase II development. In Phase II, the prototype units will be field-demonstrated at NASA facilities, with manufacturing issues and realistic operating conditions addressed. The result will be a product that will address a critical NASA instrumentation need.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
RSI will use its experience in microfabricated structures and sensors to employ a highly innovative technology – a sheer-stress-sensing retroreflector array – in order to non-intrusively measure skin friction in NASA ground test facilities. The concept can even be extended to flight tests: the arrays could be interrogated by the airdrop craft or a chase plane, with all the benefits of a retroreflected signal. The FRAP technology will avoid the use of a depleted fluid and tracer elements that are inherent to the existing oil film interferometry method, and will address a key NASA need for non-instrusive diagnostics as well as flight test diagnostics and vehicle monitoring.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Several non-Government applications are possible. Flow sensors have a lucrative commercial market in manufacturing (for process monitoring) and medical diagnostics, as well a healthy market in scientific applications. Commercialized flow sensors are used in applications ranging from industrial processing and medical diagnostics to high-speed shock testing in chemical explosions. It is expected that the newly developed FRAP arrays will compete aggressively in these existing markets. In addition to NASA, target U.S. government customers will be the Air Force (for ground testing, flight tests, and vehicle monitoring) and the Navy (for similar applications).

TECHNOLOGY TAXONOMY MAPPING
Control Instrumentation
Testing Facilities
Optical
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Traclabs, Inc.
8610 N. New Braunfels, Suite 110
San Antonio, TX 78217-4486

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Bonasso
r.p.bonasso@nasa.gov
8610 N. New Braunfels, Suite 110
San Antonio,  TX 78217-4486

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Automation and autonomy are key elements in realizing the vision for space exploration. The NASA Exploration Technology Development Program (ETDP) has been developing a procedure representation language (PRL) that both captures the form of traditional procedures and allows for automatic translation into code that can be executed by NASA-developed autonomous executives. However, PRL is in a relative infancy with regard to supporting many of the autonomous software components being developed by NASA, specifically automated planners and schedulers. In this proposal we will design and test additional representations to PRL for resources, inter-procedure constraints and subprocedures so that automated planners can take better advantage of the PRL-generated procedures. The work plan includes developing scenarios and use cases, developing requirements for planning -- both manual and automated -- from the scenarios, developing XML tags for the PRL changes, testing the PRL enhancements in the use cases with robotic and life support simulations, and translating the changes into planning languages with proven semantics.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Procedures are at the core of all NASA missions. Mission planning is also at the core of all space missions due to the high cost of space assets such as astronauts, equipment and communication links. Our technologies will have applications from Mission Control to on-board NASA vehicles and outposts. We expect applications of our technology to immediately impact NASA's Exploration Technology Development Program (ETDP). Two areas of ETDP will be immediate beneficiaries of this technology. First, the Centaur robot at NASA JSC is already using a preliminary version of PRL and a simple user interface to allow a remote supervisor to command the Centaur over a communication link. Our work will provide connection to automated planning technologies. Second, the Automation for Operations (A4O) project run out of NASA ARC is using PRL to enhance spacecraft operations. Our PRL extensions and planning technology would also be immediately applicable to spacecraft operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The military is currently a large customer for unmanned vehicle operations. Unmanned vehicles, both air and ground, are becoming more and more common in battlefield situations. Future Combat Systems (FCS) envision manned and unmanned vehicles of all sizes working side-by-side. In addition, Congress has mandated that one-third of all military vehicles must be unmanned by 2015. As these unmanned vehicles are increasingly deployed in tandem with dismounted forces coordinating software will be necessary to ensure successful operations. Procedures and mission planning play a large role in these kinds of operations. TRACLabs Inc. has an existing relationship with the Army's unmanned ground vehicle center at the TARDEC (Tank-Automotive Research, Development and Engineering Center) facility in Warren Michigan. The Army has established a new Joint Center for Unmanned Ground Vehicles (JC-UGV) at TARDEC with a new Systems Integration Laboratory (SIL).

TECHNOLOGY TAXONOMY MAPPING
Intelligence
Testing Requirements and Architectures
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
S&K Aerospace
63066 Old Hwy 93
St Ignatius, MT 59865-9008

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Arthur Molin
amolin@ska-corp.com
201 Flint Ridge Plaza
Webster,  TX 77598-4363

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA captures and distributes operational knowledge in the form of procedures. These procedures are created and accessed by a range of people performing many different jobs. These people have different needs for procedure data and different ways of interacting with procedures. We propose an Procedure Integrated Development Environment which will present different editing modes and different views depending on the users and tasks, but will use a consistent data representation for all users. We propose to explore alternate editing paradigms and discover which are the most valuable for NASA operations. We propose to build this environment on the basis of an existing prototype, PRIDE, which was developed for the Engineering Directorate of Johnson Space Center.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
An integrated development environment for procedures would improve the efficiency of the procedure authors by allowing them to concentrate on the fields in which they are expert, without worrying about details of editing and formatting. It would present each user with a procedure view that is most useful for the job at hand. It would connect up to the needed data sources and other related tools, such as workflow tools. It would provide a direct interface to simulation tools, which allow users to work out problems with procedures at the desktop, instead of requiring expensive high-fidelity simulations to be run to find minor problems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A procedure development environment would be potentially useful to a wide range of commercial and industrial interests that use a large number of procedures in their business. The electronic procedures that are proposed here would be of considerable interest to those industries that rely on procedures that could be automated, due to the availability of data sources. These industries include oil and chemical processing, power plants, and robotic assembly plants.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Operations Concepts and Requirements
Simulation Modeling Environment
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Data Acquisition and End-to-End-Management
Database Development and Interfacing
Human-Computer Interfaces
Software Development Environments
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aries Design Automation, LLC
6157 N Sheridan Road, Suite 16M
Chicago, IL 60660-5818

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Miroslav Velev
miroslav.velev@aries-da.com
6157 N Sheridan Rd, Suite 16M
Chicago,  IL 60660-5818

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We will develop an efficient tool for formal verification of PowerPC 750 executables. The PowerPC 750 architecture is used in the radiation-hardened RAD750 flight-control computers that are utilized in many space missions. The resulting tool will be capable of formally checking: 1) the equivalence of two instruction sequences; and 2) properties of a given instruction sequence. The tool will automatically introduce symbolic state for state variables that are not initialized and for external inputs. We bring a tremendous expertise in formal verification of complex microprocessors, formal definition of instruction semantics, and efficient translation of formulas from formal verification to Boolean Satisfiability (SAT). We will also provide formally verified definitions of the PowerPC 750 instructions used in the project, expressed in synthesizable Verilog; these definitions could be utilized for formal verification and testing of PowerPC 750 compatible processors, for FPGA-based emulation of PowerPC 750 executables, as well as in other formal verification tools to be implemented in the future.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The benefits to NASA will include state-of-the-art SAT-based technology for formal verification of PowerPC 750 executables. The PowerPC 750 architecture is used in the radiation-hardened RAD750 flight-control computers that are utilized in many space missions, including Deep Impact and the Mars Reconnaissance Orbiter. NASA will benefit from such a tool by being able to: 1) ensure that compiler optimizations have not introduced bugs in an executable, e.g., by checking for equivalence two versions of the code produced by different compilers or by the same compiler but with different optimizations, such that one of the sequences could be compiled without optimizations; 2) formally verify properties of code sequences that are written directly in assembly language for performance reasons; and 3) formally verify properties of executables provided by other organizations that do not supply the source code in order to protect their IP. As a secondary deliverable, NASA will get synthesizable Verilog definitions of the PowerPC 750 instructions used in the project; these definitions could be utilized for formal verification and testing of PowerPC 750 compatible processors, for FPGA-based emulation of PowerPC 750 executables, and for implementation of internal formal verification tools in the future.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercialization will target the members of Power.org, an organization whose purpose is to develop, enable, and promote PowerPC Architecture technology. Power.org has over 40 member companies. The PowerPC architecture is used in many safety-critical embedded systems. Non-NASA customers of this technology will similarly be able to use the tool to formally verify the equivalence of two instruction sequences, and to formally check properties for a given executable. Furthermore, non-NASA customers will be able to use the tool to detect security vulnerabilities in programs, thus ensuring their robustness to security attacks, as well as to detect malicious intent in executables. The last application will allow the technology to be used in sophisticated virus scanners for the PowerPC architecture, utilizing formal reasoning to ensure robustness to software obfuscations of malicious intent.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Guidance, Navigation, and Control
On-Board Computing and Data Management
Pilot Support Systems
Architectures and Networks
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Expert Systems
Software Development Environments
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Safeware Engineering Corporation
1500 Fairview Avenue E, Suite 205
Seattle, WA 98102-3727

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Grady Lee
lee@safeware-eng.com
1500 Fairview Ave. E., Ste. 205
Seattle,  WA 98102-3727

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Software testing is a complex and expensive phase of the software development cycle. Effective software testing is especially important in mission-critical software, where erroneous behavior poses a risk to safety or mission success. Automated test case generation can make testing more efficient and effective, saving resources and reducing risk. Safeware Engineering Corporation proposes to develop the algorithms necessary to streamline software testing by automatically generating test cases directly from SpecTRM-RL models. SpecTRM-RL (Specification Tools and Requirements Methodology - Requirements Language) is a requirements language that was designed to be highly readable, allowing even non-specialists to understand them, but also completely formal. A SpecTRM-RL model specifies the black-box behavior of the system; test cases based on these requirements will focus on the intended behavior of the system. A smaller set of test cases will allow for more rapid error identification, while a larger set will provide more comprehensive coverage. The algorithms will have varying levels of completeness, allowing for a trade-off between test coverage and testing resources. Safeware provides a tool, SpecTRM, which assists analysts with editing, analyzing, and executing formal requirements models. A phase II effort would implement these algorithms, adding test-case generation to SpecTRM.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is involved in the development of complex systems that are highly reliant on software, such as human-rated space vehicles. These systems must be reliable and safe, but also affordable to develop and maintain. NASA has recognized the need for innovative requirements analysis methods and automated tools; the basic SpecTRM toolset was developed under a NASA SBIR. The addition of automated test case generation to the SpecTRM toolset will provide testers with valuable assistance, streamlining software testing. The algorithms developed by the proposed research, as well as the tool to be developed in Phase II could potentially apply to any NASA project with a need for reliable, safe and cost-effective mission-critical software.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The need for innovative requirements analysis methods and automated tools has been recognized across industries as varied as aerospace, automotive, defense, and medical device, providing an ample market for such a tool. In fact, the basic SpecTRM toolset, which was developed under a NASA SBIR, is now used in the aerospace industry, for example, the Japanese Space Agency (JAXA and JAMSS) have used it extensively on their space projects and in the defense industry. JPL completed a successful Technology Infusion project to evaluate the use of SpecTRM for TeamX. Lockheed Martin Space Systems has expressed interest in using SpecTRM on the Orion space vehicle. The addition of automatic test-case generation to the SpecTRM toolset will be applicable to these projects and others throughout the industry.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Testing Facilities
Testing Requirements and Architectures
Software Development Environments

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Structured Materials Industries, Inc.
201 Circle Drive No., Suite 102-103
Piscataway, NJ 08854-3723

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gary Tompa
gstompa@structuredmaterials.com
201 Circle Drive No., Ste. 102-103
Piscataway,  NJ 08854-3723

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Field Programmable Gate Arrays are a widely used technology; however, they are generally limited in reprogrammability. Radiation hard, low power and high density ReProgramable FPGAs (RP-FPGAs) would be a tremendous asset in long duration missions. The ability to adapt to changeing mission profiles and on board capabilities is highly desirable. We herein propose to develop a RP-FPGA for flight use. In Phase I we will prove basic device concepts working with a leading FPGA manufacturer. In Phase II we will develop a viable demonstration prototype that will enable routine Phase III device manufacture.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Long duration missions often must adapt to changes in mission capabilities and mission profiles. This project will provide NASA mission planners (and prime contractor builders) with a significant enhancement in device programming capability

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
FPGAs serve a wide range of applications as an alternative to ASICs. Highly desirable is a FPGA that could be reprogrammed. Product revisions are often constrained by past programmed logic or suffer from extra cost as programmed arrays must be replaced. A reprogrammable gate array would be a significant benefit to product designers and enable a new form of product upgrade to be easily carried out - hence offering opportunity to gain a significant market share.

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sienna Technologies, Inc.
19501 144th Avenue NE, Suite F-500
Woodinville, WA 98072-4423

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ender Savrun
ender.savrun@siennatech.com
19501 144th Avenue NE-Suite F-500
Woodinville,  WA 98072-4423

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed program will develop an hermetic, CTE matched, thermal shock resistant ceramic packaging technology that will facilitate the operation of Si and SiGe devices at extreme temperatures (-230ºC to 130ºC) encountered on the Moon and Mars. Processes to assemble the components into a hermetically sealed package will be identified and developed. Process and materials capability will be demonstrated by fabricating and testing a 12 or 28 pin single chip module test vehicle.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Si3N4 ceramic package capable of operating at extreme temperatures will provide an enabling technology for space exploration efforts including Moon and Mars missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are several terrestrial applications that stand to benefit from the development of extreme environment microelectronic devices and associated packaging by achieving performance improvements and competitive advantages. These applications include low temperature radiation environments, magnetic levitation transportation systems, medical diagnostics, cryogenic instrumentation, and super conducting magnetic energy storage systems. The use of power electronics designed for and operated at low temperature is expected to result in more efficient systems than room temperature systems.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Acellent Technologies, Inc.
835 Stewart Drive
Sunnyvale, CA 94085-4514

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shawn Beard
sjb@acellent.com
835 Stewart Drive
Sunnyvale,  CA 94085-4514

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Major concerns for implementing a practical built-in structural health monitoring system are prediction accuracy and data reliability. It is proposed to develop robust state-of-the-art structural health management (SHM) technologies to overcome these concerns. The proposed solution will be capable of detecting and quantifying damage with a high probability of detection (POD), accurately predicting the residual strength and remaining life of the structures with confidence, and providing information which will allow appropriate preventative actions on the monitored structure. To achieve the objectives the proposed technology will first optimize the sensor network configuration for the SHM system to achieve the highest probability of detection. Next, robust diagnostic techniques will be developed to achieve quantifiable damage location and size estimation that account for the uncertainties induced by the environments or the system itself continuously during flight or at scheduled maintenance intervals. Finally, efficient probabilistic prognostic methods will be integrated with diagnostic outputs to provide real time estimation of residual strength and remaining life of the damaged structure. Both metallic and composite stiffened aircraft panels will be instrumented and tested under simulated flight conditions to validate the proposed technology. The work will be performed collaboratively between Acellent and Stanford University.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The SHM system can be used in all types of NASA aircraft, reusable space transportation vehicles such as boosters, shuttles, and CEVs, space habitation facilities such as space stations and outposts on the moon and Mars, and for the inspection and maintenance of any other mission critical space structures. The system developed can be used in the near-term for reusable space transportation systems and will be scalable for future missions to the moon, Mars, and beyond.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Since nearly all in-service spacecraft and aircraft structures require some form of inspection and maintenance procedures to monitor their integrity and health condition to prolong life span or to prevent catastrophic failures, the potential applications of the proposed system are very broad and extend well beyond space structures. The system can potentially be used to monitor damage in all military and commercial aging aircraft and rotorcraft structures, and civil structures such as bridges, buildings, oil platforms, etc.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Airframe
Airlocks/Environmental Interfaces
Erectable
Inflatable
Kinematic-Deployable
Launch and Flight Vehicle
Spaceport Infrastructure and Safety
Thermal Insulating Materials
Modular Interconnects
Structural Modeling and Tools
Tankage
Instrumentation
Production
Sensor Webs/Distributed Sensors
Tools
Ceramics
Composites
Metallics
Multifunctional/Smart Materials
Aircraft Engines

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gregory Kacprzynski
greg.kacprzynski@impact-tek.com
200 Canal View Blvd
Rochester,  NY 14623-2893

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Impact Technologies LLC, with support of the University of California Santa Cruz, proposes to develop and demonstrate a set of enhancements to NASA's Hybrid Diagnostic Engine (HyDE) that represent valuable and, in some cases, critical features for IVHM system developers in NASA and non-NASA application domains. Specifically, the Impact team believes that in order for HyDE to transition to a broad customer base, HyDE must meet commercial-grade software standards as well as provide 1) an innovative and powerful software-based model validation and verification environment must be integrate with Matlab/Simulink, 2) sophisticated third party plug-ins to translate from a Bayesian Network modeling paradigm and integrate generic signal validation tools and 3) the capability to generate and deploy models for common embedded targets in an efficient and user friendly package. The project team intends to define, develop and demonstrate the feasibility of these innovative and significant enhancements to HyDE with NASA's Advanced Diagnostic and Prognostics Testbed (ADAPT) as a realistic and sufficiently complex case study.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA has already utilized HyDE for some of its IVHM applications as well as its predecessor, Livingstone 2. However, the proposed HyDE enhancements will make major strides towards a comprehensive and commercial-grade IVHM design tool that will provide greater overall benefit to NASA IVHM application developers and most likely greater exposure of the software product.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The need for improved IVHM design tools and reasoning capability within the DoD is very significant given aggressive diagnostic and prognostic requirements for major new acquisition programs like JSF and FCS. Impact Technologies is directly involved in these and other DoD programs and views HyDE, with the proposed enhancements, as a powerful tool that can address this need.

TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data Management
Pilot Support Systems
Autonomous Control and Monitoring
Autonomous Reasoning/Artificial Intelligence
Software Development Environments

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Scientific Concepts, Inc.
305 E. Haley Street
Santa Barbara, CA 93101-1723

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bardley Short
bshort@asc3d.com
305 E. Haley Street
Santa Barbara ,  CA 93101-1723

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
3D Flash Ladar is a breakthrough technology for many emerging and existing 3D vision areas, and sensor improvements will have an impact on nearly all these fields. In addition ASC is partnering with many strategic large companies who have the experience and the history of commercialization. The compact, low power 3D Flash Ladar sensor developed on this project will have application in areas such as: 1. Collision avoidance 2. Pedestrian Safety 3. Surveillance 4. Terrain Mapping 5. Autonomous Navigation 6. Smart intersection 7. Radar brakes 8. Robotics 9. Machine Vision 10. Hazard Material Detection and Handling 11. Underwater 3D Imaging 12. Sub Nanosecond Dynamic Imaging.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The 3D Flash Ladar (3DFL) technology improvements developed on this project can support future Rendezvous, Proximity Operations, and Docking as well as EDL missions for lunar or planetary exploration. Not only will the sensor be able to generate 6 Degree-Of-Freedom data but it can also support hazard mapping and navigation as well as other terrain mapping requirements. The camera includes a fog, dust and liquid penetration mode, which will allow landing and navigation in hazardous conditions. This sensor will increase the success of NASA operations such as: 1. Rendezvous and Docking 2. Situational awareness 3. Mars Landed Exploration 4. Exploration of Moons (ALHAT, Jupiter Icy Moons) 5. Asteroid and comet rendezvous and sample return 6. Rock abundance and distribution maps 7. Topographical mapping 8. Rover mobility and navigation

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
3D Flash Ladar is a breakthrough technology for many emerging and existing 3D vision areas, and sensor improvements will have an impact on nearly all these fields. In addition ASC is partnering with many strategic large companies who have the experience and the history of commercialization. The compact, low power 3D Flash Ladar sensor developed on this project will have application in areas such as: 6. Collision avoidance 7. Pedestrian Safety 8. Surveillance 9. Terrain Mapping 10. Autonomous Navigation 11. Smart intersection 12. Radar brakes 13. Robotics 14. Machine Vision 15. Hazard Material Detection and Handling 16. Underwater 3D Imaging 17. Sub Nanosecond Dynamic Imaging.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Optical Systems, Inc.
6767 Old Madison Pike, Suite 410
Huntsville, AL 35806-2181

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Fred Roe
roe@aos-inc.com
6767 Old Madison Pike Suite 410
Huntsville,  AL 35806-2181

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Orion requires a rendezvous and docking sensor to provide relative navigation information during proximity operations and docking. In order to dock, the sensor must provide full six degree of freedom (6 DOF) relative position and relative attitude information at a rate sufficient for the rendezvous spacecraft guidance system to robustly control the docking maneuver. Orion faces critical weight issues that make inclusion of multiple sensors for AR&D unlikely in its baseline configuration. Locations for mounting the sensors external to the spacecraft are also critical issues. A bore sight camera however will be included in the design to furnish crew video data for the final docking maneuvers. Clever utilization of this existing Orion bore sight camera can provide a robust 6DoF capability with only the addition of vision processing software.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are numerous potential applications for AR&D within the NASA. The Orion crew will require a relative navigation sensor to successfully dock with the ISS. The COTS program seeks to provide commercial resupply to the ISS. A prox ops sensor and automated control system is required to hold the rendezvous vehicle in a control box such that the SSRMS can grapple the payload and berth it to the ISS. The Exploration initiative requires an automated docking in lunar orbit in order to safely return the crew to earth. Space construction in lunar orbit will be required to support the colonization of the lunar surface and an expedition to Mars. AR&D sensors are required to support these and future efforts.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Formation flying is important for the Department of Defense (DoD) as well as NASA. Relative position and attitude measurements would enable next-generation surveillance missions involving formation flying with tight tolerances. These AR&D sensor technologies can enable advances in in-flight aerial refueling for DoD aircraft, particularly unmanned aerial vehicles (UAVs). Enhancing UAV capabilities is one of the major focus areas of DoD research and development funding. Finally, the commercial space market, fueled by prizes similar to the 2004 Ansari X-prize, has made orbital vehicles with AR&D capabilities the next great priority for privately-funded spacecraft.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Attitude Determination and Control
Guidance, Navigation, and Control
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Scientific Concepts, Inc.
305 E. Haley Street
Santa Barbara, CA 93101-1723

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steve Silverman
ssilverman@asc3d.com
305 E. Haley Street
Santa Barbara,  CA 93101-1723

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Scientific Concepts, Inc. (ASC) has developed a 128 x 128 frame, 3D Flash LADAR video camera which produces 3-D point clouds at 30 Hz. Flash Ladar Video Cameras are 3D vision systems that return range and intensity information for each pixel in real time. The ASC camera is the equivalent of 16000 range finders on a single chip. This allows the sensor to act as a 3D video camera with functionality well beyond just range finding. A previous Phase I EDL project used an ASC camera at the JPL mars yard to gather test data. Hazard Identification, and Entry Decent and Landing applications were investigated and the data demonstrated that a Flash LADAR system can resolve landing hazards and is suitable as an EDL sensor. In response to this solicitation ASC will study unit cell designs that will increase sensitivity and dynamic range and allow for more compact unit cells that will yield higher density arrays. The Phase two effort will yield a ROIC design and fabrication of a unit cell. The end result will be a ROIC design ready for Phase 3 production of a large area array. These improvements will increase the TRL level of this sensor.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The 3D Flash Ladar (3DFL) technology improvements developed on this project can support future Rendezvous, Proximity Operations, and Docking as well as EDL missions for lunar or planetary exploration. Not only will the sensor be able to generate 6 Degree-Of-Freedom data but it can also support hazard mapping and navigation as well as other terrain mapping requirements. The camera includes a fog, dust and liquid penetration mode, which will allow landing and navigation in hazardous conditions. This sensor will increase the success of NASA operations such as: 1. Rendezvous and Docking 2. Situational awareness 3. Mars Landed Exploration 4. Exploration of Moons (ALHAT, Jupiter Icy Moons) 5. Asteroid and comet rendezvous and sample return 6. Rock abundance and distribution maps 7. Topographical mapping 8. Rover mobility and navigation

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
3D Flash Ladar is a breakthrough technology for many emerging and existing 3D vision areas, and sensor improvements will have an impact on nearly all these fields. In addition ASC is partnering with many strategic large companies who have the experience and the history of commercialization. The compact, low power 3D Flash Ladar sensor developed on this project will have application in areas such as: 1. Collision avoidance 2. Pedestrian Safety 3. Surveillance 4. Terrain Mapping 5. Autonomous Navigation 6. Smart intersection 7. Radar brakes 8. Robotics 9. Machine Vision 10. Hazard Material Detection and Handling 11. Underwater 3D Imaging 12. Sub Nanosecond Dynamic Imaging.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
nLight Photonics
5408 NE 88th Street, Building E
Vancouver, WA 98665-0990

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Shabbir Bashar
shabbir.bashar@nlight.net
5408 NE 88th Street, Building E
Vancouver,  WA 98665-0990

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to build a monolithically integrated FPA of densely packed APDs (70-um pitch) operating at or around 1500 nm wavelength that is suitable for the solicited autonomous precision landing and hazard detection and avoidance system. These would be capable of 3D imaging an area of 150m x 150m from a distance of 1 – 2km. By using highly efficient detector material (InGaAs/InP) a number of significant advantages can be leveraged. These include compactness, low mass, low cost and most importantly low power consumption and low thermal dissipation which are of primary concern in a remote environment such as the un-manned Lunar or Mars landing vehicles. It is expected that each pixel will have modest speeds (1 nano-second response time), high gain (>30) and ultra low-noise (k < 0.2) and that the FPA is easily manufactured using established growth, fabrication and packaging technologies. These FPAs would be bump-bondable to an appropriate Read Out Integrated Circuit (ROIC) that can reliably sustain a frame fresh rate of at least 20Hz and be capable of resolving depths of a few centimeters.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
3D Flash LADAR for Mars/Lunar Landing autonomous vehicle Remote sensing

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
3D Flash LADAR for automotive collision avoidance systems Medical Imaging Strategic military imaging Remote sensing

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Photonics
Power Management and Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Q-Peak, Inc.
135 South Road
Bedford, MA 01730-2307

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Glen Rines
grines@qpeak.com
135 South Road
Bedford,  MA 01730-2307

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a significant improvement in the performance of diode-pumped, Nd:YLF lasers by employing direct optical pumping of the upper level of the 1-micron laser transition. This novel pumping technique has been applied to other Nd laser systems, notably Nd:YAG and Nd:vanadate, but to our knowledge this has not been successfully applied to Nd:YLF laser systems. Q-Peak is in a unique position to develop this technique specifically for Nd:YLF owing to the extensive work that we have done over the past decade in developing our patented MPS systems, which employ Nd:YLF as the gain medium. Researchers who have applied this pumping technique to Nd:YAG have shown an increase in slope efficiency of about 20% and a reduction in thermal load of about 30%. We expect to see similar levels of improvement in Nd:YLF performance in this project.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed work has direct application to NASA programs for entry, descent and landing (EDL) systems in future lunar and planetary exploration missions. In particular, flash ladar systems that can provide real-time, three-dimensional terrain mapping capability would be useful for automation of terminal descent of unmanned vehicles. For this application the emphasis must be placed on compactness, reliability, efficiency, low weight, and high performance. The system concept we propose provides improved performance, due to higher efficiency, scalability, and modularity and the potential for improvement in overall system efficiency and the reduction in the required number of diode pump lasers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed high-efficiency, high-energy MPS technology would be an extension of our existing diode-pumped product line and would offer a step-up in efficiency and energy from our existing products. A MPS Nd:YLF laser with 10 to 100 mJ/pulse fundamental energy, and high beam quality, with the addition of harmonic generation for some systems, could provide a relatively low-cost solution for precision machining applications such as marking, cutting, welding and drilling, of interest to the electronics, automotive and medical-device industry. Q-Peak, as it is now doing with the MPS product line, would strive to establish OEM relationships with systems integrators who supply machining and processing tools to end customers.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Guidance, Navigation, and Control
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Seldon Laboratories, LLC
7 Everett Lane, Suite One
Windsor, VT 05089-0710

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Proehl
jproehl@seldontech.com
PO Box 710
Windsor,  VT 05089-0710

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Seldon Laboratories, LLC, will apply its patented carbon nanotube filtration technology for air and nanoscale particulate engine exhaust filtration to NASA's Lunar Exploration challenges. This project focuses on the problem of efficient removal of nanoscale (10-100nm) and larger lunar dust particulates from air using a nanostructured fiber media containing carbon nanotubes. Lunar dust presents an important challenge to Lunar exploration and habitation, nonetheless it has some unique properties that can be taken advantage of in designing specialized filtration media capable of achieving efficient removal from air. The rough surface shape combined with the electrically and magnetically charged nature of the dust means that rough, electrically activated filtration media will be effective tools for filtration. Seldon's work with its proprietary fused carbon nanotube media offers a unique path to significant new purification applications that meet important needs for NASA's Lunar Exploratory Initiatives. The unique physical properties of the carbon nanotubes will be capitalized upon to create a filtration media with high efficiency and low pressure drop that can be electrically powered to enhance filtration of charged lunar dust particles.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are important applications for this product throughout NASA's operations from protecting human life on lunar explorations, to cleaning the air of clean rooms, to reducing emissions from its vehicle fleet. The potential health and environmental impacts of airborne ultrafine particles are now known to be significant. Typical filtration solutions struggle to remove these very small contaminants. As a result, energy is wasted and, because of cost, some filtration applications are just not pursued. Products based on this technology will protect astronauts and sensitive equipment from lunar dust in the air handling systems of spacecraft and even in personal breathing apparatus. They will efficiently remove very small particulates from the air in NASA's clean rooms. Finally, filters will help to clean the emissions from the many earthbound diesel and other engines NASA operates to help reduce NASA's carbon footprint and improve the health of its employees and communities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The estimated global market size for air purification equipment is estimated by some observers to be about $2.5 billion. As the public awareness of the health and environmental consequences of very fine particles increases, the demand for improved filtration will continue to increase. Protecting humans, animals, and delicate machinery from these tiny contaminants will continue to be a growing opportunity. The care that has been given to filtration in clean rooms will likely be more common in other spaces such as offices and vehicles. Through careful strategic partnerships, products based on this technology will be sold to fit into the many air handling systems (e.g., vehicles, emission systems, and HVAC systems) that are already in wide use. Seldon has successfully produced thousands of linear feet of a related carbon nanotube media – proving that the media can b easily manufactured.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Sterilization/Pathogen and Microbial Control

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Reactive Innovations, LLC
410 Great Road, Suite C-2
Littleton, MA 01460-1273

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Kimble
mkimble@reactive-innovations.com
410 Great Road, Suite C-2
Littleton,  MA 01460-1273

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA desires to generate and store gases including oxygen and nitrogen at sub-critical conditions as a part of its lunar and spacecraft atmospheric systems. Oxygen at pressures up to 3000 psia is particularly desired for refilling storage tanks for lunar and in-flight applications including recharging high-pressure gas bottles for EVA/EMU, lunar rovers and surface hoppers, and lunar chemical process reactors requiring oxygen as a reactant. To address these needs, Reactive Innovations, LLC proposes to develop a compact high-pressure oxygen concentrator that can take low-pressure atmospheric gas and generate a separate stream of high-pressure pure oxygen. During the Phase I program, we will modify and adapt our high-pressure reactor hardware to compress and separate an oxygen stream up to 3000 psia from an ambient air source containing nitrogen and oxygen. A predictive performance model will be developed for the oxygen concentrator allowing NASA mission planners to conduct trade studies on metrics including the generated oxygen rate per compressor mass and power requirements. By the end of the Phase I effort, this concentrator will be at a Technology Readiness Level of 3 with a Phase II program delivering a 3000 psia operational oxygen generator and compressor at a TRL of 4-5.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Applications of this technology to NASA include generating oxygen for sub-critical storage on lunar habitats and within spacecraft environments. This technology will enable pressurized oxygen up to 3000 psia to be used for applications where cryogenic storage is not feasible or desired. Furthermore, NASA desires to use re-configurable modules that can function in dual-use or multi-use systems in these habitation environments. With our modular reactor technology, this process unit can be used for other atmospheric gas processing applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications of the proposed technology could find use in portable oxygen generators and concentrators for medical usage. This could be used in hospital and home therapy applications. Other applications of the oxygen compressor include on-site oxygen production for industrial and manufacturing needs, and on-board oxygen generation on aircraft.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Portable Life Support
Energy Storage
Renewable Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nanomaterials Company
15 North Bacton Hill Road
Malvern, PA 19355-1005

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Nicholas V. Coppa
ncoppa@nanomaterialscompany.com
15 North Bacton Hill Road
Malvern,  PA 19355-1005

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose a new spray drying technology for the recovery and recycle of water while stabilizing the solid wastes or residues as found in advanced life support systems. The proposed effort is focused on the recovery of water from concentrated waste water recovery system brine and other concentrates. Hypogravity and microgravity environments will make space based systems compact thus reducing its equivalent system mass. The application of spray drying to brine is a first step in the development of a space-based system but spray drying is likely to be applicable to the dewatering and stabilization of solid wastes. Spray drying is a one step continuous process where a solution, slurry, sludge or paste is transformed from a fluid state to dried masses by spraying the feed into a hot drying medium. The resulting dry products are granules or agglomerates and the drying medium bearing the removed moisture. Using one of several methods the drying medium yields the recovered water. The exact nature of the dried solid and recovered moisture depends on the physical and chemical properties of the feed and the design and operation of the drier. At the end of Phase II the technology will be at a TRL = 6.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Hypo and microgravity spray drying technology will largely close the water recycle loop for long interplanetary missions, and lunar and mars surface missions. Spray drying can be applied to several points in the advanced life support water recycle system including water recovery from solid wastes and the stabilization of the solid residues with low ESM. The proposed Phase I work will provide NASA with bench testing performance data and a design for a system capable of rendering concentrated aqueous solutions with viscosities and heat capacities similar to those relevant to life support systems. Component interchangeability allows a wide variety of input streams while avoiding cross contamination and other real or perceived problems associated with the processing of potable and non-potable streams. Advanced controls allow for process optimization of any waste stream without bench tests or prior characterization of the waste stream. The proposed work will serve as a foundation for more advanced space manufacturing operations, including resource recovery, space manufacturing and any other area where efficient, safe physical separation of solids and liquids is required. The work proposed here will lay the foundation for future hypo and microgravity spray drying resource recovery system designs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Nanomaterials seeks the opportunity to provide NASA with new life support tools, but as important to this goal is the opportunity to explore new production tools so that we can reach a wider customer base. We believe the proposed work will be directly applicable to our in-house materials processing needs. This often involves the recovery of valuable solvents during the processing of our materials. Spray drying is a process with applications throughout industry and products touching every aspect of nearly every American. The application of spray drying to space water recovery problems will spawn new development. Because its use is so wide spread, it will have great economic impact. One innovative aspect of our proposal will likely lead to its application to materials not currently processed via spray drying and may lead to less expensive proprietary pharmaceutical compounds.

TECHNOLOGY TAXONOMY MAPPING
Air Revitalization and Conditioning
Biomass Production and Storage
Sterilization/Pathogen and Microbial Control
Waste Processing and Reclamation
Earth-Supplied Resource Utilization
In-situ Resource Utilization
Microgravity

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
UMPQUA Research Company
PO Box 609
Myrtle Creek, OR 97457-0102

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel urine pretreatment that will prevent biological growth or chemical instabilities in urine without using hazardous chemicals is proposed. Untreated urine fosters biological growth, ammonia generation, creation of bio-solids, and inorganic precipitates, which foul water and air reclamation hardware. The current Russian system employs hexavalent chromium, a strong oxidant and carcinogen, and sulfuric acid to stabilize urine, while the American system utilizes potassium monopersulfate, another strong oxidant, sulfuric acid, and potassium benzoate. Urine stabilized in these respective manners requires triple and double containment, and chemical storage and handling become problematic due to the hazardous nature and low pH (1.3 –2.6) of these chemicals. These requirements significantly increase urine pretreatment ESM. The proposed pretreatment system consists of a simple flow-through Solid Phase Acid (SPA) bed containing sparingly soluble transition metal oxide particles for pH control, which combined with a soluble non-oxidizing biocide will provide long-term urine stabilization. This innovative system fulfills an unmet need for safe, efficient and automated urine pretreatment for current and future NASA missions. The Phase I effort will demonstrate the feasibility of this novel approach. The Phase II project will fully develop the process, including the design and testing of deliverable hardware for urine pretreatment.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The NASA application of this innovative, safe, efficient and automated urine pretreatment hardware will be as Flight Hardware for deployment in support of future long duration exploration objectives such as a lunar mission, lunar base, Mars transit or Mars base. The primary application will be as a replacement for current urine pretreatment systems aboard the International Space Station (ISS) and on the Lunar Outpost (LO). Secondarily, this device can be utilized to stabilize other waste streams, which are prone to microbial instability. It is anticipated that numerous other uses will be found for this system within NASA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This urine pretreatment technology may be employed in a variety of applications to provide a means for safe and stable urine storage. In the near term, this technology can be applied to storage onboard recreational vehicles, ships, or in conjunction with portable restroom facilities. The capability to effectively store urine can be the basis for a new technology, in which, urine is collected in bulk, stored, and treated to reduce the environmental impact of treatment facilities and improve treatment efficiency. The development of SPA units and biocides with well-characterized performance will facilitate this development. In addition, SPA beds may be used for control of pH in a variety of circumstances including analytical instrumentation and industrial processes.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Sterilization/Pathogen and Microbial Control
Waste Processing and Reclamation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Aerodyne Research, Inc.
45 Manning Road
Billerica, MA 01821-3976

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Freedman
af@aerodyne.com
45 Manning Rd
Billerica,  MA 01821-3976

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to design, build and test an optical extinction monitor for the detection of spacecraft cabin particulates. This monitor will be sensitive to particle sizes ranging from a few nanometer to tens of micrometers in diameter. Designed to utilize commercial off-the-shelf components, the monitor, once calibrated, will require no recalibration and only periodic baseline determinations, a process which can be automated as part of the operation of the instrument. It employs no consumables. This monitor employs cavity attenuation phase shift technology and involves the use a light emitting diode coupled to a low-loss optical cavity. The Phase I project will involve a proof-of-principle demonstration followed by the monitoring of ambient particulates in an urban area.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This sensor can be deployed on board spacecraft cabins for the purpose of monitoring the presence of airborne particulates. It can also be used for the same purpose in climate change studies where particulate concentrations and their optical extinction are key parameters in determining the amount of radiation forcing attributable to the presence of particles in the atmosphere. The low cost of this sensor will allow the deployment of far more sensors of this type than are currently used.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are two large commercial markets for this technology. The first is as a direct competitor to 'smoke nunber' measurement devices which are used to measure the opacity of combustion plumes from aircraft engines and smokestacks. The other involves in situ monitoring of diesel engine exhaust emissions with respect to the presence of PM2.5, a newly designated criteria pollutant.

TECHNOLOGY TAXONOMY MAPPING
Optical

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vista Photonics, Inc.
67 Condesa Road
Santa Fe, NM 87508-8136

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joerg Kutzner
jkutzner@vistaphotonics.com
67 Condesa Road
Santa Fe,  NM 87508-8136

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Reliable and efficient fire detection is a precondition for safe spaceflight. The threat of onboard fire is constant and requires early, fast and unfailing detection. Current fire detectors are prone to fatigue and have insufficient sensitivity, selectivity and time-response. Smoke detectors cannot detect early stages of combustion and become unreliable if exposed to dust particulates. New sensor technology is required to face the challenging tasks associated with future space exploration involving missions to the Moon and Mars. Carbon monoxide formation is a reliable indicator of evolving fire threats onboard spacecraft and this gaseous combustion product allows rapid early detection. Vista Photonics proposes to evaluate and implement emerging infrared light sources for high-performance optical CO detection. Optical sensors are particularly favorable due to unique features like fast response, high precision and strong species selectivity. Design criteria such as small footprint, low weight, low power consumption as well as internal calibration and continuous sensor health monitoring will be implemented to provide a spaceflight optimized sensor. The proposed optical absorption approach uses modulation techniques together with a compact path length enhancing cell with a small sample volume.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The targeted NASA application is early detection of fire threats onboard spacecraft. The emerging technology is adaptable to changing pressure conditions and suitable to operate in diverse environments, including corrosive atmospheres. The developed technology can be extended to selectively detect trace gas species for NASA relevant applications such as contaminant sensing in air revitalization and water recovery processes, and atmospheric composition monitoring.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The developed sensor will be a general device for highly reliable, sensitive fire detection and might find applications in protecting high value buildings and fire prevention in aviation. Beyond these applications, the developed sensor platform will be broadly deployable for trace gas detection of a variety of molecules with a cost-effective, small device. Applications include environmental monitoring and protection, occupational safety, modern manufacturing, and biomedical applications.

TECHNOLOGY TAXONOMY MAPPING
Spaceport Infrastructure and Safety
Airport Infrastructure and Safety
Optical

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Bomse
dbomse@swsciences.com
1570 Pacheco Street, Suite E-11
Santa Fe,  NM 87505-3993

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Spacecraft fires create exception risks to crew members. There is usually no place to escape. Even small amounts of hardware damage can compromise a mission. The most effective fire extinguishing agents, Halons, are prohibited because of the toxicity and corrosiveness of combustion byproducts. Early warning fire sensors are needed that can operate effectively in zero gravity; that means no convection to transport smoke or fire-generated gases to point sensors. Avionics compartments are often densely packed and filled with dead spaces that do not exchange air well with circulating air streams. Southwest Sciences proposes the development of a thermal mirage sensor for detecting incipient spacecraft fires. The sensor will use highly miniaturized, low power cameras to image a simple geometric pattern projected onto a flat surface. Thermally induced image distortions will provide early fire warning. The sensor will operate autonomously; we anticipate a networked set of such sensors, each having sufficient signal processing capability to determine sensor health and alarm conditions. Our innovation includes the use of highly miniaturized, low cost components. The cross line projector is a laser pointer combined with a small (4 mm × 4 mm) piece of etched clear plastic; diffraction forms the line pattern. There are no moving parts.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed thermal mirage sensor has obvious fire detection applications in nearly all types of NASA spacecraft, habitats, and large-scale, high loss, ground electronics and mechanical installations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed thermal mirage sensor has obvious fire detection applications in commercial and military aircraft as well as in extensive electronics systems such as large commercial internet server installations. The commercial applications – particularly for aircraft – will benefit from our emphasis on low cost, small size, low power, and autonomous operation. Our goal is to keep sensor component costs below $200 in quantity, so that a fully deployed sensor network remains reasonably priced. We are already close to that price point.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
Airport Infrastructure and Safety
Photonics
Combustion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Air-Lock, Inc.
Wampus Lane
Milford, CT 06460-4845

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ralph Toscano
toscanor@airlockinc.com
108 Gulf Street
Milford,  CT 06460-4845

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Air-Lock, Incorporated proposes to design an Enhanced Shoulder Mobility Joint Assembly (ESMJA) that increases dynamic mobility and static sizing capabilities for spacesuited crewmembers (CM) employing a Hard Upper Torso (HUT). The proposed shoulder joint will allow historically fixed Hard Upper Torsos to be sized in-situ by crewmembers of varying anthropometries. The Shoulders will also increase CM range of motion in a pressurized spacesuit and incorporate must mitigating strategies geared towards lunar exploration. Throughout Phase One, Air-Lock will exhibit the following innovations: • Design pressure sealed ESMJA that optimizes mobility and sizing characteristics of Hard Upper Torso Advanced Planetary Spacesuits. • Utilize 3D CAD software to design, develop and integrate the ESMJA with the MK-III HUT. • Perform a materials evaluation in order to determine the lightest, most robust material to be use in the manufacture of the ESMJA. • Create a matrix highlighting sizing potential and added mobility (i.e., range of motion). • Perform a comparative analysis of the sizing and mobility matrix to historic NASA anthropometry data to determine the optimum HUT sizes required to outfit current NASA astronaut corp.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Due to the highly specialized nature of the proposed design effort, extending the application of the Enhanced Shoulder Mobility Joint Assembly outside of pressure suits is unlikely. More feasible applications can be realized through the improved manufacturing techniques developed during Phase II. Reducing mass of historically metallic structures via composite, structural plastics or urethanes have been achieved in the past but proved to be very costly. Air-Lock plans to develop manufacturing techniques that would allow the molding of complicated geometries to "near net shape" to realize cost reduction of lightweight, robust structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The recent increase in commercial space business ventures (Virgin Galactic, Commercial Orbital Transportation Services, (i.e., COTS), Bigelow Aerospace, etc.) would present excellent opportunities to implement the ESMJA with any suit design that requires enhanced mobility and/or suit sizing. Additionally, and of equal importance are the manufacturing techniques to be developed throughout the proposed effort that can be utilized for any pressure suit hard mobility joints.

TECHNOLOGY TAXONOMY MAPPING
Suits

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Roger van Boeyen
roger.vanboeyen@lynntech.com
7610 Eastmark Drive
College Station,  TX 77840-4023

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With the increasing demands placed on extravehicular activity (EVA) for the International Space Station assembly and maintenance, along with planned lunar and Martian missions, the need for increased human productivity and capability becomes ever more critical. This is most readily achieved by reduction in space suit weight and volume, and increased hardware reliability, durability, and operating lifetime. Considerable progress has been made with each successive generation of space suit design; from the Apollo A7L suit, to the current Shuttle Extravehicular Mobile Unit (EMU) suit, and the developmental I-Suit and Mark III suits. However, one area of space suit design which has continued to lag is the fluid pump used to drive the water cooling loop of the Primary Life Support System (PLSS). Conventional electric motor-driven fluid pumps are heavy, bulky, inefficient, and prone to wear. A new pump type is needed. Lynntech proposes to further reduce the size, weight and power consumption of its long-life, low-power, compact, lightweight, efficient electrochemically-driven pumps, which will allow their use in the next generation space suit.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A rugged, long life, compact, light weight, efficient pump will have applications in the next generation of advanced Primary Life Support Systems (PLSS) for NASA's space suits. By replacing the existing electric motor-driven pump in the water cooling loop of the PLSS with Lynntech's electrochemically-driven pump, the size, weight and reliability of the PLSS will be significantly improved.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
With the increasing power density of electronics, there is a growing market for miniature, low-power pumps for use in the thermal management of consumer electronics. Some of the many other commercial applications that require reliable, efficient fluid pumps include environment water treatment, filtration, sterilizers, washing machines, fuel cells, and hydrogen generators.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Portable Life Support

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Grant Anderson
ganderson@paragonsdc.com
3481 E. Michigan Street
Tucson,  AZ 85714-2221

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The concept development and test of a water-based, advanced Phase Change Material (PCM) heat sink is proposed. Utilizing a novel material choice for both an expansion diaphragm and the PCM case itself, the PCM can accommodate both the expansion of the freezing water-based material and very low temperature of approximately -250F. The water-based PCM itself would be non-toxic and non-flammable, but additives will be included to preclude deterioration of wither the PCM container or the diaphragm material. The use of a water-based PCM gives the highest heat capacity for the mass. This is highly limited due to the needs for portability as required for an Extra-Vehicular Activity (EVA). The total heat capacity of an operational unit would be for full duration EVA use. Through a logical progression of tasks including concept of operation formulation, requirements formulation, concept design reviews and detail design reviews that include design and thermal analysis using Thermal Desktop<SUP>TM</SUP> models, this effort can progress from TRL 2 to TRL 3. The team will confirm the robust choice of diaphragm materials, the choice of casing material and the choice of the additives to the water used for the PCM. The PCM will be tested to confirm heat input/temperature performance and cycling capability. The test bed will allow for accurate heat input knowledge, temperature monitoring and cycling capability. The results will be compared to the thermal model to ensure accurate prediction capability for the next phase full-scale unit. The design description and test results would form the basis of the final report.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The purpose of this SBIR is to address the need as identified within the NASA SBIR solicitation under X4.02 "Space Suite Life Support Systems" and, to wit, "..a non-toxic, non-flammable, super cooled below 32<SUP>o</SUP>F phase change material that can absorb metabolic heat for an 8 hour duration. Hence, the primary application will be for the purpose of providing this heat rejecton capability in a compact, reliable form for the utlizaton within a PLSS. However, the application of this technology may go well beyond this to: 1) PCM utilization within the emerging Orion vehicle design. 2) PCM utilization within the future Lunar Surface Access Module design 3) PCM ulitization within any lunar surface habitat Each of these potential NASA applications could be augmented, and perhaps greatly enhanced via the use of the high heat capacity and heat of fusion of water. In the case of the lunar vehicles or habitats, the access to a thermal environment that is very low (Shakelton crater region on the moon) will allow for quick regeneration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are multiple industries within the commercial sector that could use a cooling system that is portable and robust. In Paragon's experience, our Navy work has exposed us to the critical needs of Navy Seals for underwater cooling during vigorous littoral operations. Other commercial sectors that may be interested in this technology would be the mining industry, the firefighting equipment industry, the commercial warm-water diving industry, and the chemical/biological hazard suit industry. Each of these have a similar theme of an enclosed person generating substantial metabolic load as well as experiencing environments where the rejection of heat through passive convection and radiation is not possible.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Reuseable
Air Revitalization and Conditioning
Portable Life Support

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christine Iacomini
ciacomini@paragonsdc.com
3481 E. Michigan Street
Tucson,  AZ 85714-2221

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metabolic heat regenerated Temperature Swing Adsorption (MTSA) technology is proposed for a Portable Life Support System to remove and reject heat and carbon dioxide (CO2) regardless of the environment (lunar or Mars, vacuum or CO2), as well as to help control humidity in the ventilation loop. The basic principal is removal of metabolically-produced CO2 by an adsorbent with regeneration using a temperature swing. The lower temperature is achieved via expansion of liquid CO2 (LCO2). The higher temperature is achieved with metabolic heat from the moist ventilation loop gas through a condensing ice heat exchanger. The condensed water is saved and recycled at the habitat. Both the LCO2 exhaust and the metabolically-produced CO2 are rejected to the surrounding environment. The effective temperature swing is between the CO2 sublimation temperature (~195 K) and the ventilation loop gas temperature (~300 K). MTSA has reasonable mass, volume and power with minimal impact on infrastructure and operations. The basic principles of MTSA technology are well-proven, safe, do not rely on cryogenics, do not consume water but conserve it, are regenerable and will not compromise scientific investigations by sublimating water for heat rejection onto the premises. An added benefit of MTSA technology is that the LCO2 coolant can be produced and stored on the surface of Mars, saving launch costs and providing easy emergency access and replenishment. As Paragon has demonstrated adsorbent and LCO2 cooling performance relevant to MTSA operating conditions, Phase 1 will emphasize understanding the condensing ice heat exchanger design through analytical formulations and validation through testing. Paragon's unique experience will ensure that this Phase 1 effort will be successful, resulting in a strong Phase 2 MTSA development plan to design, build and test in a relevant environment a full-scale MTSA subsystem prototype.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
MTSA technology specifically addresses the challenges faced by a Martian PLSS. These include rejecting metabolically-produced CO2 to a CO2 environment and thermal control without wasting resources and contaminating the Martian surface. MTSA has the potential added benefit in that it recycles water easily with no added mass or infrastructure back at the habitat. Further, the coolant can be made from Martian resources, reducing the reliance on Earth launches. The coolant can also be stored on the Martian surface without boil-off, readily accessible during an EVA to enable extended operations or provide extra cooling in emergencies. Another potential NASA application includes using MTSA on the moon. Liquid oxygen (LOX) could be used as the coolant rather than LCO2. Warmed LOX exhaust would provide the user with breathing gas rather than be expelled. If LOX is available, this would be a means for using the moon to test Martian technologies. Regardless of LOX availability, the LCO2 cooling capacity on the moon could be desirable, particularly in the event of an emergency where an astronaut will require significant heat rejection.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include a wide variety of portable life support systems for the Department of Defense and Home Land defense in chemical warfare agent shelters. We also anticipate interest from the fire fighter community as LCO2 is a powerful means for safe thermal control that exhausts non-flammable, spent coolant. Developments made during this research will contribute to making personal LCO2 thermal control systems more affordable and reliable.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Air Revitalization and Conditioning
Portable Life Support

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ZIN Technologies, Inc.
6745 Engle Road
Middleburg Hts, OH 44130-7994

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Hall
David.Hall@zin-tech.com
6745 Engle Road
Middleburg Hts,  OH 44130-7994

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZIN Technologies, Inc will breadboard an integrated electronic system for space suit application to acquire images, biomedical sensor signals and suit health & status data. The system will then process, display, store, transmit and manage the results under control of embedded firmware. A commercial off-the-shelf heads-up display which is applicable to space suit helmets will be the primary display device. The system will include a breadboard version of a lightweight, low power, general purpose computing platform based on commercial-grade components with available, upgraded versions that can tolerate the EVA thermal/vacuum/radiation environment. Initial development of a camera interface will be included. A breadboard of the proposed system will be built, programmed and demonstrated. ZIN will leverage our past experience in NASA spaceflight hardware/software development and existing biomedical monitoring technology to deliver a mature concept demonstration at minimal cost and risk. The system will be compatible with medical industry standard sensors to measure CO2, core temperature and other biomedical parameters. The proposed Phase 1 effort will be geared toward future development of a Phase 2 version that could be integrated into a functional EVA system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system is an innovative, reliable candidate for the CAI (Communications, Avionics and Informatics) element of the Constellation Space Suit System (CSSS) for use in Lunar Sortie and Outpost missions (Block II) as described in CxP 72002 (Constellation EVA System Requirements Document). The proposed Space Suit Sensing, Display and Data Management System will be based on the existing vMetrics biomedical monitoring device which was developed by the ZIN Medical division. The vMetrics-based system will meet NASA requirement EVA1084 for monitoring heart rhythm data as well as other medical parameters for the non-tethered (Block II) EVA Space Suit.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed system could be applied to a wide range of civilian and military applications. It meets the needs of workers in numerous occupations who have task- or mission-critical data requirements and who currently have to access that data using their hands or by moving their eyes away from their primary task. The embedded firmware could be easily reprogrammed to allow the device to serve the needs of aviators, heavy equipment operators, maintenance and healthcare workers, emergency response personnel and others who need a hands-free data acquisition and display device. The same ruggedization needed for the space environment would also serve well in undersea and harsh-environment industrial applications such as steel mills, refineries and nuclear power plants.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Data Input/Output Devices
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Suits
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luminit, LLC
20600 Gramercy Place, Suite 203
Torrance, CA 90501-1821

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dmitry Voloschenko
kyu@luminitco.com
20600 Gramercy Place, suite 203
Torrance,  CA 90501-1821

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To address the NASA need for lightweight, space suit-mounted displays, Luminit proposes a novel Holographic Waveguided See-Through Display. Our proposed Holographic Waveguided See-Through Display (HoWSD) will integrate highly selective waveguiding Bragg holograms, Luminit diffuser technology, a unique LCD backlight into a helmet-mounted display (HMD) that will provide easy- to-access clearly visible information to astronauts during extravehicular activity (EVA). The proposed HoWSD incorporates a unique design and Luminit novel diffusers into a functional HMD, which enables us to meet NASA goals for a functional, unobtrusive display device that provides information to astronauts during EVA. HoWSD offers a compact, low-profile display with high brightness and contrast, which is fully see-through and high resolution. In Phase I Luminit will demonstrate the feasibility of a see-through helmet-mounted display that can operate under various illumination levels, and which will prepare us for Phase II. In Phase II, Luminit plans to develop a fully-functional rugged prototype and demonstrate HoWSD functionality. The demonstrated results will offer NASA the capability of incorporating a non-obtrusive, rugged, wide field-of-view display into a space suit helmet designed for EVAs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
If successful in Phase I and in Phase II, the HoWSD system, integrated into a space suit helmet, will enable astronauts to see important mission information, such as updates from the Primary Life Support System (PLSS), warnings and checklists, during EVA.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The HoWSD system will find applications in avionics, combat vehicle crew, soldier's integrated protective ensemble, logistics and training, fire fighting, and in other areas where rugged helmet-mounted displays are needed. HMD technology advances made possible by successful development of the proposed HoWSD visor optics system will lead to cost-effective commercialization. In particular, the new HMD system will find numerous real-time 3D virtual reality applications. Medicine, avionics, education, CAD, portable computing and communication, law-enforcement, fire fighting, space exploration, and video games represent major markets for compact, low-cost lightweight HMDs in the private sector.

TECHNOLOGY TAXONOMY MAPPING
Data Input/Output Devices
Human-Computer Interfaces
Suits
Tools

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Vista Photonics, Inc.
67 Condesa Road
Santa Fe, NM 87508-8136

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Pilgrim
jpilgrim@vistaphotonics.com
67 Condesa Road
Santa Fe,  NM 87508-8136

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Breath respiratory species measurement during extravehicular activity (EVA) or intravehicular activity (IVA) is a demanding application for optical sensing techniques. Yet optical techniques offer many advantages including high-precision, fast response, and strong species selectivity. Accommodation within spacesuits demands that optical sensors meet stringent size, weight and power requirements. Vista Photonics proposes to develop rugged, compact, low-power optical sensor technology capable of selectively determining carbon dioxide at EVA-relevant concentrations. The enabling technology for meeting stringent NASA mission requirements is a new low power infrared optical source that provides the high-sensitivity of established optical absorption detection techniques.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate targeted application for NASA is respiratory species monitoring during EVA and IVA. Phase II prototypes will be capable of selectively detecting carbon dioxide and water vapor. Other species can be included as required. The integrated sensors will be suitable for variable pressure EVA operation in diverse environments like the Moon, Mars and ISS. Unmanned planetary exploration missions in substantial atmospheres like Titan's are likewise contemplated. The emerging technology will also be suitable for use on both manned and unmanned terrestrial atmospheric research craft. Other applications include fire detection on aircraft and high-value installations, gas sensing in air revitalization and water recovery processes on spacecraft, and leak detection during spacecraft launch operations.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase III commercial applications abound for sensors whose performance and physical characteristics are suitable for spaceflight. Examples include contaminant monitoring in process gas streams in the chemical and microelectronics industries, medical diagnosis through detection of biogenic gases in human breath that correlate to specific pathologies, and environmental monitoring and regulatory compliance in agriculture, power production, and occupational safety. The fully-developed Phase II instruments shall offer a compelling and desirable blend of performance, affordability, compactness, simplicity and ease-of-use relative to present commercial product offerings in these applications.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biomolecular Sensors
Optical
Portable Life Support
Photonics

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Hartenstine
john.hartenstine@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5688

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovative Research project by Advanced Cooling Technologies, Inc. (ACT) will develop an advanced high temperature heat pipe solar receiver that can be used for the production of oxygen from lunar regolith. ACT proposes a high temperature heat pipe solar receiver that can accept and and transfer the solar thermal energy to the lunar soil, thereby extracting oxygen. The heat pipe design will also be able to isothermalize the reactors, increasing the available area for soil evaporation, and consequently increasing the throughput and efficiency. The overall objective of the Phase I and II programs is to develop a heat pipe solar receiver for the production of oxygen from regolith. In Phase I, the principal objectives are to design the receiver, and fabricate and test a representative heat pipe under simulated conditions. The Phase II program will fabricate and test the full scale heat pipe solar receiver.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary application is the development of a heat pipe solar receiver for oxygen production. A lunar oxygen production plant is projected to provide breathable oxygen for astronauts a well as oxygen for rocket propulsion. The heat pipe solar receiver could also be used for materials processing. There is a vast amount of resources on the moon that could be processed into materials such as concrete, cast and sintered basalt, fiberglass and metals such as aluminum. Anorthite, available on the moon, could be processed using the furnace to produce aluminum, calcium and silica materials.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Remote materials processing is a second application for both NASA and commercial industries. The heat pipe solar receiver could be used for remote materials processing where there is insufficient electricity or funding to operate expensive furnaces.

TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Berggren
mberggren@pioneerastro.com
Pioneer Astronautics 11111 W. 8th Ave; Unit A
Lakewood,  CO 80215-5516

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Lunar Sulfur Capture System (LSCS) is an innovative method to recover sulfur compounds from lunar soil using sorbents derived primarily from in-situ resources. Most of the sulfur released from lunar soil during higher-temperature thermal treatment is trapped by the LSCS at lower temperatures on iron oxides present in lunar soil. As needed, small amounts of polishing sorbents are used to reduce equilibrium sulfur concentrations to the low ppm level. After sorbents become saturated, sulfur compounds are desorbed and converted to useful sulfur products. Sulfur is present in concentrations of about 0.1 percent in lunar soils and can be recovered by the LSCS as a useful product from in-situ resource utilization (ISRU). The LSCS can capture and recover sulfur from lunar soil as a primary product during thermal desorption of volatile compounds or during thermal reduction ISRU processes used for oxygen production. Removal of sulfur compounds is required during ISRU to prevent electrolyzer damage, catalyst poisoning, and equipment corrosion. The LSCS is applicable to thermal ISRU reduction processes in which sulfur is released in forms such as hydrogen sulfide (H2S), carbonyl sulfide (COS), or carbon disulfide (CS2).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary initial application of the LSCS is for lunar sulfur capture and recovery. The LSCS has direct use to both protect ISRU hardware and catalysts while producing useful amounts of sulfur for other lunar ISRU applications. Implementation of the LSCS will proceed through the SBIR Phase 1, 2, and 3 programs, with increasing levels of development achieved through each step. During each phase, Pioneer will identify the LSCS requirements and will establish the commercial relationships needed to provide materials, fabrication, and implementation strategies for NASA lunar application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
One non-NASA commercial application of LSCS is the large-market target of integrated gasification combined cycle power generation from coal. Other smaller-market opportunities are at least as likely to benefit from the LSCS applied to reduce emissions and waste disposal requirements from a variety of industrial applications. These opportunities are likely to grow as de-centralized fuel preparation technologies are advanced for conversion of biomass and other potentially contaminated feeds to alcohol and other fuels. Pioneer will be actively monitoring these activities and the potential applications and the use of the LSCS technologies. As appropriate, Pioneer will make contact with those involved in these markets to establish the business feasibility of the LSCS to terrestrial applications.

TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The multi-cell thermal battery (MCTB) is a device that can recover a large fraction of the thermal energy from heated regolith and subsequently apply this energy to heat up cool regolith. The individual cells of the MCTB contain a thermal storage media that is specifically designed for optimal performance at a given temperature range. Each of these cells is charged with thermal energy from hot regolith that has been used in a lunar ISRU application. Once the MCTB is charged, the heat is transferred from the battery to newly harvested regolith. In this manner over 85% of the heat can be transferred from the expended to the new regolith. This is a large improvement especially considering that this reduces the heating requirement to produce 1000 kg of O2 from lunar regolith from an average of 1 kW to only 0.15 kW (assuming 3% O2 recovery by weight). The other irreducible power consumption of lunar ISRU O2 production is electrolysis which consumes at least 0.3 kW. Hence, using the MCTB decreases the irreducible power consumption of lunar ISRU by 65 %.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary initial application of the multi-cell thermal battery is for heat recovery from expended lunar regolith to new regolith during O¬2 production via hydrogen reduction. The MCTB reduces the heating requirement for lunar O2 production by 85% and reduces the overall power requirement by 65% given an O2 production rate of 1000 kg/year and 3% O2 recovery by weight. During the phase I the superior performance of the MCTB will be demonstrated by transferring over 60% of the heat from hot regolith at 800 oC to cold regolith initially at 25 oC. During the subsequent Phase II and Phase III programs, the MCTB will be further optimized and refined to integrate seamlessly with state-of-the-art lunar regolith reduction systems. The MCTB will be light-weight and provide significant energy savings for lunar ISRU applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The multi-cell thermal battery will be a valuable tool wherever heat needs to be stored or transferred from one solid substance to the next. Any chemical process that requires high temperatures and operates in batch mode would greatly benefit from using the MCTB to conserve energy. Batch furnaces for hardening and annealing metals, for example, require high temperatures and operate in batch mode. Using the MCTB in this application could greatly reduce the operational cost of such facilities. In such a process the expended product can be used to fill the thermal battery with heat and this heat can then be used to pre-heat the following batch. As shown before, this can lead an energy savings of over 85%.

TECHNOLOGY TAXONOMY MAPPING
In-situ Resource Utilization
Energy Storage
Power Management and Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Grainflow Dynamics, Inc.
1141 Catalina Drive, PMB #270
Livermore, CA 94550-5928

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Otis Walton
walton@grainflow.com
1141 Catalina Dr., PMB #270
Livermore,  CA 94550-5928

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has serious unmet needs for simulation tools capable of predicting the behavior of lunar regolith in proposed excavation, transport and handling systems. Current simulation tools do not include the effects of triboelectric and photo-ionization induced charges on regolith particles. Existing DEM or FE models largely focus on coarse smooth non-brittle particles and lack adequate fidelity for fine cohesive powders comprised of friable particles with irregular shapes. As such, they are inadequate for assessing the reliability of regolith excavation and handling systems, and even less so for evaluation of engineering trade offs between total system mass, power and energy consumption. Grainflow Dynamics proposes to develop a high-fidelity DEM model incorporating a new charge-spot model for electrostatic forces arising from localized charge patches on the surfaces and in the interiors of individual particles, and also including an innovative new comprehensive cohesive-contact model. Grainflow Dynamics further proposes to demonstrate the ability of the new cohesive-contact model to mimic the compaction and dispersion behavior of lunar regolith simulants JSC-1A and JSC-1AF. This work will lead to an improved engineering design tool that can be used by NASA engineers and contractors developing designs for ISRU equipment, to evaluate reliability of various configurations, and the trade-offs of system designs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
New high-fidelity simulation tools for charged cohesive powders would be applicable to a wide range of ISRU situations including excavation, transport, handling, platform mobility, slope stability and wheeled vehicle traction analysis. New designs in all of these areas would benefit from improved fidelity of simulation models. The ability to include the effects of charged particles and reduced gravity, and to test sensitivity of equipment designs to regolith model parameters and equipment designs can greatly assist in prioritizing regolith characterization measurements and optimizing equipment designs, once the properties of the regolith have been more accurately characterized. In addition the new charged-particle capability will greatly facilitate evaluation of various dust mitigation strategies, a critical need for manned exploration missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The pharmaceutical industry, has a large number of applications which would benefit from significantly-improved simulation capabilities for cohesive powders in a variety of pharmaceutical material manufacturing, transport and handling operations, including micronization, granulation, coating, blending, tableting, dosating and capsule or blister-pack filling – especially powders designed for pulmonary delivery. The FDA's Process Analytical Technology (PAT) initiative emphasizes the need for pharmaceutical makers to understand the processes they use and to design the processes for quality, reliability, robustness and consistency. Reliable tools to predict powder deformation and flow behavior would greatly facilitate the attainment of such goals. In addition, the xerographic industry (e.g., laser printers and copiers ) could benefit from a predictive tool that could assist in design improvements for powdered toner tribocharging, transfer, and fusing. Despite 50 years of R&D, many details of the overall xerographic process are only poorly understood, and fierce competition provides motivation to seek design improvements.

TECHNOLOGY TAXONOMY MAPPING
Manned-Manuvering Units
In-situ Resource Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Adherent Technologies, Inc.
9621 Camino del Sol NE
Albuquerque, NM 87111-1522

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jan-Michael Gosau
adherent@earthlink.net
9621 Camino del Sol NE
Albuquerque,  NM 87111-1522

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Establishing human presence outside the protective cover of earth's atmosphere is a challenge. On earth, the atmosphere does not only present breathing gas, it also acts as a thermal buffer and protects the biosphere from harmful radiation. Shielding of humans from harmful radiation during long-term stays on an extraterrestrial body like the moon is a difficult task. Lunar regolith provides an excellent source of readily available insulation and shielding material. About 2 m of packed regolith would provide an excellent cover for a permanent installation.. In order to either bury shelters or to surround habitats with berms of protective material, it is necessary to excavate regolith on a large scale, a difficult undertaking due to the dustlike consistency of the material. To stabilize the regolith, it is necessary to either consolidate the surface material of the slopes or to convert the regolith into a solid building material. Adherent Technologies, Inc. has developed several specialty resins for material stabilization. This includes penetrating urethane foam for asbestos remediation and epoxy resins for borehole casings in dry-drilling applications. ATI now proposes to develop a stabilization system for lunar surface dusts using a polyurethane foam binder.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Being able to shape the environment during the establishment of a permanent outpost on the moon is a mission-critical task. As such, the proposed technology enables the long term occupation of lunar surface bases without the use of cost-prohibitive terrestrial resource use. The concept is based on established technology and offers a solid, low risk approach to the use of extraterrestrial resources.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology for the fabrication of habitat structures from locally available materials using a polymer binder can be extended to terrestrial use in environments where normal building means are not readily available and the delivery of standard components like cement, and of course water, is cost prohibitive. This includes desert environments, mountainous regions, or the Antarctic. Since the environment on earth is usually much less severe than the environment described in the project, the binder material could be optimized for performance instead of application. This includes strength, for example as a protective material in military applications where sandbags are used today or heat retention in mountainous or arctic regions.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Thermal Insulating Materials
In-situ Resource Utilization
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Starsys, Inc.
1722 Boxelder Street
Louisville, CO 80027-3008

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Scott Christiansen
scottc@starsys.com
1722 Boxelder Street
Louisville,  CO 80027-3008

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Clearly, the presence of lunar dust has the propensity for major adverse impacts on dynamic mechanical systems required for future lunar operations such as Rovers, Robotic Systems, In-Situ Resource Utilization (ISRU) and science experiments. As such, the development of innovative techniques for mitigating dust affects is warranted. In abrasive environments such as the presence of regolith dust on the moon, mechanism seals must be either designed for robustness to avoid premature damage and leakage, or, the dust particles must be removed. For this SBIR, Starsys proposes an enabling all-metal, knife-edge seal capable of maintaining seal integrity even in the presence of the abrasive, lunar dust. The proposed Knife Edge Seal concept provides for an innovative mechanism by which to seal critical ISRU mechanisms even in the presence of lunar dust contamination. Starsys' knife edge seal approach will utilize a hard metal knife edge and seal gland filled with an Indium alloy. The knife edge geometry is sized to allow for low forces required to penetrate the Indium, while the gland geometry is sized to properly and reliably capture the Indium. The Indium is a phase change material available in a variety of alloys to target specific melting points. The Knife Edge Seal offers two distinct advantages when attempting to mitigate the affects of lunar dust; 1) the knife edge will penetrate any dust layer developed on the seal gland surface and embed itself into the gland material, and 2) the Indium can be heated and re-flowed in between mate and de-mate cycles, allowing the dust particles to mix in with the soft Indium material and most likely eliminating sufficient barrier between the knife edge and Indium to allow for sufficient sealing to occur.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA commercial applications include manned and unmanned lunar operations, operations on MARS, and other exploratory missions involving operations in abrasive environments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA commercial applications include commercial space flight tourism, commercial space satellites and instrument/sensor cover systems, and terrestrial applications requiring operation of sealed mechanical systems in abrasive environments.

TECHNOLOGY TAXONOMY MAPPING
Airlocks/Environmental Interfaces
Fluid Storage and Handling
Portable Life Support
Suits
In-situ Resource Utilization

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Owen Evans
oevans@aerogel.com
30 Forbes Road, Building B
Northborough,  MA 01532-2501

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In 2005, President George W. Bush issued a Vision for Space Exploration that included a return to the lunar surface by as early as 2015. This mission is expected to undertake far more ambitious activities than those of the previous Apollo mission, possibly involving medium to long term lunar habitation. The use of inflatable structures for large-volume crew habitation on the lunar surface has proven to be an effective technology to maximize payload volumes and reduce overall launch costs. NASA is currently seeking cutting edge material technologies that can simplify the construction of these habitats and provide for enhanced performance. Aspen Aerogels proposes to develop novel hybrid aerogel materials that are able to simultaneously provide for thermal, micrometeoroid and radiation protection in one single layer. Chemical modifications in the sol-gel preparation of aerogel materials are expected to afford hybrids materials that will combine the durability and thermal performance of a standard silica aerogel with the flexibility, resilience and radiation protection properties of a polymeric material.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The nanostructured, lightweight, flexible aerogel composites will improve thermal, radiation and MMOD impact shielding for inflatable habitat structures. Multi-layer insulation (MLI) layers in habitats would be replaced with the developed technology. EVA suits including gloves and footwear, and helmets could also potentially utilize the new insulation materials. The flexible aerogels are air, water, and vacuum capable and thus could be incorporated into new single suit designs for a broad spectrum of astronaut mission. The excellent durability and toughness of the flexible aerogel might facilitate use in cryogenic insulation in difficult vibration and acoustic environments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other potential applications include use as insulation in commercial and military aircraft, cryogenic tanks, liquefied gas transport, gloves, footwear, systems for warming, storing, and/or transporting food and medicine, sleeping bags and pads, military and recreational tents, etc.

TECHNOLOGY TAXONOMY MAPPING
Inflatable
Thermal Insulating Materials
Radiation Shielding Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Adherent Technologies, Inc.
9621 Camino del Sol NE
Albuquerque, NM 87111-1522

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrea Hoyt Haight
adherent@earthlink.net
9621 Camino del Sol NE
Albuquerque,  NM 87111-1522

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Any manned missions to extraterrestrial locations will require shelter structures for a variety of purposes ranging from habitat usage to biomass production. Such shelters need to be constructed in such a way to minimize stowed volume and payload weight. The structures must also be very durable and have the ability to survive punctures without collapsing. Ways of increasing available crew-load volume without greatly increasing launch weight or volume are also sought. Inflatable structures are ideal candidates for habitat structures for several reasons: (1) they feature the low stowage volume and payload weight required, (2) deployed volume can be easily increased without large increases in launch weight or volume, (3) they offer unique opportunities for incorporating intelligent and/or multifunctional systems such as self-healing capability, power generation and storage, sensor systems, and radiation protection. Adherent Technologies, Inc. is proposing an inflatable, rigidizable shelter system based on our Rigidization on Command<SUP>TM</SUP> (ROC) technology. The proposed shelter system would feature not only the required low stowage volume and lightweight character, but would also feature a self-healing foam system incorporated into the final structure to minimize the damage caused by any potential punctures to the structure. Additional features will be incorporated in the Phase II follow-on, including thin film photovoltaics to provide power for the lighting system and later habitat function, sensor systems for monitoring both structural and crew health, and radiation protection systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This system is being designed to support the need for structures on future manned space missions to the moon and Mars. Applications are seen as shelters for equipment with the potential for expansion into habitats and airlock structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The rigidizable shelter that is the focus of this Phase I program is very similar in concept to air beam structures currently being pursued by the military. Inflatable air beam technology is enabling rapid deployment of various shelters for military applications. Our rigidizable, self-healing system should find easy application in military applications, where light weight, low storage volume, and limited manpower required to construct shelters are of interest.

TECHNOLOGY TAXONOMY MAPPING
Inflatable
Kinematic-Deployable
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Dynamic Structures and Materials, LLC
205 Williamson Square
Franklin, TN 37064-1321

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffrey Paine
jpaine@dynamic-structures.com
205 Williamson Square
Franklin,  TN 37064-1321

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Piezoelectric motors operate on the principal of high frequency oscillation of high force precision ceramic elements. The high power oscillations are converted to rotary motion through a novel conversion mechanism to produce high torque precision motion when compared with traditional electromagnetic motors. Dynamic Structures and Materials (DSM) proposes to focus the Phase I innovation on the development and design of a precision rotary conversion mechanism that will take the piezoelectric oscillatory power and produce rotary motion for operation at cryogenic and extreme environments. DSM has already demonstrated operation of its high force linear motor actuators for environments as low as 77 K. The proposed rotary motor should operate from approximately 25K to 400 K and should provide very low or no outgassing as well as operational capabilities in hard vacuum. The technology is proposed for applications in the area of rover control, driving operational equipment, instruments, and other such facilities. This proposal addresses DSM's perceived approach to the development of flight-scalable demonstration components for the novel rotary motor technology.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
An actuator system featuring the proposed capabilities (> 5 Nm torque, 1 to 200 RPM, lightweight, submicron dynamic range, nanometer stability) will help facilitate the success of lunar and Mars missions. Derivatives of this actuator technology could be deployed with many space-based rovers and instruments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed type of rotary motor technology could be readily leveraged to satisfy the requirements of precision terrestrial applications. Piezoelectric rotary motors are used where precision motion and high torque are required in a compact space. Since piezoelectric motors do not require a gear box to provide substantial torque levels, they can be much more compact and precise than electromagnetic motors with gearboxes. In addition, many precision assembly and fabrication processes related to optoelectronics and semiconductor fabrication and metrology could benefit from the general actuation technology proposed herein.

TECHNOLOGY TAXONOMY MAPPING
Kinematic-Deployable
Large Antennas and Telescopes
Instrumentation

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has identified the need for the development of lightweight structures technologies to support Lunar Lander and Lunar Habitats programs and for the transfer of relevant technology to Crew Exploration Vehicle and Crew Launch Vehicle programs. NASA further calls for revolutionary advances in radiation shielding materials and structures technologies to protect humans from the hazards of space radiation during NASA missions. To address this need and in response to NASA Subtopic X6.03, International Scientific Technologies, Inc. in conjunction with the College of William and Mary, proposes the development of hydrogen-rich monomers for high performance polymers, such as polyimides, and the incorporation of metallic nanoparticles to form nanocomposite materials having multifunctional properties. The Phase I Technical Objectives include preparation of hydrogen-rich monomers, fabrication of polymeric nanocomposite films, and acquisition of test data to determine key parameters for optimal radiation-shielding materials. The anticipated result of the Phase I and Phase II programs is the development of polymeric nanocomposite materials consisting of hydrogen-rich monomers and metallic nanoparticles. The nanocomposite materials have multifunctional properties of radiation shielding against galactic cosmic radiation, neutrons and electromagnetic radiation, structural integrity to permit use in flexible and rigid structures and habitats, and electrical conductivity for electrostatic control to be used in dust mitigation during lunar missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed multifunctional nanocomposites will find application in the Exploration Systems mission in protecting astronauts and sensitive optical, electronic, thermal and acoustic components from environmental hazards including radiation, dust and thermal transients, while, at the same time, providing lightweight structural functions. It is expected that nanocomposite systems will provide a high-performance-to-weight radiation shield that can be used within human habitats, spacecraft and protective apparel. Other missions supported by NASA could also make use of the nanocomposite materials in low earth orbit or in other orbital paths traversing high radiation regions of space.

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

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

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Steinbeck
steinbeck@psicorp.com
20 New England Business Center
Andover,  MA 01810-1077

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Physical Sciences Inc. (PSI) has developed fiber reinforced ceramic composites for radiation shielding that can be used for external walls in long duration manned space shelters. The wall system comprises a high strength, hollow core composite that can be filled with materials to perform other critical operations such as thermal management. The composite technology enables a modular wall shielding system that exhibits superior radiation resistance to galactic cosmic radiation (GCR), solar particle emission (SPE) and secondary radiation sources produced by the interaction of the primary source with the lunar regolith and shield materials. This Phase I SBIR will develop and demonstrate radiation shielding composite wall architecture that … 1) Can replace aluminum in lunar shelter structural applications. 2) Can act as a ballistic shield enclosing a multifunctional cavity. 3) Can serve as a multifunctional platform for additional shelter functions such as thermal management. We will design and fabricate as well as strength and radiation resistance test prototype multifunctional composite structures. We will demonstrate that the composite system components have superior mechanical properties to and at least 20% greater radiation shielding effectiveness than an aluminum structure of comparable areal density.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application for the proposed radiation shielding materials is the construction of long duration space habitats for manned missions to the moon and Mars. Habitat modules that can be lifted by the Ares V launch vehicle would provide near term living quarters and laboratories for initial lunar missions. Modular construction will enable a facility to be built using the same principles as those used to build the international space station. The large structure ceramic composite technology to be developed during the effort has additional applications beyond space habitats. Development of large ceramic composite components with application tailored matrices will enable the fabrication of gas turbine, scram jet and rocket engine components. Specific engine components include combustion liners, inlet ducts and nozzles. Tailoring the matrix for high temperature applications will enable engine housings for aircraft engines and power generation systems. Fabrication of large, uncooled, nonablating rocket nozzles will improve thrust to weight and/or engine specific impulse.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Developing large ceramic composite components both with and without boron carbide will also enable the fabrication of large ceramic composite structures for next generation nuclear plant (NGNP) applications including hot ducts, control rod guides and containers. Additional nuclear applications include long term storage and transport containers for radioactive waste. In addition, the development of high strength boron carbide based composites will lead to improved armor systems that can be seamlessly integrated into vehicle systems as structural members to minimize vehicle weight while adding significant ballistic protection. Specific component applications include pilot seats, armored limousines and up-armoring kits for existing vehicles.

TECHNOLOGY TAXONOMY MAPPING
Radiation Shielding Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
San Diego Composites, Inc.
9550 Ridgehaven Court, Suite A
San Diego, CA 92123-5607

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gary Wonacott
gwonacott@sdcomposites.com
9550 Ridgehaven Court, STE A
San Diego,  CA 92123-5607

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cost and size are limiting factors in efforts to produce high strength, high stiffness, and high temperature composite parts. To address these issues, new processes to lower cost for high temperature composite manufacturing need to be explored. An obstacle for high temperature processing of composites is the creation of by-products or volatiles during cure. An innovative technology, Double Bag Assisted Resin Transfer Molding (DBARTM), has been developed by Dr. Tan Hou at NASA Langley that deals with this obstacle. The technology has only been developed for phenolic resins which is a lower temperature curing resin than is required for many high temperature composite component applications. This process has been shown to reduce the amount of volatiles trapped in the laminates. The key is innovative volatile control during the DBARTM fabrication process. The process results in low-void to void-free quality laminates and fulfils a critically needed technology gap that will enable insertion of an important class of high performance materials into commercial, military and aerospace market places at an accelerated pace. The primary technical objective of the proposed work is to show the feasibility of the use of the NASA DBARTM technology for high temperature polyimides composite manufacturing. In Phase I, work will focus on material selection, process development, and fabrication and test of flat panels of both phenolic and polyimides. At the end of Phase I, the Technology Readiness Level (TRL) is expected to be 2-3. In Phase II, the DBARTM process will be used with a polyimide resin system to fabricate a full-scale prototype of the initial application.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are many different applications that may come from the development of low cost high temperature composite processing. Programs such as Mission to Mars could have benefited from such composite processing, and all future deep space explorations programs. Specific components include airframes, large antennas and telescopes, launch and flight vehicle structures, and components that require power management and thermal protection systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA commercial applications include commercial aircraft and Integrated Defense Systems such as advanced UAV's. Specific components that would benefit from this technology includes aircraft engines, control structures, fluid storage and handling containers, fan blades, engine ducts, supersonic engine cowlings, high speed missile bodies and nose tips, and rocket motor cases.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Large Antennas and Telescopes
Thermal Insulating Materials
Tankage
Fluid Storage and Handling
Composites
Power Management and Distribution
Aircraft Engines

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed project is aimed at developing a model based resource and mode management system for space robotics systems that will allow real time assessment of resources status and provide required situational awareness to execute efficiently the mission. Traditionally, resource management is being done remotely by the robotics operations team. This approach has numerous disadvantages. For instance, it does not support a more autonomous operation, it takes a longer time to complete than potentially available when the decision has to be made in real time, it has the high costs associated with a large operating team, continuously working for mission support. Ideally, such a function should be part of a full Integrated System Health Management (ISHM), but while a lot of research is being done on the development of ISHM systems, very little effort is made to provide the robot with the capability to use system information to assess the possible strategies with respect to the remaining resources of the vehicle. A model based system can use its understanding of the system state, of its operational modes and of its resource usage to deduce the potential optimum strategies in order to achieve the mission goals.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Applications of the resource and mode management toolset are numerous at NASA. In the short term, the tool can be used for existing space robotics system such as the Robonaut, Centaur and Surface Rover. In the longer term, our concept can apply to the different types of advanced robotics systems to be developed to support the Human/Robotic missions to the surface of the Moon and Mars . For instance the initial missions will need the development of telerobotic rovers and aerial vehicles for science, site reconnaissance, and potentially hazardous operations. Then, autonomous and tele-robotic rovers for planetary resource excavation, transport, and processing will follow, to prepare for EVA assistant rovers for site exploration. The tool should allow these programs to significantly reduce the need for costly manual assessment and planning of the system missions before the operations. In the future, the tool could be applicable to the lunar habitats supporting the new exploration vision.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A tool that can be customized to different systems will be useful within DoD organizations using complex autonomous systems such as UAV, UCAV, ULV transport equipment, or logistics support equipment. In the commercial arena, robots are becoming more ubiquitous and used in an ever growing range of disciplines. They are used for carrying hazardous tasks, routine security tasks, and performing a variety of surgical tasks such as hip replacement, cardiac surgery, or supporting laproscopic surgery. These Robotic surgical assistants have potential application in the nearly one million endoscopic surgical procedures performed each year in the U.S. alone. Our concept could provide significant improvements to these commercial robots. Resource and mode management is also being used in a broad range of different domains, such as airplane operations, power plant, refineries, and chemical plants operations. This type of technology can be adapted to these different domains and provide benefits similar to those provided to NASA.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Teleoperation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Rapid Imaging Software, Inc.
1318 Ridgecrest Place SE
Albuquerque, NM 87108-5136

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mike Abernathy
mikea@landform.com
1318 Ridgecrest Place S.E.
Albuquerque,  NM 87108-5136

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Situation Awareness Technologies (ASAT) will facilitate exploration of the moon surface, and other planetary bodies. This powerful technology will also find application in the commercial sector, particularly submersible vehicle operation. ASAT will fuse video and other sensor technologies, with geographic databases to maximize vehicle operator situation awareness, and enhance the navigation state of the guidance and control system. During previous research and development activities RIS invented a method to use video camera data to enhance vehicle attitude estimation from gyroscopic inertial navigation systems. In non-earth environments, the absence of a strong reference field increases the problem of INS drift, and decreases operator situation awareness as a consequence. RIS will develope technology which enhances navigation and situation awareness in these challenging environments.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Telepresence and teleoperation are vital components of NASA space exploration for the next decades. The return to the moon, and the desire to explore our solar system fuel the need for advanced technlogies like ASAT. ASAT will aid future lunar rover vehicles will facing challenges of navigation and safe operation in a challenging environment. There, the GPS that we now take for granted on earth will not be useful. Earths magnetic field, so useful in navigating our planet, will not be available so problems of INS drift become exagerated. Fortunately, the ASAT technology will be there to provide the situation awareness for vehicle operators so needed for safe exploration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ASAT will find application in the operation of remotely operated vehicles in the commercial sector. Areas of particular emphasis include submersible ROV operation for mineral explortation and extraction, Unmanned Aerial Systems, and Unmanned Ground Systems used in extractive industries in dangerous environments. Rapid Imaging Software, Inc. is uniquely positioned to commercialize this technology because of our extensive history in successful UAV teleoperation situation awareness technologies, and because of our relationship with large UAV manufacturers.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Perception/Sensing
Teleoperation
Attitude Determination and Control
Guidance, Navigation, and Control
Pilot Support Systems
Human-Computer Interfaces

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Rutberg
rutberg@honeybeerobotics.com
460 W 34th Street
New York,  NY 10001-2320

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future lunar initiatives will demand sophisticated operation of mobile robotics platforms. In particular, lunar site operations will benefit from robots, both autonomous and tele-operated, that complement or replace human extravehicular activity (EVA). Three-dimensional sensing technology is at the heart of such functionality, enabling safe and reliable navigation in complex, dynamic environments, and serving as a valuable tool for inspection and site survey. Honeybee Robotics therefore proposes to develop a small-envelope, high-performance scanning LIDAR (LIght Detection and Ranging) system, geared primarily towards mobile robot navigation, and secondarily to site inspection and survey. The proposed device would draw on the results of a design study conducted by Honeybee, under contract to DARPA, to develop a miniature LIDAR for a serpentine robotic platform. The baseline Honeybee 3D Miniature LIDAR (3DML) design uses an innovative scanning mechanism in conjunction with a pulse-time-of-flight optical rangefinding subsystem. The 3DML design, developed with expert input from Sensor Designs, Inc., an Oregon-based electro-optical systems consultancy, achieves a wide field of view and high resolution while maintaining an ultra-compact package size. Phase I of this SBIR effort will focus on proof-of-concept of the opto-mechanical system through prototyping and test. Phase II will include development of a fieldable brassboard system prototype and a full path-to-flight study. Phase III will include commercialization of a 3DML unit for terrestrial research, and incorporation of 3DML into a flight program. As an experienced developer of miniature electromechanical systems for spaceflight, Honeybee is well-positioned to flight-qualify 3DML in Phase III.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Honeybee 3DML is strongly targeted towards mobile robotic platform navigation. The combination of a wide field of view and a high angular resolution make 3DML uniquely suited for this application. The long-term goal is to produce flight units for NASA lunar missions, to facilitate robotic site operations support. In addition to rover navigation, a flight 3DML could be employed as a sensor for lunar vehicle and structure inspection. With some modifications, the system could potentially attain long-range survey capability as well, resulting in an all-in-one navigation/inspection/survey sensor. Rover missions for Mars exploration could also make use of a compact, robust 3D LIDAR system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Honeybee anticipates considerable terrestrial demand for a compact, short-range, high-resolution 3D LIDAR system. Applications include military robotics, automotive automation, construction, and mining. In addition, research units could be marketed to roboticists in defense, industry, and academia.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Perception/Sensing
Optical
Manned-Manuvering Units

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
New Span Opto-Technology, Inc.
16115 SW 117th Avenue, A-15
Miami, FL 33177-1615

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jame Yang
jyang@new-span.com
16115 SW 117th Ave. A-15
Miami,  FL 33177-1615

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Laser rangefinders have numerous NASA and non-NASA applications, including navigation, landing hazard avoidance, automated rendezvous and docking, air and missile defense, infantry and artillery target designating, tank and infantry fighting vehicle fire controlling, surveillance through foliage, cloud-height measurement, and production monitoring in industries as well as commercial and law enforcement, etc. Existing laser rangefinders cannot meet some of the advanced performance requirements including wide field of view (FOV) for situation awareness, high angular resolution for detailed target shape discrimination, and fast response for transit event or moving objects tracking, as well as low weight, volume and power requirements, etc. For NASA's lunar exploration missions, lunar roving vehicle with features of automated path planning, automated driving, and obstacle avoidance are of interest for making planetary surface missions more reliable, safer, and affordable. New Span Opto-Technology Inc. proposes herein a novel laser rangefinder architecture with non-mechanical scanning foveal aperture providing wide FOV 3-D scene profile for situation awareness and high resolution 3-D profile of region of interest for object tracking. System packaging is rugged, compact and light-weight. Phase I research will establish the model, demonstrate the feasibility, and recognize challenging issues of the proposed concept through model analysis and bench top experiments.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications of the proposed foveated 3-D imaging rangefinder include LRV or MER vehicles navigation, landing hazard avoidance, automated rendezvous and docking such as International Space Station re-supply or repair missions. It will also enhance the safety of other proximity operations in space by providing high-speed inputs for collision avoidance and close approach inspection maneuvers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The successful development of foveated 3-D imaging rangefinder will find extensive applications in military. The man-portable applications include hand-held devices for infantry and artillery observers and dual-mode rangefinder-designators for forward observers and forward air controllers. Land vehicle applications include tank and infantry fighting vehicle fire control and air defense gun-missile fire control, as well as vehicular variants of ground rangefinder-designators. Airborne applications include missile command guidance for attack helicopters and electro-optical targeting for fixed-wing close air support and interdiction aircraft. Laser rangefinders are also used on board naval vessels for conventional fire control and air defense applications. Space-based laser rangefinders for a variety of applications are also being developed. Applications in commercial filed include navigational guidance, surveillance through foliage, cloud-height measurement, and production monitoring in industries as well as commercial and law enforcement applications.

TECHNOLOGY TAXONOMY MAPPING
Telemetry, Tracking and Control
Guidance, Navigation, and Control
Autonomous Control and Monitoring
Laser
Optical

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Herman
herman@honeybeerobotics.com
460 W 34th Street
New York,  NY 10001-2320

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed effort will perform a detailed examination of dust mitigation and tolerance strategies for connections and mechanisms to be employed on the lunar surface. These strategies will be examined by characterizing the effects of lunar dust simulants on the function of basic mechanical and electrical components, and the effectiveness of tolerance or mitigation strategies in lessening those effects. The project will be led by Honeybee Robotics, with consultation and support from Dr. Masami Nakagawa of the Colorado School of Mines as well as consultation with Hamilton Sundstrand Space Systems International, Inc.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Dust mitigation strategies will be key components to future exploration missions and would find extensive applications in systems designed to operate in the lunar and other dusty environments. Future mission scenarios involving erectable structures, diverse EVA-compliant tools, EVA-to-rover or EVA-to-robot interfaces, and other in-situ assembly or interconnection activities, will all call for such measures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There is a need for dust insensitive electrical and mechanical connectors by several industries as well as the United States military. Dust mitigation strategies developed in this effort will have construction and device interconnection applications in terrestrial harsh environments, such as desserts and dry climates, down-hole geothermal and oil machines, and mining operations.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Manned-Manuvering Units
Portable Life Support
Suits
Tribology

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The severity of the lunar dust problems encountered during the Apollo missions were consistently underestimated by ground tests, illustrating the need to develop significantly better lunar dust simulants and simulation facilities. ORBITEC proposes to develop a family of High-Fidelity Lunar Dust Simulants that will better match the unique properties of lunar dust than existing simulants (such as JSC-1AF). Current lunar dust simulants do not have enough of the very fine particles, and they lack the agglutinitic glass and complex surface textures that dominate lunar dust. The proposed family of High-Fidelity Lunar Dust Simulants will approximate the size, morphology, composition, and other important properties of lunar dust. High-Fidelity Lunar Dust Simulants are required to physically evaluate the effects of lunar dust on the operation of all Exploration Surface Systems and to verify the effectiveness of dust mitigation strategies and technologies. The proposed Phase 1 effort will define requirements, develop, characterize, and deliver a sample of a prototype lunar dust simulant to NASA (TRL 4). The Phase 2 effort will refine the production process to create a large quantity of lunar dust simulant that will be characterized and delivered to NASA (TRL 6).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High-fidelity lunar dust simulants are required to physically evaluate the effects of lunar dust on the operation of all Exploration Surface Systems. Accurate lunar dust simulants will be needed to verify the effectiveness of dust mitigation strategies and technologies for extravehicular mobility suit material composition and cleaning operations, lunar habitat construction design, mechanical performance (radiators, seals, valves), electrical performance (tools and equipment), landing operations (vision systems), and all manners of surface operations. Since this simulant will also contain the critical metallic iron component (including "nanophase" iron) along with the morphology of true lunar dust, it will also be applicable to human health and toxicity studies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of High-fidelity Lunar Dust Simulants is clearly focused on supporting the needs of the NASA lunar exploration program. However, industry and research institutions that are developing any EVA equipment for use on the lunar surface will require the High-Fidelity Lunar Dust Simulant. Much of this work in the near future will be under NASA contracts. Longer term, private industry plans to develop a variety of EVA equipment for use on the lunar surface. High-Fidelity Lunar Dust Simulants are required to physically evaluate the effects of lunar dust on the operation of all Exploration Surface Systems and to verify the effectiveness of dust mitigation strategies and technologies.

TECHNOLOGY TAXONOMY MAPPING
Testing Facilities
In-situ Resource Utilization

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ElectroChem proposes technology advances in its unique PEM IFF water electrolyzer design to meet the NASA requirement for an electrolyzer that will operate very efficiently both at low current densities and at high pressures. This SBIR effort will develop technical solutions to the draw-back of high pressure operation, namely hydrogen gas crossover losses, that is, an increased diffusion of hydrogen across the membrane which effectively decreases the efficiency. Two approaches to reducing gas permeation through the membrane at high pressure will be investigated: 1) The use of palladium thin films embedded in the membrane; and 2) The use of Nafion proton conductive polymer-clay nanocomposite blends. Two different bonding approaches and membrane configurations will be used for the first approach. Determining the best composition is the key for the second approach. Promising candidates will be determined by two tests: 1) hydrogen permeability tests; and 2) proton conduction measurements to assure that the effects of reducing hydrogen permeability will not affect electrochemical proton conduction. Finally, the most promising candidates will undergo their final Ph I proof of concept tests in a PEM IFF electrochemical cell. Phase I will lead to the Ph II development of a complete PEM IFF Electrolyzer System and delivery of a demonstration unit to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The RFC has long been the leading energy storage candidate for supplying stationary power for the fourteen day/night cycle on the Moon. Of the two major subsystems in the RFC, water electrolyzers are at a lower technology readiness level (TRLs) than primary fuel cells. ElectroChem's proposed technology advance in its unique PEM IFF Water Electrolyzer design will meet the NASA requirement for an electrolyzer that will operate very efficiently both at low current densities and at high pressures. This will result in reduced system weight and volume. In addition, incorporating ElectroChem's advanced water electrolyzer in its unique IFF design will produce a more stable and passive RFC for providing power for Exploration missions at remote locations. The characteristics of the proposed RFC, containing its advanced PEM Water Electrolyzer design, are ideal for providing UPS backup power for NASA applications, either in space or on earth, and for providing portable power for landers and rovers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
For terrestrial applications ElectroChem's PEM IFF Water Electrolyzer is ideal for future auto refueling stations. Also, IFF PEM RFCs, containing the advanced water electrolyzer design, will be strong candidates for supplying power to remote sites with solar and/or off-peak utility power as sources of electrolyzer input power. Because of difficult maintenance problems, ElectroChem's highly reliable, stable, long life IFF PEM RFC will be an excellent replacement for the lead acid batteries used in Navy Bases. In the Transportation area, advanced RFC systems are being considered for a wide range of vehicles. For the UPS industry, ElectroChem's advanced RFC has many very unique characteristics that are very attractive to hospitals, telecommunications, and other business activities where down time is critical. Unlike battery power storage systems, the RFC's power and cycle duration are independent, which provides the designer much more freedom in meeting the specific needs of the UPS application, including siting.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage
Renewable Energy

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Utilizing high strength polymers with controlled pore dimensions as a support, a customized membrane electrode assembly (MEA) can be generated for NASA's electrolyzer stack that has optimized electrochemical performance with greatly improved mechanical properties enabling high pressure (>1000 psi) operation. The overall objective is to generate and test an optimized dimensionally stable membrane (DSM) for a lunar NASA application. This will be accomplished through four tasks; 1. Generation of DSM MEAs of various configurations; 2. Testing of these MEAs; 3. Modeling and fitting of test data to electrolyzer performance; 4. Use model to generate optimum 1000 psi Electrolyzer MEA and test.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lunar and space stations, satellites, high altitude aircraft

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Fuel cell vehicles, hydrogen filling stations, chlor-alkali process

TECHNOLOGY TAXONOMY MAPPING
Composites
Energy Storage

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Water electrolyzer stacks are a key component of regenerative fuel cells, designed to replace batteries as a means of storing electric energy on the lunar surface. The design and demonstration of an innovative water electrolyzer cell is proposed. The cell design will be significantly smaller and lighter than previous aerospace electrolyzers designed and built by Giner Electrochemical Systems, LLC. The new cell will support high-efficiency electrolysis at pressures up to 2,000 psi. Test data will be used to calibrate electrolyzer performance models. These models will, in turn, be used to guide design decisions for regenerative fuel cells relative to the electrolyzer stack and maximum operating/gas-storage pressures of the regenerative fuel cell. A preliminary analysis of an advanced cell frame new thermoplastic material will be conducted to determine its suitability for use in water electrolyzers. Successful completion of the first phase will lead to the development of a demonstration stack in a second phase.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA is charged with returning humans to the moon in a permanently occupied lunar station. This station will require electric power during both the daylight hours, and the nighttime. The lunar day/night cycle is twenty-eight (28) earth days long. This necessitates commensurately larger quantities of stored product/reactant gases for the regenerative fuel cell. A very high-pressure water electrolyzer as a component of a closed-loop regenerative fuel cell will permit smaller launch volumes, saving space aboard the Orion crew exploration vehicle. The electrolyzer will also be useful for the production of hydrogen and oxygen for space vehicle propulsion, enabling missions to Mars. Other electrolyzers may be used to produced oxygen for life support systems both during flight and on the lunar and Martian surfaces.

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

TECHNOLOGY TAXONOMY MAPPING
Energy Storage
Photovoltaic Conversion
Thermodynamic Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Yardney Technical Products, Inc.
82 Mechanic Street
Pawcatuck, CT 06379-2154

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Malgazorta Gulbinska
mgulbinska@lithion.com
82 Mechanic Street
Pawcatuck,  CT 06379-2154

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Non-incremental improvements are necessary in lithium-ion batteries order to meet future space applications demands such as NASA's call for lithium-ion battery cathodes with specific capacity values exceeding 240mAh/g at C/2 discharge rate and 25ºC. Novel concepts for lithium-ion battery chemistry and/or design are therefore desired. Yardney Technical Products, Inc. proposes a development of an advanced nano-composite cathode, based on two crucial components, each performing a different vital function: &#61607; The first component, a layered non-transition oxide material will provide the matrix of the composite and ensure that the cathode voltage falls above ~4.0V. &#61607; The metallic nano-particulate domains, dispersed uniformly within the layered oxide matrix will provide the composite cathode with a potentially high specific capacity. Metallic nanoparticles are expected to form an in-situ oxide phase upon cycling in a lithium ion battery. The composite electrode material may be coated with a thin layer of carbon in order to enhance the electronic conductivity of the as-synthesized composite electrode.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Development of power capabilities is critical in enabling the human exploration beyond Earth orbit pursued by NASA. Lithium ion batteries are required to be human-rated and required to operate over a greater range of temperatures for the lunar environment. Human-rated energy storage devices are required to enable future robotic and human exploration missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of human-rated and inexpensive lithium-ion battery with high energy density is crucial the commercial consumer market and in military applications. Among commercial applications electric vehicle (EV) market and hybrid electric vehicle (HEV) applications would benefit from the safe, reliable and high-performance lithium-ion batteries. YTP will also conduct market studies to identify other niche space, aircraft, military, and commercial markets where the proposed technology would enjoy a unique advantage relative to available battery technologies. Applying a novel power systems solution on these kinds of applications will allow Yardney to establish a growing presence in these markets. Other commercial applications include hybrid electric vehicles, portable instruments (testing and medical), power tools and commercial satellites may soon follow. The developed technology will enhance the desirability of Li-ion technologies for some of these applications.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Aron Newman
newman@psicorp.com
20 New England Business Center
Andover,  MA 01810-1077

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Physical Sciences Inc. (PSI) proposes to develop a hybrid composite structure of molybdenum disulfide (MoS2) with a class of polysulfide for lithium-sulfur rechargeable batteries on a Phase I program. This cathode provides safety, improved cycle-life, and high capacity at a competitive cost. Crystalline MoS2 is low cost and has a theoretical capacity of 335 mAh/g but it has a low conductivity. The nanocomposite design provides a synergistic improvement in conductivity and electrochemical cycling as a result of the layered MoS2 structure, provided by the intercalation of polysulfide. In the Phase I program, PSI will demonstrate a technology readiness level of 3 with a cathode energy density of greater than 350 mAh/g (800 Wh/kg) using 2 mAh cells. These performance goals will result in an overall battery energy density of 350 Wh/kg. In the Phase II program, PSI will increase cell size to 250 mAh and optimize cell design to further improve cycle life.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Energy storage with improved weight and volume performance are required for various NASA applications which are both orbital and planetary surface. Flight elements of the Exploration Vision initially include the Orion and ARES crew and launch vehicles, respectively. For lunar capability, additional elements include the Lunar Lander or Lunar Surface Access Module (LSAM), robotic missions, and surface systems. Surface systems include human habitats, Extravehicular Activities (EVA), science measurements, and the utilization of in situ resources. This lithium-sulfur battery system has the capability to be scaled to the size requirement of 10 kWh in addition to having high-energy density, long-life energy storage systems, and a greater temperature range than lithium ion batteries. The battery system has intrinsic safety and lends itself to being human rated for Exploration missions. These mission applications include portable power for landers, rovers, and astronaut equipment; storage systems for crew exploration vehicles and spacecraft; and stationary energy storage applications such as base power or peaking power applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The portable electronic industry needs improved energy density power sources for longer runtime. The consumer electronics industry is continually driving in the direction of smaller devices that require high specific energy and high specific power batteries. The PSI technology represents a substantial increase in performance over current state of the art and it is anticipated that a battery based on this technology will be lower in lifetime cost to current offerings. Therefore, this low-cost battery is appropriate for many applications, including: mobile telephones, lap-top computers, power tools, personal data assistants, portable entertainment devices.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TIAX, LLC
15 Acorn Park
Cambridge, MA 02140-2301

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Muharrem Kunduraci
Kunduraci.Muharrem@TIAXLLC.com
TIAX LLC, 15 Acorn Park
Cambridge,  MA 02140-2301

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
TIAX proposes to develop as a novel negative electrode active material for rechargeable lithium-ion batteries. This material will fill the gap between the state-of-the-art high energy density (e.g. graphitic carbon or amorphous tin-carbon composite) and high charging rate capability (e.g. nano-Li4Ti5O12) anode materials. The novel anode material will have specific capacity of 625 mAh/g and electrochemical potential of ~0.9 V vs. Li, making it capable of meeting NASA battery energy target of 180 Wh/kg. The mechanism of its electrochemical cycling will be by zero-strain topotactic lithiation/delithiation, making it capable of meeting NASA's requirements for cycle life and for rapid recharge capability. This novel anode material will provide for lithium-ion batteries having enhanced safety by virtue of its being non-toxic and having low thermal reactivity. Furthermore, the use of this novel anode chemistry will enable the implementation of other lithium-ion battery system enhancements, such as improved electrolytes. The Phase I program will demonstrate synthesis of the targeted material composition in the desired structure, and will demonstrate electrochemical performance of that material. Correlations between physical, structural and electrochemical properties of this novel anode material will be investigated through the course the program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Rechargeable lithium-ion batteries incorporating the proposed novel anode are expected to become the primary regenerative electrical energy storage technology for a broad spectrum of NASA space exploration platforms including spacecraft, landers, rovers and other vehicles, astronaut equipment and stationary units. Lithium-ion batteries already possess the outstanding high specific energy required for NASA applications, and further improving their charge rate capability and their life charging rate capability will make them even more competitive in NASA applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There will be significant market opportunities for the TIAX rapid recharge, high energy, long life Li-ion battery anode technology beyond those presented by the NASA's needs for advanced batteries in space exploration platforms. The emerging commercial sector HEV and future PHEV applications will place the same demands for rapid recharge, long life and safety on Li-ion technology as do the NASA's space exploration applications, and if the TIAX technology is successful it will be highly valued in HEVs. Enhanced charging rate capability will also make the novel TIAX anode attractive for use in lithium-ion batteries for power tools. Thus the technology's potential for use in the broader commercial sector that will help to drive its development and to facilitate its availability and drive down its cost for use in space applications.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Brian Williams
brian.williams@ultramet.com
Ultramet
Pacoima,  CA 91331-2210

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Fission-based power systems are anticipated for various planetary surface human base applications with power levels of 30–100+ kWe. The development of high temperature, high efficiency heat exchangers, turbines, and pumps is critical for next-generation nuclear power and space propulsion systems. High temperature heat exchangers are required for nuclear reactors to operate above 1000 K and take advantage of improved Brayton cycle efficiency at high inlet temperatures. In previous work for the Department of Energy involving fusion reactor components, Ultramet demonstrated the capability of an innovative heat exchanger composed of a highly porous, open-cell refractory metal foam coolant channel enclosed within a solid refractory metal shell of the same material. High heat flux testing with helium coolant was performed at the Sandia National Laboratories Plasma Materials Test Facility. A component survived heat flux levels up to 22.36 MW/m2 (2236 W/cm2). The turbulence created by flowing helium coolant through highly porous open-cell foam dramatically increased heat transfer relative to a conventional open coolant channel. Foam core heat exchanger technology is anticipated to substantially improve power conversion efficiency of liquid metal-to-gas, high temperature heat exchangers for fission surface power systems. Ultramet proposes to team with Sandia to design a component and demonstrate initial feasibility.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Lunar bases and colonies would be strategic assets for effective utilization of abundant lunar resources and development and testing of space technologies required for further exploration and colonization of favorable places in the solar system. A reliable power system is required to supply energy demands for life support, science, and operation. The proposed fission power system has the potential to provide the necessary high power conversion to meet surface power requirements.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to compact, high efficiency space reactors, the proposed technology could contribute to a new Department of Energy Generation IV power system that significantly lowers cost, improves passive safety, has no carbon dioxide emissions, uses an advanced, proliferation-resistant fuel cycle, and reduces nuclear waste. The foam core heat exchanger technology could also be used in ground-based power or in portable power systems for military or surveillance applications and remote deployment.

TECHNOLOGY TAXONOMY MAPPING
Ceramics
Composites
Metallics
Multifunctional/Smart Materials
Nuclear Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Payload Systems, Inc.
247 Third Street
Cambridge, MA 02142-1129

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Merk
merk@payload.com
247 Third Street
Cambridge,  MA 02142-1129

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Nuclear reactors to support future lunar and Mars robotic and manned missions impose new and innovative technological requirements for their control and protection instrumentation. Long duration surface missions necessitate reliable autonomous operation, and manned missions impose the added requirement of fail-safe reactor protection systems. There is a need to define an advanced instrumentation and control system for space-nuclear reactors that addresses both aspects of autonomous operation and safety. The constraints and conditions imposed on instrumentation for earth-based reactors are stringent enough to provide an excellent reference for a similar space-based system. However, these systems are typically analog-digital hybrids, and are not optimized for mass, volume, or power consumption. As a result, there is currently no earth-based reactor control system that is practical for use in space. We propose to develop a comprehensive reactor instrumentation and control system based on proven technology used at nuclear research facilities, for operation in the space environment and in particular for nuclear surface power facilities. The heritage established by these terrestrial 'reference' reactors through years of flawless operation on earth make them ideal candidates on which to base a compact, fully-digital space instrument for the control and protection of nuclear surface power systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA foresees numerous applications of nuclear power reactors, with anticipated power needs that might range from a few kilowatts to the megawatt level. Illustrative examples of these applications are: deep-space missions, orbiting power stations, weather stations, habitats, surface mobility for robotic & piloted rovers; excavating and mining equipment, and science payloads in general. All of these applications will require autonomous systems for control, safety and monitoring of the reactor. Space-qualified reactor instrumentation and control systems will be a useful COTS product for manufacturers of space-qualified nuclear reactors. The predicted total demand is subject to the development of space-based nuclear reactors but it is not unthinkable to forecast demand in the order of a dozen a year.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The key likely non-NASA customers for space-based reactors will be the DoD, as part of future space-based surveillance or missile defense systems. At present, we are not aware of a planned system requiring nuclear power. However, given the energy levels, mission durations, and reliability requirements to support the DoD's mission over the next two decades, it is likely that space-nuclear reactors will be needed at some point. With regards to ground-based applications, the concept of a fully-digital, compact, autonomous control system for reactors is very appealing. As part of our WRND effort we contacted several organizations which operate ground facilities. These included the MIT Nuclear Reactor in Cambridge MA and the RA6 nuclear reactor run by the Bariloche Atomic Center in Argentina. These organizations expressed significant interest in the benefits afforded by this type of instrumentation. It is highly likely these same organizations could benefit from the RICS proposed here.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sierra Lobo, Inc.
426 Croghan Street
Fremont, OH 43420-2448

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Stochl
rstochl@sierralobo.com
11401 Hoover Road
Milan,  OH 44846-9711

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The ability to store large amounts of cryogenic fluids for long durations has a profound effect on the success of many future space programs using these fluids for propellants, reactants, and life support systems. The high cost of delivering payload mass to orbit will require storage systems capable of limiting cryogenic losses due to boil-off to less than two percent per year for mission durations of up to ten years; or in some cases, completely eliminating boil-off losses. Although Multi-Layer Insulation (MLI) Systems have been extensively used to insulate cryogenic vessels in a space environment, it has been for short-duration missions that require from 30 to 50 layers to meet the mission requirements. Conversely, 150 layers or more of MLI will likely be needed to meet the requirements of future long-term missions. Limited data exists on the performance and physical characteristics of these thick MLI systems. A key opportunity relative to the development of advanced MLI insulation systems is identifying and analyzing concepts for minimizing heat-leak through seams and penetrations, which will be the major contributor to cryogenic losses for thick MLI systems. Sierra Lobo proposes to identify the more promising seam and penetration concepts, based upon previous research with the Missile Defense Agency, and to provide an analytical model to evaluate their performance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Application of this technology would significantly reduce the losses associated with the storage of cryogenic fluids. The advanced insulation techniques being proposed by Sierra Lobo will directly benefit NASA's Space Exploration Program. Cryogenic fluids such as hydrogen, methane, and oxygen are required for many current and future space missions that will use life-support, propulsion, and power systems. The targeted NASA applications for long term cryogenic propellant storage, in-space as well as on the lunar surface, include space transportation orbit transfer vehicles, space power systems, spaceports, spacesuits, lunar habitation systems, and in situ propellant systems. In addition, NASA spaceport operations and propulsion test facilities are both heavily dependant upon a wide range of cryogenic systems. Improving the efficiency of these systems at these facilities using advanced insulation techniques will directly benefit the programs they support through reduced operating costs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The advanced insulation techniques being proposed by Sierra Lobo can be used in nearly any industrial, commercial, or medical application currently requiring storage of liquid cryogens such as helium, hydrogen, nitrogen, and oxygen. Such fluids are routinely used in the medical industry, metals processing, semiconductor manufacture and as well as many non-NASA government agencies. The targeted applications for the Department of Defense include Unmanned Underwater Vehicles (UUV) that carry liquid oxygen and potentially liquid hydrogen, liquid hydrogen powered ground transportation systems, space platforms using electric propulsion (xenon, hydrogen), space-based chemical lasers (hydrogen, helium), orbit transfer vehicles (hydrogen, oxygen), and orbital propellant depots/space stations (hydrogen, oxygen, nitrogen). The Department of Energy applications include reducing heat leak into liquid helium cooled superconducting magnets for particle acceleration systems. Commercial market applications include cryogenic storage dewars for medical and process systems and over-the-road dewars for transporting cryogenics, especially the lower temperature cryogens, liquid hydrogen and helium.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Propellant Storage
Simulation Modeling Environment
Testing Facilities
Thermal Insulating Materials
Fluid Storage and Handling
Production
In-situ Resource Utilization
Radiation Shielding Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Creare, Inc.
P.O. Box 71
Hanover, NH 03755-3116

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark Zagarola
mvz@creare.com
P.O. Box 71
Hanover,  NH 03755-3116

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Long-life, high-capacity cryocoolers are a critical need for future space systems utilizing stored cryogens. The cooling requirements for planetary and extraterrestrial exploration missions, Crew Exploration Vehicles, extended-life orbital transfer vehicles, and space depots will range from 10 to 50 W at temperatures between 20 and 120 K. Turbo-Brayton cryocoolers are ideal for these systems because they are lightweight, compact and very efficient at high cooling loads, in addition to their inherent attributes of high reliability; negligible vibration; long, maintenance-free lifetimes; and flexibility in integrating with spacecraft systems and instruments. To date, space-borne turbo-Brayton technology has been developed for low cooling loads. During the proposed program, Creare will develop an advanced, high efficiency turbine optimized for a high-capacity cryocooler. The advanced turbine will enable a landmark reduction in cryocooler input power and overall cooling system mass. In Phase I, we will define the requirements for a particular mission class, develop the conceptual design of a multistage cryocooler to meet these requirements, develop the preliminary design of the advanced turbine and perform proof-of-concept tests. During Phase II, we will fabricate the turbine and demonstrate its performance at prototypical operating conditions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced turbines will enable high-capacity turbo-Brayton cryocoolers that are compact, lightweight, and consume minimal power. Space applications include cryogen storage for planetary and extraterrestrial exploration missions, Crew Exploration Vehicles, extended-life orbital transfer vehicles, long-term geosynchronous missions, in-space propellant depots and extraterrestrial bases, and cooling systems for observation platforms requiring large arrays of infrared and X-ray detectors. Terrestrial applications include cooling for spaceport cryogen storage and cryogen transportation systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications include cooling for laboratory- and industrial-scale gas separation; liquefaction; cryogen storage and cryogen transportation systems; high-temperature superconducting magnets in motors and magnetic resonance imaging systems; liquid hydrogen fuel cell storage for the automotive industry; and commercial orbital transfer vehicles and satellites.

TECHNOLOGY TAXONOMY MAPPING
Fluid Storage and Handling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Orion Propulsion, Inc.
105 A-4 Commerce Circle
Madison, AL 35758-2637

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tim Pickens
tpickens@orionpropulsion.com
105 A-4 Commerce Circle
Madison,  AL 35758-2637

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An acoustic igniter eliminates the need to use electrical energy to drive spark systems to initiate combustion in liquid-propellant rockets. It does not involve the use of catalysts (which have a limited life), it does not exhibit typical wear and tear as seen in spark and catalytic igniters, and it is simple in design with no moving parts. Orion's proposed Acoustic Igniter is expected to offer a long-life, highly reliable ignition system that does not require high-voltage electrical connections. It is less complex to operate and simpler than a traditional ignition system. Orion's primary technical objective is to produce an acoustic igniter design that will ignite combustion of common liquid rocket fuel and oxidizer combinations such as gaseous oxygen and kerosene, and oxygen/methane. During Phase 1, we will analyze the operational issues that inhibit acoustic igniter performance. Based on these results, Orion will build a prototype unit, test it, and evaluate its performance. This work will be sufficiently broad and deep to establish a basis for the follow-on Phase 2 effort to refine the design and upgrade the technology level of the acoustic igniter.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The acoustic igniter can be used in every current and planned liquid propellant rocket engine to cut cost, weight, and complexity. When the technology level of the igniter reaches a sufficient level to be considered on a competitive tradeoff basis, NASA programs, i.e., Ares and Orion, will be obvious candidates for the acoustic igniter benefits. Commercial launch vehicles such as the Space-X Falcon 1 and 5 launchers, Pegasus, and Taurus are also candidates. Orion is developing its own small launch vehicle for commercial applications. Consequently, we will be performing such a trade off study when it is timely.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The acoustic igniter can be used in every current and planned liquid propellant rocket engine to cut cost, weight, and complexity. When the technology level of the igniter reaches a sufficient level to be considered on a competitive trade off basis, Non NASA programs, i.e., Air Force heavy lift launcher vehicles. Delta and Atlas, are likely prospects. Other vehicles, mostly foreign, such as Ariane, Soyuz, Long March, Vega, Proton, Athena and Zenit (Sea Launch) could be candidate users, if ITAR restrictions can be overcome.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Fundamental Propulsion Physics
Feed System Components

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Firestar Engineering, LLC
557 Burbank Street, Unit J
Broomfield, CO 80020-7160

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Fisher
david@firestar-engineering.com
557 Burbank Street, Unit J
Broomfield,  CO 80020-7160

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose conducting further development for a Nitrous Oxide Fuel Blend (NOFB) propulsion system. Phase I activities will concentrate on a revising a previous 5 lbf thruster to facilitate continuous operation with repeated restart. The thruster will utilize a novel new NOFB monopropellant. NOFB series monopropellant formulations have the following characteristics: 1) Non-toxic and readily manufacturable; 2) Vacuum specific impulse of 310+s (compared to monopropellant hydrazine's 235s); 3) Space-storable with wide temperature storage limits from <-77 C to >100 C; 4) High storage density at equivalent to twice as dense as monopropellant hydrazine depending on temperature; 5) Potentially highly throttleable due to very fast reaction kinetics; and 6) Self-pressurizing thereby simplifying the overall feed system architecture and reliability. Due to these desirable characteristics of NOFB monopropellants, Phase I funding is requested from the NASA SBIR program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Increasingly demanding in-space propulsion requirements will benefit from NOFB monopropellants. Lunar launders require high Isp rocket propulsion. By utilizing NOFB monopropellants, the mass associated with bipropellant system hardware can be eliminated without a significant decrease in Isp performance. Additionally, the limiting factor on many satellite's life is their propellant reserves. By increasing the Isp from hydrazine's ~230 s to NOFB3's ~310 s, greater total impulse can be achieved with the same mass as legacy propulsion systems. This will serve to either lengthen the life of a satellite, facilitate greater non-propulsion system payload, or a combination of both.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commercial spacecraft will also benefit from the increased performance of NOFB monopropellants. Launching satellites is an expensive endeavor. To maximize the cost/benefit ratio, extended satellite life is very attractive. Because our monopropellants have >30% improvements in specific impulse performance, a satellite's life can be extended without requiring larger and more expensive launch vehicles. The private sector can achieve longer satellite life without increased expenditures or decreased payload capabilities.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Monopropellants
Propellant Storage
Feed System Components
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SPACEDEV
13855 Stowe Drive
Poway, CA 92064-6800

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jeffery Hickerson
Jeffery.Hickerson@SpaceDev.com
13855 Stowe Drive
Poway,  CA 92064-6800

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Engineers at SpaceDev have conducted a preliminary design and analysis of a proprietary annular design concept for a hybrid motor. A U.S. Patent application has been submitted and is pending approval. The annular hybrid motor is an improvement to hybrid rocket motor technology that can be used for a wide range of applications. The technology will lead to improvements in hybrid payload mass fraction, increased performance during throttling, and reduced costs associated with casting hybrid fuel grains. The technology is highly scalable and can be used for applications ranging from small thrusters on satellites, to launch vehicle booster applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
SpaceDev believes that the Annular Hybrid Motor has a wide range of possible applications to both government and commercial customers. Efficiency gains realized by decreased O/F shift and increased fuel utilization benefit all applications using the Annular Hybrid Motor. Similarly, cost savings associated with simplified fuel grain design and thermal management are beneficial across the board Applications that are currently being explored for the annular hybrid motor include: Compact motors for satellite applications Sounding Rockets Upper Stage Motors Full Launch Vehicle

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Given that space is at a premium in satellites – particularly in microsatellites and nanosatellites – the Annular Hybrid Motor's increased packing options would be of immediate benefit to satellite designers. Also, many satellite CONOPs call for multiple burns in their nominal missions as well as to be available for additional contingency burns. The improved restart ability of the Annular Hybrid Motor would be helpful in this regard for both satellite motors and upper stages. Finally, the Annular Hybrid Motor has possible applications in the space tourism market.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Propellant Storage
Launch and Flight Vehicle
Tankage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Plasma Processes, Inc.
4914 Moores Mill Road
Huntsville, AL 35811-1558

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Daniel Butts
dbutts@plasmapros.com
4914 Moores Mill Road
Huntsville,  AL 35811-1558

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Pratt and Whitney Rocketdyne (PWR) J-2X engine will power the upper stage of the Ares I and the earth departure stage (EDS) of the Ares V, which will enable manned travels to the Moon and eventually Mars. Building on Apollo heritage, the J-2X is a derivative of the J 2 engine. One unique feature of the J-2X is its planned carbon/carbon (C/C) composite nozzle extension, which will replace the heavy metallic extension and increase engine performance. Currently, NASA and PWR plan to employ a Noveltex or Naxeco C/C nozzle extension from a foreign supplier on the J-2X. Plasma Processes Inc., with the support from ATK Launch Systems, proposes a program with the primary goal of demonstrating a domestically produced C/C composite nozzle extension for use on the J-2X. The specific objectives include evaluation of higher strength C/C materials and manufacturing methods, investigation of oxygen protective coatings and design of nozzle extension subcomponent. The team of Plasma Processes, Inc. and ATK Launch Systems offers a state of the art skill set that is uniquely suited to the Phase I program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Leading edges and control surfaces for hypersonic aircraft Propulsion components for space access and space return vehicles Propulsion components for Moon/Mars landing vehicles Common Extensible Cryogenic Engine (CECE)

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Nosetips , rocket nozzles and control vanes for strategic and tactical missiles Thermal control components for nuclear power applications. Crucibles

TECHNOLOGY TAXONOMY MAPPING
Chemical
Micro Thrusters
Monopropellants
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Solar
Ceramics
Composites
Metallics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Touchstone Research Laboratory, Ltd.
The Millenium Centre, RR 1, Box 100B
Triadelphia, WV 26059-9707

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Harry Danford
hed@trl.com
Touchstone Research Laboratory, Ltd.
Triadelphia,  WV 26059-9707

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal addresses NASA's need for improved TPS materials. The incumbent CEV heatshield TPS for Orion's Block II lunar return is PICA, a low-density carbon fiber infiltrated with phenolic resin. Variants of PICA with improved thermomechanical properties would benefit future missions. This effort will create a series of "mid-density" ablative materials to fill the gap between low-density PICA and high-density Carbon-Carbon. Touchstone's carbon foam (CFOAM<SUP>REG</SUP>) has excellent thermomechanical properties, can be tailored to a range of densities (12 to 95 lbs/cu-ft), and has an open-cell structure allowing infiltration of high-temperature materials. Aspen Aerogels recently completed a Phase II subcontract with Touchstone demonstrating the capability of fully infiltrating CFOAM<SUP>REG</SUP> with phloroglucinol-furfuraldehyde carbon aerogels with chemistry similar to PICA's. Phase I will use carbon aerogel infiltration in CFOAM<SUP>REG</SUP> samples of 3 densities from 17 to 35 lb/cu-ft to be calcined at Touchstone to carbonize the aerogel, creating a mass of amorphous carbon within the pore structure. Filling CFOAM<SUP>REG</SUP> pores with pure carbon yields an inherent reduction in the TPS radiant heat transfer. Fully carbonized samples will be re-infiltrated with PICA phenolic resin, and sample characterization will be conducted via SEM to demonstrate the capability of producing small-scale Carbon Foam-Aerogel/Phenolic composites at various densities. At the end of Phase I, the TRL will be 3-4 and then 4-5 by the conclusion of Phase II.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Larger vehicle size and entry conditions of future NASA missions demand TPS materials beyond the PICA ablator in use since the 1976 Viking mission. This proposed effort will provide significant benefit to NASA by introducing a new class of TPS materials critical to upcoming explorations. With tailoring capability, the material has potential to create a suite of ablative TPS materials that can be chosen based on aerothermal conditions and density requirements of particular missions. The Astrobiology Mission to Mars is a new robotic sample return initiative where larger vehicles and higher re-entry speeds produce more severe combined environments (turbulent flow, combined convective and radiative heating rates) than previous missions. The ESMD Orion Block III crew exploration vehicle (Mars return) is a future NASA mission with the heatshield's TPS material to be determined. The TPS material challenge is that the heating rates will be five times greater than for lunar return.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The benefits of this effort stand to be of enormous value not only to NASA but also to the Department of Defense. The potential exists to use these (ablative) TPS materials for the U.S. Army Space & Missile Defense Command (SMDC) as thermal protection components of next-generation hypersonic weapon systems such as Kinetic Energy Interceptor (KEI) and the Advanced Hypersonic Glide Vehicle (AHGV). Large aerospace contractors such as Lockheed Martin, Boeing, and Raytheon stand to benefit from the development of these new TPS material solutions by providing new TPS technologies at a manufacturable scale to support key DoD initiatives.

TECHNOLOGY TAXONOMY MAPPING
Ablatives
Launch and Flight Vehicle
Thermal Insulating Materials
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Eltron Research & Development, Inc.
4600 Nautilus Court South
Boulder, CO 80301-3241

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Richard Bley
eltron@eltronresearch.com
4600 Nautilus Court South
Boulder,  CO 80301-3241

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this work is developing new thermoelectric materials for use in fabricating solid state cooling devices and electrical power generators, which are 200 to 300% more efficient than current thermoelectric materials and can operate in temperatures ranging from cryogenic to 700 C. These materials will be made from new nano-composites, using fabrication techniques developed at Eltron. The proposed thermoelectric composite's matrix has already demonstrated exceptional ability for functioning in the environment of space. Used in a cooling system, these materials will provide an effective means for controlling the temperature of surfaces subject to the rapidly changing temperatures encountered in space. They can be used to prevent development of large temperature gradients and thereby prevent the mechanical stresses that accompany them. Used for power-generation, these new materials will be very efficient both because of the properties that the nano-phase materials and its matrix bring to the thermoelectric material. Because of the difficulties presented in the harsh environment of space, thermal management and power generation is most easily provided through devices that do not have any moving parts, are very durable, do not require maintenance, and operate efficiently over a wide range of temperatures. The proposed materials meet all these requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In the past, NASA's interest in thermoelectric systems has stemmed both from the need for an effective means of temperature control via the Peltier effect for surfaces exposed to the rapidly changing temperatures that occur in space, and for use in generating electrical power via the Seebeck effect for space vehicles too distant from the sun for effective use of solar panels. The new materials being developed here will be capable of withstanding both high and low temperatures and so they can be used to prevent development of large temperature gradients and the mechanical stresses that accompany them on missions such as the upcoming Mars and Venus trips. This is particularly true of the Venus landing, where materials will need to withstand up to 500 C temperatures. The improvement in efficiency possible from these materials could make them competitive with solar cells as a power source for space missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Successful development of this technology could result in considerable improvement in efficiency over currently used evaporative systems used in consumer and industrial refrigeration. This technology would also be of great value to the electronics industry. Systems incorporating this new technology will run more quietly and will produce much less pollution than current refrigeration and air conditioning systems. They will not be subject to the maintenance problems common in the compressors used today. An efficient, solid state electrical power generator that uses heat as its energy source would also result from successful development of this technology. The Boeing Company is very interested in seeing this Phase I project succeed because of the great potential for reducing fuel in air vehicles. They have asked to be able to participate in this project in an advisory and reviewer capacity, as stated in their letter of support.

TECHNOLOGY TAXONOMY MAPPING
Cooling
Composites
Semi-Conductors/Solid State Device Materials
Thermoelectric Conversion

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
William Anderson
bill.anderson@1-ACT.com
1046 New Holland Avenue
Lancaster,  PA 17601-5688

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Long-term Lunar and Martian systems present challenges to thermal control systems, including changes in thermal load, and large changes in the thermal environment between Lunar (or Martian) day and night. The Lunar thermal environment typically includes long periods in extremely cold thermal environments. A variable conductance heat pipe (VCHP) radiator will be developed that passively accommodates the changing thermal load and environment. In a VCHP, a non-condensable gas is added that blocks a portion of the condenser. The gas charge blocks more of the condenser as the heat pipe evaporator temperature changes. This allows the heat pipe evaporators (and any attached heat exchanger) to remain at an almost constant temperature. In addition to passively controlling the thermal load, the gas allows the fluid in the heat pipe to freeze in a controlled fashion as the heat pipe is shut down, avoiding damage. In addition, the gas in the VCHP will help with start-up from a frozen condition.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate NASA application is for Lunar and Martian radiators that can passively accommodate the large swings in environmental conditions between Lunar (or Martian) day and night, including long periods at very low temperatures. In addition, the VCHP can passively accommodate large changes in thermal load, and avoid damage during periods of low thermal load. In addition, the non-condensable gas in the VCHP will help with the heat pipe start-up from cold conditions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A commercial application is VCHP heat exchangers in fuel cell reformers. In a fuel cell reformer, diesel fuel and air pass through a series of high temperature reactors to generate hydrogen. The operating temperature of the reactors must be closely controlled to maintain their chemical equilibrium. A typical system must maintain inlet and outlet temperatures within ±30<SUP>o</SUP>C despite a turndown ratio of 5:1 in reactant flow rate. The current scheme uses a bypass valve, which has several drawbacks: it requires active control, requires power, and has a large pressure drop. ACT believes that VCHP heat exchangers can replace the current heat exchanger and control system with a passive system that automatically maintains the output stream from the heat exchanger at a constant temperature.

TECHNOLOGY TAXONOMY MAPPING
Cooling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Energy Science Laboratories, Inc.
6888 Nancy Ridge Drive
San Diego, CA 92121-2232

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Timothy Knowles
tknowles@esli.com
6888 Nancy Ridge Drive
San Diego,  CA 92121-2232

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR proposal aims to develop thermal energy storage heat exchangers that are significantly lighter and higher conductance than the present art which involves significant metal weight. We aim to use carbon fiber for conductive and convective heat transfer enhancements and replace metal with novel carbon-polymer composites. The concept materials can be configured to serve a broad range of thermal management applications for NASA, in particular thermal storage heat exchangers. Phase 1 will gather NASA requirements for near term systems involving active cooling with single- and two-phase loops passive cooling with heat pipes. In particular the Constellation program and the Orion vehicle will be considered to assess the potential benefits of the proposed materials approach. Initial fabrication and characterization of the materials concept will be performed. Design options for Phase 2 development units will be prepared.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Reduced size and weight of thermal management hardware in Low earth orbit Lunar orbital and surface missions High power remote sensing Lidar and Radar instruments

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed materials could offer reduced cost of heat exchangers and thermal energy storage for Energy generation Defense Directed Energy programs (mobile high energy laser and high power microwave) Commercial refrigeration, HVAC equipment Computer server and consumer electronics

TECHNOLOGY TAXONOMY MAPPING
Cooling
Composites

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Illuminex Corporation
1064 New Holland Avenue
Lancaster , PA 17601-5606

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Youssef Habib
joe.habib@illuminex.biz
1064 New Holland Ave.
Lancaster ,  PA 17601-5606

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Illuminex Corporation proposes a NASA Phase I SBIR project to develop high performance, lightweight, low-profile heat pipes with enhanced thermal transfer properties enabled by utilizing copper nanowire arrays as the wick material in the heat pipe. Thermal management is a critical issue for advanced electronic and optical systems as current cooling techniques are being rapidly outpaced by the heat load of new technologies. Superior thermal control technologies are needed both for NASA's science spacecraft components and commercial products such as computers and medical lasers. The incorporation of nano-structured materials in heat pipe manufacturing will allow the development of thermal management devices with increased heat dissipation efficiency and a reduced size and weight profile as compared to currently utilized cooling approaches. Illuminex will develop processes to engineer the nanowire wick directly onto the heat pipe package, and using this approach, it s envisioned that heat pipe systems can be manufactured directly into the housings of devices requiring advanced thermal management. This nanotechnology enabled miniaturization can be further size reduced to near the MEMS level for cooling micro-electronics and sensors. Phase II will lead to full commercialization and manufacturing of high performance, low profile, and lightweight heat pipes.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Heat pipes are passive, two-phase closed loop systems used for temperature regulation in electronic, power generation/conversion, and optical systems. They require no maintenance and consume no power, making them attractive components for space vehicles, satellites, and astronaut support systems. Illuminex innovation will result in size and weight reductions over current devices. Currently, NASA is developing nuclear electric propulsion systems for long-duration space missions like the Jupiter Icy Moon Orbital mission. Heat pipes are proposed for the transfer of waste heat from the power generation systems and for use in the radiator systems used for the dissipation of the waste heat. Heat pipe thermal control technology has also been proposed for electric power generation for a lunar habitat, for the Space Solar Power Project, and spacecraft thermal control. Improved capillary pumping capabilities in zero gravity and under acceleration in nanowire heat pipes could prove valuable in space applications where gravity assisted systems are not functional.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The thermal characteristics of high-power-density CPUs in today's high-end computing applications are rapidly outpacing the cooling capabilities of commercially available strategies. The primary devices driving the market for nanowire heat pipes are high performance microprocessors. Technological advances in thermal control are needed to accommodate rising power densities in new electronic and optical devices and a steady replacement of traditional heat sinks by hybrid heat sinks with embedded heat pipes. The initial market for the nanowire array wick heat pipes will be the niche market of high end specialty heat pipes designed for military and aerospace applications including laser, radar and antenna systems. The next anticipated specialty market is thermal management in high end servers, followed by portable computers and other electronic consumer goods. Illuminex has partnered with Thermacore Inc., the largest North American manufacturer and distributor of heat pipes to bring the advanced nanowire heat pipe technology to the market.

TECHNOLOGY TAXONOMY MAPPING
Cooling

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
AM Biotechnologies, LLC
6023 Avenue S, #228
Galveston, TX 77551-5419

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Xianbin Yang
xianbin.yang@thioaptamer.com
6023 Ave S, #228
Galveston,  TX 77551-5419

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
AM Biotechnologies (AM) will develop a system to detect and quantify bone demineralization biomarkers as outlined in SBIR Topic "Technologies to Detect Biomarkers". AM will enhance the current clinical gold standard immunoassay methodology by using its proprietary bead-based aptamer selection process to select dithiophosphate backbone-modified (PS2) "thio" aptamers (PS2-thioaptamers) as replacements for antibodies in immunoassays. The PS2-thioaptamers are binding agents with functionality comparable to antibodies but with very long shelf-life under ambient environment storage. The PS2-thioaptamers bind much more tightly to their targets than regular aptamers without sacrificing specificity, and are much more nuclease resistant. AM's bead-based process allows selection and identification of PS2-thioaptamers, which cannot be directly selected using older aptamer technologies such as Systematic Evolution of Ligands by Exponential Enrichment (SELEX). AM will also demonstrate PS2-thioaptamer integration into a state-of-the-art microfluidics instrument from Sandia National Laboratory that meets NASA's form factor needs for space flight. The Phase I Project will demonstrate detection and quantification of osteocalcin (OC) using a PS2-thioaptamer in a prototype microfluidics device (TRL-4). Phase II will entail completing the panel of biomarkers for bone demineralization and delivering a prototype of the system to NASA. In Phase III, AM and Sandia will deliver a flight test system to NASA and begin FDA validation of the system for potential use in clinical diagnostics of osteoporosis as well as other conditions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The combination of AM's proprietary PS2-thioaptamers with the microfluidics technology from Sandia National Laboratory will result in a biomarker detection and quantification system that is compatible with long duration spaceflight. The PS2-thioaptamers offer performance comparable to antibodies but have a very long shelf life and can be stored in ambient conditions. The Sandia microfluidics instrument is small, low mass, easy to operate and draws little power. The combination of these two technologies would result in a flight system that would enable NASA to detect and quantify bone demineralization biomarkers during long duration missions and would also enable NASA to develop other clinical diagnostic assays for many other conditions of interest. The stage of development of these technologies as well as the use of proven clinical diagnostic immunoassay methodologies enables AM to develop and deliver a flight test system quickly for near-term NASA flight research into bone loss as well as other conditions of interest.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A PS2-thioaptamer assay for potentially any condition that has FDA-approved biomarkers could be developed and integrated into the microfluidics instrument, which provides significant clinical diagnostic market commercialization potential. The PS2-thioaptamer binding agents could also be used in almost any detection/quantification technology thus opening the possibility of faster diagnostic market commercialization using current clinical devices. Prior to FDA-approved diagnostic applications, the PS2-thioaptamers could readily be used in a manner similar to antibodies for life science research. Additionally, since the PS2-thioaptamers are very nuclease resistant, it is possible that the same binding agents selected for diagnostic/research use could also be used effectively as therapeutics.

TECHNOLOGY TAXONOMY MAPPING
Biomolecular Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Linea Research Corporation
781 Rosewood Drive
Palo Alto, CA 94303-3638

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Yong Jin Lee
lee@linearesearch.com
781 Rosewood Drive
Palo Alto,  CA 94303-3638

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A key component of NASA's human exploration programs is a system that monitors the health of the crew during the space missions. The wearable physiological monitor proposed by Linea Research Corporation can be used to continuously observe the beat to beat blood pressure. The monitor can be used to observe the physiological effect of various countermeasures against prolonged exposures to reduced gravitational environments. The proposed device will allow the monitoring of the pharmacological effect on blood pressure over prolonged periods. Currently, beat to beat monitoring of blood pressure is done primarily in hospital settings through invasive procedures involving percutaneous insertion of catheters into the radial or brachial arteries. While non-invasive beat to beat blood pressures based on either the Penaz method or arterial applanation tonometry are currently available, they each have limitations. In addition, all monitors are based on large stationary equipment that requires the subject to be immobile. Successful implementation of the proposed program will result in an accurate wearable beat to beat blood pressure measurement.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Autonomous medical care for the crew during human exploration missions is critical in preventing degradation in health due to adverse physiological responses to space flight environments. A wearable multi-parameter physiological monitor that includes continuous blood pressure measurements will be crucial in providing proper medical support for both normal activities and medical emergencies. The device can be used to monitor the long term physiological effects of hypogravity and the effects of the countermeasures against hypogravitational environments. The device can also be used to monitor the health status of crew during extravehicular activities (EVA). The system will be developed with the goal of implementing the monitor as a wearable device which necessitates low power consumption and compact and lightweight form factor. The size criterion is a key factor for space applications as launch costs are directly determined by mass and volume.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed device can fundamentally change the way beat to beat blood pressure is measured in clinical settings. Currently, an accurate measurement of the beat to beat blood pressure requires an insertion of a pressure transducer into the blood vessel. While non-invasive methods that use the Panaz method or applanation tonometry exist, they do not provide the accuracy and repeatability provided by the invasive method. The goal of the proposed research is to develop an accurate beat to beat blood pressure monitoring device that will eventually eliminate the need for cannulation. The wearable nature of the device also provides significant market opportunities. There is a strong need for devices that can provide ambulatory monitoring of physiological parameters for the elderly or for individuals with chronic illness. There is also a market need for devices that can track the physiological status of individuals whose health is at risk from environmental hazards in their working environment (e.g. soldiers, first responders, mountain climbers, etc.).

TECHNOLOGY TAXONOMY MAPPING
Ultra-High Density/Low Power
Pilot Support Systems
Biomedical and Life Support
Optical
Portable Life Support
Optical & Photonic Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Operational Technologies Corporation
4100 N.W. Loop 410
San Antonio, TX 78229-4253

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Bruno
john.bruno@otcorp.com
4100 N.W. Loop 410, Suite 230
San Antonio,  TX 78229-4253

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Astronauts lose approximately 1-1.5% of their bone mass per month during space travel due to a lack of physical stress in the microgravity environment. Although, no effective treatments or prophylactic regimens have yet been defined, it is important to monitor the bone loss process in space. As such, the sensor must be compact and facile to operate. Therefore, OpTech proposes to extend its already successful and patent-pending competitive fluorescence resonance energy transfer (FRET)-aptamer assay technology to the detection of bone loss and formation markers such as osteocalcin fragments, hydroxylysine, hydroxyproline, C-terminal and N-terminal telopeptides. In Phase I, OpTech will develop, clone and sequence aptamers to each of these markers. OpTech will also incorporate fluorophore-labeled dUTP into the sequenced aptamers by asymmetric PCR and complex them to their quencher-labeled bone markers for testing in buffer, animal sera, and urine. Finally, in Phase I OpTech will dry and reconstitute the assays that will be tested using a commercially available handheld, battery-operated fluorometer and validated using OpTech's spectrofluorometer. In Phase II, the FRET-aptamer assays will be optimized and packaged in special leak-proof sealed plastic cuvettes and delivered to NASA along with the handheld fluorometer for testing on the ISS or other space missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA would use this technology as a portable means for astronauts to self-monitor their bone loss with one-touch ease from urine or serum samples. Monitoring of other non-bone-related analytes by NASA would also be possible, if appropriate FRET-assays were developed.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Women and the elderly could use this system as a rapid and facile point-of-care diagnostic system to monitor osteoporosis and the efficacy of therapeutic regimens. The system might also be used to monitor bone repair following severe fractures or skeletal procedures related to plastic or reconstructive surgeries. In a broader sense, OpTech is developing FRET-aptamers for a wide array of analytes on Earth including foodborne and other pathogens and clinical analytes.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biomolecular Sensors
Biochemical
Biophysical Utilization

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Valeo Human Performance, LLC
1235 Clear Lake City Blvd., Suite F
Houston, TX 77062-8105

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Paul Colosky
pcolosky@valeopt.com
1235 Clear Lake City Blvd Ste F
HOUSTON,  TX 77062-8105

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA's vision for future exploration-class missions has made countermeasures for muscle atrophy, bone loss and cardiovascular deconditioning areas of major research design and development within the U.S. space program. Due to restricted volume and mass capabilities within the newly-developing Crew Exploration Vehicle (CEV) and Lunar Surface Access Module (LSAM), there is a need for a multi-functional, compact exercise machine that can incorporate both resistive and aerobic exercise capabilities during lunar sortie missions. The proposed innovation is an exercise device, the multi-functional Constant Force Resistive Exercise Unit (CFREU), that can provide a whole-body workout for aerobic exercise and resistive exercise. The device provides constant force eccentrically and concentrically during multiple exercise configurations, allows resistance selection in 2.5kg increments, requires no power to operate, requires no on-orbit maintenance, and can be stowed in an area of 1 cubic foot. During the Phase I performance period, we propose to develop a prototype of this device and a feasibility assessment of the design for spaceflight and commercial use.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Valeo's competitive advantage lies within the CFREU design. The unit is compact, easy to use, requires no power to operate, and requires no on-orbit maintenance or calibration. There is an evident need for a gravity-independent exercise unit that can provide a constant force for resistive exercise with integrated aerobic capability fashioned in a compact and lightweight design that offers familiarity, safety, and comfort during exercise.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Rehabilitation institutions would benefit from the multi-functional CFREU design. A portable exercise machine that can provide aerobic and constant force resistive capabilities in such a small volume is essential in clinical settings, and would prove especially beneficial in treating patients confined to bed rest. Physiologically, the constant force resistance provided by the CFREU is comparable to a traditional weight stack machine, but without the bulkiness and mass of weight plates. The personal home exercise equipment industry would also benefit from the multi-functional CFREU device. The compact force packs of the CFREU allow the overall unit to be small enough for easy use as a home gym. For the home gym design, future force packs can be designed such that they may be purchased individually by a consumer, and used as portable exercise devices when not in use with the full CFREU. Thus, the force packs replace the need for expensive, heavy, and bulky traditional weight plates, and allow portability.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
The DNA Medicine Institute
116 Charles Street, Suite 6
Boston, MA 02114-3217

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Eugene Chan
echan@dnamedinstitute.com
116 Charles Street, Suite 6
Boston,  MA 02114-3217

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of rHEALTH sensor is a universal handheld sensor that can provide rapid, low-cost complete blood count (CBC) with differential, electrolyte analysis, and potential for advanced lab tests such as biomarker analysis all in one single microfluidic sensor. The first innovation is that the device can perform multiple lab measurements in a single microfluidic device. Most sensors can only perform one test at a time, such as CBC analysis. Adequate health monitoring requires at the minimum measurement of CBC and electrolytes. Second, our microfluidic chip is reusable because of its flow-through design. This minimizes cost and obviates the need for bulky consumables. Third, our sensor uses fluorescent analyte sensing dyes and fluorescence technology, which allows the sensor to measure a broad range of analytes. In Phase I, we plan to fabricate a prototype microfluidic sensor and test it for its ability to perform both CBC and electrolyte measurements. Upon proof-of-principle, in Phase II, our goal is to complete and deliver a prototype rHEALTH sensor for NASA to monitor astronaut health on a routine and cost-effective basis.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
(1) Real-time health monitoring. The proposed rHEALTH sensor is designed to monitor daily astronaut status so that adverse health events can be managed. (2) Real-time intervention. The ability to measure routine health status allows clinical intervention at appropriate times. (3) Electrolyte measurement on a daily basis for long space flight. (4) CBC measurements on a daily basis. (5) Measurement of cardiac biomarkers for chest pain to rule out myocardial infarction. (6) Measurement of CBC and electrolytes in response to astronaut illness. (7) Monitoring of astronaut renal function to assess volume status. (8) Tracking of bone biomarkers and calcium levels throughout duration of missions to assess intangible bone loss and remodeling.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
(1) Real-time health monitoring. Development of the rHEALTH allows monitoring of health status in real-time at the bedside or doctor's office. (2) Real-time intervention. Clinical intervention can be accomplished rapidly in acute situations with a handheld monitor. (3) Measurement of daily hematocrit for patients on coumadin or other anti-coagulation to diagnose early blood loss. (4) Detection of acute myocardial damage rapidly and outside the hospital so that life-saving therapy can be administered for heart attack patients. (5) Monitoring resolution of a patient's infection by tracking white blood cell counts throughout a prolonged antibiotic course. (6) Monitoring daily renal function of patients with kidney transplants or those with end-stage renal disease. (7) Measurement of athletes volume status during prolonged training for early diagnosis and dehydration. (8) Daily monitoring of electrolyte status for those individuals taking diuretics. Frequently, diuretics such as furosemide may cause hypokalemia and need to have their daily electrolyte status assessed.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support
Biomolecular Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Design Interactive, Inc.
1221 E. Broadway, Suite 110
Oviedo, FL 32765-7829

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ali Ph.D.
ali@designinteractive.net
1221 East Broadway, Ste. 110
Oviedo,  FL 32765-7829

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cog-Gauge is a portable hand-held game that can be used by astronauts and crew members during space exploration missions to assess their cognitive workload decrements that possibly result from fatigue, stress, or neurocognitive deficits. Cog-Gauge combines behavioral workload assessment using a dual-task approach with predictive workload models to counter the effects of game learning. The game will be built using an iterative usability driven approach where emphasis will be placed on building an engaging relevant game that builds from contextual task analysis and user profiling. The specific technical challenges foreseen are integrating two a