NASA 2005 STTR STTR Phase 1 and 2 Solicitation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Redefine Technologies
44 Linn Lane
Golden, CO 80403-9708

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
The Regents of the University of Colorado
UCB 572, 3100 Marine Street, Room 481
Boulder, CO 80309-0572

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steven Wichman
steve@redefine.com
44 Linn Lane
Golden,  CO 80403-9708

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Redefine Technologies, along with researchers at the University of Colorado, will use three redundancy methods to decrease the susceptibility of a spacecraft, on a mission survivability level, to electronic failures anywhere throughout the spacecraft. By using Field Programmable Gate Array (FPGA) chips, we will analyze the spacecraft-wide benefits of: *triplicating the logic and RAM on-board each subsystem using a Xilinx proprietary Triple Modular Redundancy (TMR) tool; *triplicating the persistent memory storage (i.e. ROM, science data, and flight code) on-board each subsystem using various methods specific for the space environment; and, *triplicating the backup architecture itself, while reducing weight and volume requirements, so subsystem code can run on alternate processors if any component is rendered inoperable due to an electronic failure (radiation, manufacturing, human-error, etc). These three methods of triplication should significantly increase the reliability of non-radiation hardened designs, which should allow commercial off-the-shelf (COTS) processing components to be used as flight critical hardware. The analysis that is performed will predict the total benefit of this approach to any future spacecraft.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The benefit to NASA for funding this research is an increased mission survivability level for all its spacecraft. By integrating redundancy on multiple levels throughout the spacecraft, mission critical functions can be migrated around to make the most efficient use of the resources available and to avoid damaged resources. Interplanetary missions to support putting humans on the Moon and Mars will become more flexible and responsive (i.e. quicker to develop) than ever before. The faster, better, cheaper strategy will become more feasible. While radiation tolerant devices will maintain an essential role in spacecraft design, having the cheaper and more state-of-the-art options of COTS products available and using this research to make them more palatable to the industry, will decrease satellite turn-around time in terms of the testing and specialized design knowledge required. In addition, more University satellites will be taught to use this COTS technology because it's already in their schools through the Xilinx University Program (which is available to all higher-learning institutions). These students are NASA's future workforce and moving NASA's component selection closer to COTS aligns well with the students' education and will ease the transition into their future NASA careers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Redefine Technologies will closely investigate the patentability of all claims related to this research. The code distribution methods under consideration are marketable, either as an off-the-shelf product that can be sold to spacecraft system manufacturers or as services provided by Redefine Technologies in its normal consulting business. As mentioned earlier, the Spacecraft Benchmark Software Code (SBSC) will be made available on the Redefine Technologies' website for all to use and compare designs against. This standalone product of the Phase I research will follow the same business philosophy as personal computer benchmark tests or products under the GNU Public License. This code set will be improved upon over time and used industry-wide as a standardized test platform. It will solidify the redundancy technology proposed here, create healthy competition that will result in better and better products, and it will further standardize spacecraft design.

TECHNOLOGY TAXONOMY MAPPING
On-Board Computing and Data Management
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Highly-Reconfigurable
Radiation-Hard/Resistant Electronics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Kestrel Technology LLC
3260 Hillview Ave.
Palo Alto, CA 94304-1201

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Jet Propulsion Laboratory
4800 Oak Grove Dr., MS 301-270
Pasadena, CA 91109-8001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Allen Goldberg
goldberg@kestreltechnology.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary focus of Integrated Vehicle Health Management (IVHM) has been on faults due to hardware failures. Yet software is growing in complexity, controls critical functionality under a wide range of conditions and does so with greater autonomy. Furthermore, software errors have negatively impacted major missions. Runtime recovery from software faults is gaining momentum in research community with major efforts such as the IBM autonomic computing effort and the Stanford/Berkeley Recovery-Oriented Computing project. We propose application of these methods to flight software in the context of JPL's Mission Data System (MDS), an integrated systems and software architecture for next-generation space missions. Specifically, we consider: ? Detection and repair of radiation induced Single Event Upsets (SEU) that can either change data values or code. ? Recovery from bugs manifested as the use of computational resources outside of a specified mode-dependent resource profile. ? Software organization and infrastructure to help diagnose and limit the impact of errors. We shall study how to restructure MDS as a distributed system with redundant hierarchical components. ? A recovery strategy based on component-level rebooting. This STTR is a cooperative project between the small business Kestrel Technology and NASA's Jet Propulsion Laboratory (JPL).

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This technology is relevant to all NASA mission- and safety-critical flight software. The technology will not be specific to MDS. It can improve margins of safety for all critical software.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology is relevant to all safety-critical embedded control systems, now commonly found in automobiles, airplanes, other transportation systems, power plants, etc.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Pirouette Software Consulting
1030 N. State St., Suite 40C
Chicago, IL 60610-2812

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Board of Trustees, University of Illinois at Chicago
MB 502, M/C 551, 809 South Marshfield Avenue
Chicago, IL 60612-7205

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ouri Wolfson
ouriwolfson@ameritech.net
1030 N. State St., Suite 40C
Chicago,  IL 60610-2812

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Information Technology (IT) is a key element in the successful achievement of NASA's strategic goals. Modern IT tools and techniques have the capability to redefine many design and operational processes as well as enable grand exploration and science investigations. This proposal plans to address NASA's needs for innovative communication concepts for autonomous systems that require local information dissemination among mobile entities. We will explore a peer-to-peer paradigm for local dissemination of information among surface-based assets that are in geographic proximity. In this paradigm, a set of mobile objects (astronauts, rovers, robots, sensors, etc.) form a Mobile Ad-hoc NETwork (MANET), and they communicate with each other via short-range wireless technologies such as IEEE 802.11 and Bluetooth. We propose to develop a novel software toolkit that enables efficient local information dissemination applications in such an environment. The heart of this toolkit is a distributed peer-to-peer (P2P) algorithm that disseminates information intelligently based on the semantics of the information. This algorithm does not rely on any infrastructure, central server, or routing data structures, and therefore provides a higher survivability of the network than the traditional data dissemination techniques.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's exploration of planetary surfaces will require dissemination of local information by surface-based assets, including base stations, astronauts, habitats, rovers, and robots. For example, a rover monitors the operation of a robot in proximity and be warned when the robot is moving in a wrong direction or is about to lose its capability; a base station needs to receive the notification about a malfunctioning rover, possibly generated by the vehicle health monitoring system; astronauts in proximity need to monitor each other and be aware of who is where, who is contacting whom, who has what capabilities; and so on. In these applications, the local resources that are of interest to mobile users are often only available during a limited period of time and these resources themselves may be mobile. For example, a malfunctioning robot may be moving and it is available only until it completely loses capability. Similarly, the current location of an astronaut, and the current temperature in a particular geographic area, are temporarily valid or available resources. MOBI-DIC provides surface-based mobile assets with an efficient information dissemination tool. MOBI-DIC will be embedded within a hardware device attached to mobile objects such as astronauts, robots, rovers, and sensors, and it will enable quick building of information dissemination services needed in NASA's exploration of planetary surfaces.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
MOBI-DIC will enable quick building of matchmaking or resource discovery services in many application domains including social networks, transportation, mobile electronic commerce, emergency response, and homeland security. For example, in a large professional, political, or social gathering, the technology is useful to automatically facilitate a face-to-face meeting based on matching profiles. In transportation, MOBI-DIC incorporated in navigational devices can be used to disseminate to other similarly-equipped vehicles information about relevant resources such as free parking slots, traffic jams and slowdowns, available taxicabs, and ride sharing opportunities. In mobile electronic commerce, MOBI-DIC is useful to match buyers and sellers in a mall, or to disseminate information about a marketed product. In emergency response, MOBI-DIC can be used by first responders to support rescue efforts even when the fixed infrastructure is inoperative; it will match specific needs with expertise (e.g. burn victim and dermatologist), and help locate victims. In homeland security, sensors mounted on neighbouring containers can communicate and transitively relay alerts to remote check-points.

TECHNOLOGY TAXONOMY MAPPING
Teleoperation
Telemetry, Tracking and Control
On-Board Computing and Data Management
Architectures and Networks
Autonomous Control and Monitoring
RF
Data Acquisition and End-to-End-Management
Database Development and Interfacing
Portable Data Acquisition or Analysis Tools
Sensor Webs/Distributed Sensors
Power Management and Distribution
Wireless Distribution

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cleveland BioLabs, Inc.
11000 Cedar Avenue, Suite 290
Cleveland, OH 44106-3052

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Cleveland Clinic Foundation
9500 Euclid Avenue
Cleveland, OH 44195-0001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Pavel Komarov
pkomarov@cbiolabs.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this proposal is to explore a novel proprietary biopharmaceutical agent, named deltaFL-AA', a first in the series of innovative radioprotectors to act as an agent providing protection of the organism against major space radiation risks. These risks include organism death resulting from acute irradiation as well as radiation-induced carcinogenesis caused by low-dose exposure. An unprecedented radioprotective potency of deltaFL-AA' demonstrated by its ability to cure 100% of mice from supralethal (14 Gy) doses of gamma-irradiation and its strong immunostimulatory properties (especially the ability to trigger natural killer response, which is well established as one of the antitumor firewalls) make this drug an extremely attractive candidate for testing in a NASA-funded program.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
deltaFL-AA' and related inhibitors of cell death will be useful in the protection of human organisms from damage caused by both acute high-level and chronic low-level irradiation during space flights.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The projected market for the new class of inhibitors of cell death in the biopharmaceutical industry is broader than radioprotection associated with the specifics of space flights. Our data demonstrates that deltaFL-AA' is extremely potent in curing mammals from supralethal, single doses of gamma-irradiation, thus making it a candidate radioprotector for biodefense needs. These same properties also position the drug on the civilian radioprotectors market as a radiation antidote in the case of nuclear accidents. Another, not less important, civilian application is cancer treatment, where the administration of deltaFL-AA' may increase the efficacy of chemo- and radiotherapy enabling dose escalation by protecting normal tissues from the side effects of anti-tumor therapy. Additional, othert unexplored uses include other life-threatening injuries that involve massive cell death or require immunostimulation.

TECHNOLOGY TAXONOMY MAPPING
Biomedical and Life Support

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Stirling Dynamics, Inc.
4030 Lake Washington Blvd NE, Suite 205
Kirkland, WA 98033-7870

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Washington
P.O. Box 352400
Seattle, WA 98195-2400

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Stirling
rstirling@stirling-dynamics.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Stirling Dynamics Inc and the University of Washington propose to develop a MATLAB toolbox for rapid aeroelastic (AE) and aeroservoelastic (ASE) modeling, analysis and optimization of flight vehicles. In practically all current aeroelastic analysis/optimization codes, model generation takes a considerable amount of effort, as does the processing of results. The proposed AE/ASE toolbox will provide user-friendly, mostly GUI-driven capabilities for rapid pre- and post-processing that will considerably decrease model generation effort and analysis/sensitivity cycle time compared to currently available tools. ASE toolbox users will have access to customizable databases containing organizational knowledge and standards for flight vehicle material properties, construction details, actuator/sensor models, airfoil shapes, etc. Model construction will be fully automated, eliminating time-consuming manual pre-processing. A full-range of ASE analyses and design sensitivities will be available within the MATLAB/Simulink environment. Utilities will be developed for importing and exporting computational model data (FEM, CFD, DLM, etc.) and results to and from the major commercial analysis codes. Key innovations include: 1) rapid model development, analysis, and optimization; 2) integration with the widespread and highly accessible MATLAB/Simulink computational environment; and 3) connectivity from MATLAB to more general purpose codes such as NASTRAN for higher fidelity follow-on analyses and model refinement.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Direct application of the STTR results to issues of current interest to NASA represents a prime opportunity where continued involvement in further product development and enhancement represents a considerable potential revenue stream in engineering support and future software sales. There are several avenues of potential commercial exploitation within NASA that include: 1) Engineering support and consulting work in future advanced vehicle projects, 2) Designs to meet specific performance requirements, 3) Interfacing of the software code with other aerospace vehicle design procedures, 4) Licensing of the software code, 5) Methods and software code development for advanced concept evolutions. The various divisions of NASA are engaged in many design, test and evaluation programs, ranging from general aviation aircraft to hypersonic waverider vehicles. All of these projects require increasingly sophisticated analysis tools and are potential customers for the proposed software capability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Components of the Department of Defense will have strong interest in the technology developed in this STTR project, such as the USAF, US Navy and DARPA, and those dealing with ballistic missile defense and guided missiles. Commercial and military aircraft manufacturers worldwide represent further major sales prospects, with applications in preliminary design cycles and in the need to achieve low structural weight. Several aircraft companies have plans to design vehicles for low cost access to space and will need advanced software tools in the design process to meet performance objectives. From their very nature, advanced vehicle designs with light weight structure are likely to encounter problems with vibration and dynamic loads response due to aeroelastic characteristics. The proposed aeroelastic/aeroservoelastic optimization methods will offer a very useful design tool for these applications, which will provide additional research, development and product sales opportunities arising from the STTR project.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Controls-Structures Interaction (CSI)
Launch and Flight Vehicle
Simulation Modeling Environment
Structural Modeling and Tools
Software Development Environments
Software Tools for Distributed Analysis and Simulation
Manned-Manuvering Units

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tao of Systems Integration, Inc.
144 Research Drive
Hampton, VA 23666-1325

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Florida
P.O. Box 116250, 231 Aerospace Building
Gainesville, FL 32611-6250

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Siva Mangalam
siva@taosystem.com
144 Research Drive
Hampton,  VA 23666-1325

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An Integrated Sensing and Control of Aeroelastic Deformation (ISCAD) Toolbox is proposed. Specif-ically, this toolbox will provide a methodology, both hardware and software, that serves to compensate for uncommanded de?ections of ?ight systems. This toolbox is meant to augment existing procedures for design of both aircraft and autopilots by providing additional capabilities that address aspects unique to for aeroelastic control. The sensors are provided by the ?ow and loads measuring systems pioneered by Tao Systems while the control synthesis builds upon expertise at the University of Florida in ?exible -wing aeroelasticity. The approach integrates state--of--the -art sensing capability with advanced control synthesis systems. In this way, a collaborative partnership is formed that is ideally suited to develop the ISCAD Toolbox.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced aerospace vehicles and system components tend to be slim and elastic, resulting in severe aeroser-voelastic problems at high speeds, which require attention in both design and routine performance for safety and ride quality. The proposed innovation has signi?cant potential applications for both NASA and the aerospace industry (commercial and military): Fixed wing aircraft, Rotary wing aircraft, Turbo-machinery, planetary-exploration vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In non--aerospace applications, the proposed innovation will be of value for the health monitoring of tall structures (skyscrapers, suspension bridges, chimneys and cooling towers), sails, keel, rudder, and control surfaces of sailboats (particularly racing sailboats), ship masts and tall ship deck structures, submarine and its subsystems (e.g., control surfaces and propulsor)

TECHNOLOGY TAXONOMY MAPPING
Controls-Structures Interaction (CSI)
Telemetry, Tracking and Control
Attitude Determination and Control
Guidance, Navigation, and Control
Pilot Support Systems
Sensor Webs/Distributed Sensors

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Virginia
PO Box 400195
Charlottesville, VA 22904-4257

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Burkholder
burkholder@bainet.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The increased aircraft safety potential of active flow control using synthetic jets - specifically, using synthetic jets on the leading edge of the wing to delay flow separation - is of critical importance. Delaying flow separation could allow an aircraft to recover from adverse conditions that would otherwise result in a loss of control. Active flow control using synthetic jet actuators has been the subject of significant research in recent years due to its immense potential to expand the operating regimes of unconventional airfoils and provide "virtual" shaping. Barron Associates (BAI) and its research partners at the University of Virginia and the University of Wyoming propose innovative active flow control solutions that will allow achieve virtual sur-face shaping objectives and delay flow separation at high angles of attack to provide a safer and more efficient flight environment. The proposed integrated actuation and control systems will be demonstrated using a Boeing 747 flight simulation. In Phase II, the team will: (1) implement the control algorithms in real time in hardware; (2) fabricate a Boeing 747-like scale model with integrated synthetic jet actuators, and; (3) demonstrate the actuation capacity and control algorithm performance for achieving desired flow control objectives.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research effort clearly offers the potential for a significant leap in vehicle performance, operation, safety, cost, and capability. The technology will require a demonstration in an actual-flight environment to fully characterize and validate the performance that is predicted in simulation and demonstrated in wind tunnel experiments. The research is particularly relevant to NASA's Intelligent Flight Control System (IFCS), which has the objective of enabling a pilot to land an aircraft that has suffered a major systems failure or combat damage, and also to the Single Aircraft Accident Prevention thrust of the Aviation Safety Program in which BAI has participated for a number of years.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Adaptive active flow control methods could enable significant advances for numerous aerospace systems, including military fixed-wing aircraft, unmanned air vehicles, projectiles, and commercial and general aviation aircraft. The vast array of corporations and federally-funded entities currently engaged in active flow control research creates the potential for a large contract R&D market. Furthermore, active flow control technology provides a natural complement to other advanced intelligent vehicle control products already under development at BAI. The most direct commercialization route is via collaboration with the major airframers. Fortunately, BAI has strong, existing working relationships with these companies. As parallel research advances at the major aerospace companies, BAI will pursue commercialization and collaboration opportunities. Although it is difficult to predict the rate of advancement of the ongoing research activities upon which future com-mercialization may depend, even a relatively small market can play a significant role in our growth as a company.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Migma Systems, Inc.
1600 Providence Highway
Walpole, MA 02081-2553

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Louisiana State University
Department of Mechanical Engineering
Baton Rouge, LA 70803-6413

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bo Ling
bling@migmasys.com
1600 Providence Highway
Walpole,  MA 02081-2553

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The investigation of the coating friction as a function of time is important to monitor the ball bearing heath. Despite the importance of the subject mater, there is a crucial lack of information in the literature about coating life and friction force in ball bearings as coating wear of progressively increases. Here we propose to develop a strategic space vehicle health monitoring system that will identify potential and/or imminent lubrication problems, analyze these parameters in real time, and provide direct input so that these problems are mitigated prior to failure. We will set up a lab experiment environment with a universal microtribometer and acoustic emission sensors measuring the signals associated with wear and the changes that tend to occur as a function of time. Friction force and acoustic signal will be measured with respect to the bearing condition. To capture the dynamic nature of friction evolution, we propose to extract the temporal transient features from the sensing data and develop Hidden Markov Models with four distinct states associated with four operation conditions of the ball bearing. Our system uniquely combine both physics-based and stochastic models for the online diagnosis.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate benefits for NASA will be the reliable operation of many precision machinery used in tracking systems satellites, telescopes and other space instruments require very stringent position accuracy ? in the range of microns. Our system will make it possible for these enormously expensive systems to operate reliably with little or no maintenance and long service-life duration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Process industry represents a major industrial segment, including oil refinery, gas, metals & mining, food processing, pulp & paper, power, pharmaceutical, etc. Our core technologies can be used in the process industry where thousands of instruments are placed in the field. These instruments are either connected in a local network or connected to the central control room. For example, our component health monitoring system can be used to monitor and perform real-time diagnosis for the process systems where instruments and control equipment are placed across the entire plant. Our system can help the plant operators avoid unnecessary costly shutdowns.

TECHNOLOGY TAXONOMY MAPPING
Autonomous Reasoning/Artificial Intelligence
Data Acquisition and End-to-End-Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Invocon, Inc.
19221 I-45 South, Suite 530
Conroe, TX 77385-8746

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Colorado
572 UCB
Boulder, CO 80309-0572

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kevin Gifford
gifford@rintintin.colorado.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Integrated Data Assimilation Architecture (IDAA) is a middleware architecture that facilitates the incorporation of heterogeneous sensing and control devices into a unifying system with standardized application interfaces. The architecture is standards-based (IEEE wireless standards) and is an open architecture that can be easily extended. This system is innovative from several perspectives: (1) the design explicitly supports multiple disparate devices ? to date, wireless middlewares have focused on single device types or single network types; (2) independent development is explicitly supported by means of a published application programmer interface (API) along with system client libraries that provide standard services; and (3) a Development Kit ("DevKit") that includes working examples and source code templates is provided to assist developers in the integration of a new monitoring device and/or the composition of a new application that is a consumer of the data produced by the system. The proposed system will support the T3.01 Aerospace Communications topic by delivering a hybrid architecture that by design can incorporate multiple heterogeneous wireless devices and networks. Additionally, the IDAA system provides for multi-developer system extensibility, alleviating the problem of a monopolistic single-vendor implementation, where only the original developer of the middleware can efficiently extend the system functionality.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential near-term NASA applications of the proposed architecture include vehicle health monitoring of the Shuttle and CEV, structural and environmental monitoring in and around the International Space Station (ISS), and crew medical monitoring. As part of the Exploration Directorate, proximity networks could easily be deployed on the Moon and Mars, with inherent interoperability and coexistence capabilities even when provided by multiple sources. Such networks could include imagery collection, crew communication, remote sensing nodes for scientific applications, robotic command and control, and environmental and safety monitoring of crew habitats.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of a wireless networking capability for use by NASA on the ISS and for Exploration missions has significant application to commercial terrestrial markets, including homeland security, environmental monitoring, medical instrumentation and the healthcare industry, chemical and biological sensors, and security monitoring. Wiring of sensors within buildings can cost anywhere from $50-$100 per square foot. Overall, wireless sensor networks are a commercial market that is in the early phases of growth. As technology capabilities become user-friendly and less cost prohibitive, and businesses begin to understand the benefits of wireless communication, it is positioned to become a rapid growth market.

TECHNOLOGY TAXONOMY MAPPING
Architectures and Networks
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Anvik Corp
6 Skyline Drive
Hawthorne, NY 10532-2165

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Illinois at Urbana-Champaign
109 Coble Hall, 801 S. Wright Street
Champaign, IL 61820-6242

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Marc Klosner
mklosner@anvik.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Reconfigurable antennas are attractive for remote sensing, surveillance and communications, since they enable changes in operating frequency and / or radiation pattern, resulting in high-bandwidth antenna systems, with broad areas of coverage. Additional functionality would be achieved by integrating: control, processing, and communications directly onto the antenna substrate; MEMS sensors into the antenna substrate to monitor the system health; and opto-electronic beam forming networks, providing immunity to electromagnetic interference. In order to make such systems affordable for space exploration, it is critical to minimize the cost of transporting them into space. For this reason, antennas fabricated on flexible substrates are highly desirable since they can be rolled up and launched in a low-volume configuration, then inflated in space. While these advantages are significant, the fabrication of antennas providing these features is challenging due to the lack of manufacturing technologies that can meet all of the processing requirements for fabrication on flexible substrates. In this program we will develop antenna designs and lithography-based processes, enabling manufacturing processes that cannot be carried out using existing patterning technologies, in particular: laser-crystallization, allowing for the integration of ICs; and a combination of processes to produce MEMS for on-board sensors and for reconfiguring the array.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed program will lead to highly-integrated flexible antenna systems, featuring sensors, processors, and command and communications systems. Additionally, the antenna will feature highly directional gain patterns as well as reconfigurability, to cover a large bandwidth and a wide range of scan angles. These antennas will be lightweight and, since they are flexible, they can be "collapsed" into a small volume for launch into space, and then "inflated" at the destination site. This highly integrated systems-on-flex program would also have applications in other areas of interest to NASA, such as integrated sensor skins, and solar sails / gossamer spacecraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The highly-integrated systems-on-flex technology developed in this program can be used for fabricating mobile electronics, where a high level of integration on lightweight, flexible substrates is critical. There are also commercial applications in other large consumer market segments such as flat-panel displays, where portable wall-sized displays that can roll-up are the long-term goal of the industry; and in commerce, particularly in the areas of electronic labels and RFID tags.

TECHNOLOGY TAXONOMY MAPPING
Large Antennas and Telescopes
RF
Sensor Webs/Distributed Sensors
Highly-Reconfigurable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Phoenix Nuclear Labs
301 N. Whitney Way
Madison, WI 53705-2722

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Wisconsin-Madison
301 N. Whitney Way
Madison, WI 53706-1609

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Noah Hershkowitz
hershkowitz@engr.wisc.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A device to produce electron beams from magnetized plasma created with rf fields combined with electron extraction by electron sheaths is proposed. The source can provide electrons for neutralizing positive ion beams emerging from ion thrusters or as a generic electron source. With hollow cathode sources currently employed to provide neutralizing electrons, operation is limited in time and/or current density by cathode deterioration. RF electron sources provide an alternative approach that does not consume electrode material. The current from this Non-ambipolar Electron Source (NES) exceeds the current normally extracted from conventional rf plasma sources by a factor of (mi/me)1/2 where mi and me are the ion and electron mass. Ions are lost to a negatively biased conducting cylinder with area Ai chosen to be Ai ≥ (mi/me)1/2 *Ae where Ae is the electron extraction area. Slots in the conducting cylinder allow the cylinder to serve as a Faraday shield to reduce capacitive coupling from the antenna to the plasma. Proposed phase 1 design improvements should result in electron currents comparable to hollow cathode sources with lower neutral gas flow in the inductive discharge phase and higher currents with helicon operation. Phase 2 will develop prototype sources suitable for spacecraft testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Due to the absence of electron emitting surfaces, the NES design allows for longer operational lifetimes and lower gas consumption compared to hollow cathodes used on solar-powered spacecraft and satellites which use electric propulsion for orbital maneuvers and station keeping. This technology will serve NASA by creating a new generation of electron neutralizers which will be able to function with decreased energy and fuel consumption causing a reduction in launch and operational costs. This concept is consistent with NASA's new vision for reliable, long-life, high current neutralizers that will be necessary for the successful completion of missions in Earth orbit, and to the moon, Mars and beyond. Other terrestrial NASA applications that would benefit from the replacement of hollow cathodes include: producing protective thermal spacecraft coatings, plasma assisted thin film formation, and optical coating deposition for large telescopic mirrors.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are currently 100's of commercial satellites in earth orbit that use electric propulsion technologies for daily station keeping and orbital maneuvers. All of these systems are limited in operational lifetime by hollow cathode deterioration and fuel consumption. NES technology has the promise of extending lifetime while reducing the fuel consumption of ion neutralizers. The U.S. military, Boeing, L3 Comm, Pratt & Whitney, Aerojet, and other large aerospace programs would directly benefit from this technology as it would extend the operational lifetime of their satellites. A very large non-NASA market exists for hollow cathode sources over a wide range of industrial applications that could be upgraded by NES technology. These include electron beam evaporation, electron beam surface modification, thin film growth, plasma assisted chemical vapor deposition, plasma vapor deposition, electron beam curing, waste handling, metallizing packaging films, electron beam reactive deposition, and more.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Fundamental Propulsion Physics
MHD
Particle and Fields
Thermal Insulating Materials
Electrostatic Thrusters
Sterilization/Pathogen and Microbial Control
Ceramics
Composites
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ENTECH, Inc.
1077 Chisolm Trail
Keller, TX 76248-7000

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Auburn University
231 Leach Center
Auburn University, AL 36849-5320

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark O'Neill
mjoneill@entechsolar.com
1077 Chisolm Trail
Keller,  TX 76248-7000

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Over the past six years, ENTECH, Auburn, NASA, and other organizations have developed a new space photovoltaic array called the Stretched Lens Array (SLA), which offers unprecedented performance (e.g., >80 kW/cu.m. stowed power, >300 W/sq.m. areal power, and >300 W/kg specific power in the very near term) and cost-effectiveness (>75% savings in $/W compared to planar high-efficiency arrays). SLA achieves these outstanding attributes by employing flexible Fresnel lenses for optical concentration (e.g., 8X), thereby minimizing solar cell area, mass, and cost. SLA's small cell size (85% less cell area than planar high-efficiency arrays) also allows super-insulation and super-shielding of the solar cells to enable high-voltage operation and radiation hardness in the space environment. Recent studies show that SLA offers a 3-4X advantage over competing arrays in specific power for many NASA Exploration missions. ENTECH and Auburn, with Aerojet support, propose to develop and demonstrate a special version of SLA, specifically optimized for Solar Electric Propulsion (SEP) missions. This SLA for SEP will operate at 600 V to direct-drive an Aerojet Hall-effect electric thruster. Such a combination of an ultra-light, high-voltage, radiation-hard SLA with a high-specific-impulse electric thruster will have widespread applicability to many NASA, DOD, and commercial missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The 600 V Stretched Lens Array (SLA) for Solar Electric Propulsion (SEP) technology proposed under this STTR program will have major applications for near-term and far-term NASA Exploration Missions. One major NASA application is SLA for SEP technology applied to reusable cargo tugs, both for near-term robotic and human missions to the moon, and also for longer term missions to Mars and beyond. One reusable cargo tug using SLA for SEP technology can save NASA over $3 Billion in launch costs alone, compared to conventional chemical propulsion delivery of 110 metric tons of cargo to the lunar surface over a five year period. Other NASA applications of SLA for SEP technology include efficient orbit raising or lowering of spacecraft for science missions in orbit about the earth, moon, planets, or asteroids, and large-scale deep space science missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The 600 V Stretched Lens Array (SLA) for Solar Electric Propulsion (SEP) technology proposed under this STTR program will also have major applications for near-term and far-term DOD and commercial space missions. For DOD missions, SLA for SEP technology could be applied to efficient repositioning of space assets for specific missions. For commercial missions, SLA for SEP technology could be applied to efficient orbit raising of communication satellites from low earth orbit (LEO) or geostationary transfer orbit (GTO) to geostationary orbit (GEO). Over the longer term, transportation of cargo in support of commercial exploitation of space resources and the advent of space tourism could be most efficiently and cost effectively done using SLA for SEP technology.

TECHNOLOGY TAXONOMY MAPPING
Electromagnetic Thrusters
Micro Thrusters
Solar
Kinematic-Deployable
Simulation Modeling Environment
Testing Facilities
Testing Requirements and Architectures
Cooling
Electrostatic Thrusters
Radiation-Hard/Resistant Electronics
Optical & Photonic Materials
Radiation Shielding Materials
Semi-Conductors/Solid State Device Materials
Photovoltaic Conversion
Power Management and Distribution
Renewable Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Powder Solutions
10010 Cucklebur
Houston, TX 77095-6964

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Northwestern University
633 Clark Street 2-545
Evanston, IL 60208-2900

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dean Baker
stbaker2000@cs.com
10010 cucklebur
Houston,  CA 77095-6964

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed STTR is the combination of a small business with unique materials experience, and Northwestern Unviersity, with expertise in Mirror applications, processing and characterization. The combination of these two entities with various prime contractors providing assistance makes for a successful STTR program. The applications for these materials have significant impact on NASA and other commercial entities. The unique materials being demonstrated under this program also have significant commercial applications. A successful Phase I will result in the identification of various parts and programs that can be supported by these materials. Phase II will focus on characterization and qualification of these materials.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Light weight materials play a major role in many applications from mirrors, to electronics to secondary structure. Possible mirror applications include IR, NIR and LIDAR with various prime contractors. Since weight is critical a material 30% lighter than Be (also lighter the Gr/Epoxy) and stiffer than Al has many applications due to its weight advantage.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Light weight matarials such as these can be used in computers, cell phones, electronics, automotive and many other applications to name a few.

TECHNOLOGY TAXONOMY MAPPING
Erectable
Large Antennas and Telescopes
Thermal Insulating Materials
Optical
Highly-Reconfigurable
Composites
Metallics
Optical & Photonic Materials
Radiation Shielding Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Decisive Analytics Corporation
1235 South Clark Street, Suite 400
Arlington, VA 22202-4361

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Louisiana State University
Office of Sponsored Programs, 330 Thomas Boyd Hall
Baton Rouge, LA 70803-0001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Fiske
david.fiske@dac.us

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We will design and implement an interface between the Paramesh computational libraries, developed and used by groups at NASA GSFC, and the Cactus computational framework, developed primarily by scientists at Louisiana State University, the RI on this proposal. Our innovation falls in the domain of adaptive mesh refinement (AMR), a technique to focus computational resources in regions of small scale dynamics. Our approach is innovative as it brings together one of the leading AMR packages (Paramesh) with Cactus, a widely used modular, parallel problem solving environment that is supported on multiple computing architectures. Our innovative proposal responds specifically the to the "Computing" subtopic in the solicitation in three areas: It will (1) reduce costs for current Paramesh users at Goddard, by providing access to the wide variety of validated tools already available through Cactus and which would otherwise need to be redeveloped at NASA; (2) facilitate sharing of novel algorithms between Paramesh and Cactus users worldwide through the existing and proven interoperability features provided by Cactus; and (3) position Paramesh users to benefit from the many next-generation computer science innovations that are actively researched by the core Cactus development team (such as grid computing) and other Cactus contributors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In Phase 3, we would continue the work started in Phases 1 and 2 by offering consulting services to existing Paramesh users, government and private sector, who wish to convert to Cactus via the interface developed under this proposal. We will also investigate the possibility of charging a licensing fee for commercial users of the Paramesh driver thorns developed under this proposal. Building the interface proposed here will also play an important role in DAC's long-term commercialization strategy in combination with similar products developed under outside funding. DAC has allocated internal investment dollars for developing tools and marketing consulting services based on an internally developed, Paramesh-based computational fluid dynamics code. The PI for this effort, Dr. David Fiske, is actively pursing specific opportunities with the Rotorcraft Dynamics group run jointly by the U.S. Army and NASA Ames Research Center. Our approach to this industry already uses Paramesh, so by integrating this with Cactus, we will also enjoy all of the benefits that NASA end-users will enjoy after Phases 1 and 2. This combination will provide DAC with a competitive advantage in this market, since we will be able to leverage open source tools provide through Cactus with proprietary tools developed in-house.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We will combine the results of this effort with an existing effort to develop a CFD code. Customers for the results of this combined effort will be the big 3 rotorcraft manufacturers; Bell-Textron, Boeing, and Sikorsky for the design of the next generation of military rotorcraft. The ability to do accurate vorticity modeling will grant greater understanding of the capabilities of current platforms, as well as aid in the design of rotor geometries to meet the future goals for rotorcraft. The ONR S&T Division has also identified "Computational Mechanics" as a core area for basic research, and there will be cross-over in the hydrodynamic issues that arise for helicopters and naval vessels. Another application where results of this effort would be useful is in the analysis of river currents. Vortex systems are sometimes created around pillars, for example, and can lead to the shifting of sediment at the base of the pillar. The increased understanding of how these flows behave will allow for the better design structural pillars. A similar application is a priority of the U.S. Geological Survey and the State of Louisiana. In Louisiana the Mississippi Delta Tidal Basin has lost 70% of its land mass since 1932, and the State has made it a priority to study preventive measures. Numerical models of the hydrodynamics of the Basin will be important in solving this problem. We will explore partnerships with companies that provide consulting services in these applications.

TECHNOLOGY TAXONOMY MAPPING
Software Development Environments
Software Tools for Distributed Analysis and Simulation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
III-N Technology, Inc.
2601 Anderson Ave, Suite 102
Manhattan, KS 66502-2809

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Kansas State University
2 Fairchild Hall, KSU
Manhattan, KS 66506-1103

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jing Li
3n@3n-tech.com
2033 Plymouth Road
Manhattan,  KS 66503-7542

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase I project is to investigate the feasibility for achieving EUV detectors for space applications by exploiting the ultrahigh bandgap semiconductor - AlN. We plan to devise methods to improve the AlN epitaxial material quality and device structures for EUV detectors. Specifically, we will study the properties of Si and Mg doped AlN epilayers and investigate n- and p-type doping issues in AlN and hence the feasibility for achieving high performance EUV detectors; improve the AlN material quality by exploiting novel template/substrates and growth schemes to reduce the dislocation and native defect density. Use knowledge gained from these investigations to provide new understanding of the III-nitride system and to improve EUV detector structural design. It is intended that EUV detector wafers will also be delivered to NASA scientists for the fabrication of detector arrays. Improved performances of AlN based EUV detectors over conventional existing technologies are expected.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The UV range supplies a richness experimental data which is unmatched by any other domain for the study of hotter objects in the universe because it samples molecular, neutral and atomic gas at temperatures ranging from 10 to 105 K. The performance of UV detectors has steadily improved over the last decades in many respects, and astronomical applications benefit from this evolution. Nevertheless, current detectors designed for UV, especially for extreme UV (EUV) observations (ranging approximately from 5 nm to 200 nm), are based on Si semiconductors and exhibit a few major drawbacks that are difficult to overcome within silicon technology. For space applications, the ideal EUV detector is the one that is visible blind, reliable, high resistant to radiation damage, high efficiency, lightweight, minimal power consumption, and can operate at room temperature. AlN based wide bandgap semiconductor materials hold very strong promise to satisfy these general requirements due to their inherent physical properties.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of AlN based EUV detectors will have broad applications in military, homeland security, and commercial sectors. For military applications, there is also a need for higher performance sensors that require less power and occupied smaller volume in the military systems; EUV sensors may be used on UAVs, sub-munitions, guided flairs and other guided and precision munitions. In the areas of homeland security, EUV sensors can be used for biothreat detections. For commercial applications, there exists a huge potential for miniaturized EUV sensors. The applications range from spectroscopy, medical applications to environmental monitoring. EUV detectors will have huge applications in the electronics industry because EUV photolithography will be used in the manufacture of next generation of semiconductors, integrated circuit components and printed circuit boards

TECHNOLOGY TAXONOMY MAPPING
Particle and Fields
Ultra-High Density/Low Power
Airport Infrastructure and Safety
On-Board Computing and Data Management
Laser
Optical
High-Energy
Photonics
Radiation-Hard/Resistant Electronics
Optical & Photonic Materials
Semi-Conductors/Solid State Device Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Atlas Scientific
1367 Camino Robles Way
San Jose, CA 95120-4925

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
San Francisco State University
1600 Holloway Avenue
San Francisco, CA 94132-1722

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ben Helvensteijn
bhelvensteijn@atlasscientific.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Microcalorimetry is an enabling technology for many NASA space science missions because it permits detection of single photons at high rates with unprecedented energy resolution and efficiency. This remarkable technology relies upon superconducting devices that must be cooled below 100 mK. We propose to construct a doubly-integrated circuit in which critical features of microcalorimeter pixels on micromachined thermal isolation structures are cooled by microscale refrigerators that exhaust heat into the substrate at 300 mK. In Phase 1 we will demonstrate a new process for fabricating suspended thermal isolation membranes that is planar and fully photolithographic. A parallel Phase 1 activity will be to design a self-contained "omni-orientable" sorption refrigerator as a 300 mK heat sink that can be started and operated in any orientation in order to facilitate retrofitting microcalorimeters to existing materials analysis systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications for Icy IC's is to produce spectrometers and imaging arrays for space science instrument. Microcalorimetry is an enabling technology for many NASA space science missions because it permits detection of single photons at high rates with unprecedented energy resolution and efficiency.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are two potential applications of integrating a microcalorimeter-based X-ray spectrometer in scanning electron microscopy (SEM) wafer metrology. As semiconductor device geometries continue to shrink, the defects that threaten yields become smaller. One solution is to use X-ray energy dispersive spectroscopy (EDS) with low electron beam voltage, which takes advantage of the small electron scattering range and thus the small volume in which X-rays are generated by the low-energy incoming electron beam. To analyze < 50 nm defects, acceleration voltages of < 3 kV are needed. However, in the low energy region of the X-ray spectrum, line overlap becomes a serious issue which makes clear distinction between different materials difficult. This problem can be overcome with superconducting detector technology which has very high energy resolution (< 20 eV) and thus the ability to separate X-ray lines of important material combinations. Microcalorimeter-based X-ray microanalysis technology can also be adapted to provide quantitative implant metrology for ultra-shallow junctions (USJs). A junction profile is typically measured by a spreading resistance probe or secondary ion mass spectroscopy. Both methods require special sample preparation and are destructive. An X-ray microanalysis system utilizing the superconducting detector technology can serve as an alternative method to obtain dopant profiles in the substrate with high spatial resolution and high precision.

TECHNOLOGY TAXONOMY MAPPING
Instrumentation
Sensor Webs/Distributed Sensors
High-Energy

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mide Techology Corporation
200 Boston Avenue, Suite 1000
Medford, MA 02155-4242

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Massachusetts Institute of Technology
77 Massachusetts Avenue
Cambridge, MA 02139-4307

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Marthinus van Schoor
tienie@mide.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Spacesuit systems for planetary EVAs must maximize human productivity and provide the astronaut with the capability to perform useful work tasks. Mide plans to work with MIT to develop mechanisms to augment astronaut productivity during advanced EVA missions. We propose to demonstrate the feasibility of using shape memory polymers (SMPs) to provide pressurizing life support in the Bio-Suit, an advanced EVA system based on mechanical counterpressure (MCP) that is being designed to provide a "second skin" biomechanically and cybernetically augmented human performance capacity for planetary exploration. SMPs are "smart" polymers whose pliability makes them comfortable to wear against the skin. However, their material properties and shape can also be controlled using external stimuli such as temperature, electricity or stress, making them particularly appropriate for use in a "second skin" spacesuit that adapts to the astronaut's shape changes during EVA movements. Our initiative would be the first-ever demonstration of the use of smart materials in an MCP spacesuit; as such, this innovation could potentially accelerate the development of space-rated MCP suits because it would provide both a means of increasing the pressure production and control whilst maintaining user comfort and usability ? competing requirements which have hindered development of previous MCP spacesuits.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Active materials such as SMP may soon revolutionize the clothing industry. SMP garments have the potential to provide a highly controllable pressure distribution and conform to the user's body with great comfort. As such, the innovations we propose to develop can be applied not only to advanced EVA systems, but also to applications where pressure and/or a conformal protective suits are required. Potentially this research could lead to live in spacesuits for non-EVA systems. Active suits could be designed for multi-purposes, conforming from everyday use to EVA missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In the medical sector pressure garments for burn victims, patients with varicose veins and other vascular diseases could be developed. In addition active tourniquets are another potential application for this research.Actively conforming protective suits for hazardous materials or hazardous environment operations. The SMP garments would conform or expand to best protect the wearer from hazards. A Fireman's suit could contract or expand due to high temperatures to maximize thermal insulation during a fire. Scuba suits with controllable dimensions. This would allow the diver to vary the space between garment and skin and thus the desired level of insulation.

TECHNOLOGY TAXONOMY MAPPING
Suits
Multifunctional/Smart Materials

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Agave BioSystems, Inc.
PO Box 80010
Austin, TX 78708-0010

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Universities Space Research Association
10211 Wincopin Circle, Suite 500
Columbia, MD 21044-3432

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joel Tabb
jtabb@agavebio.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
While the protective qualities of activated carbon have been enhanced by the addition of specific metal salts, activated carbon technology has changed little over the last 60 years. In this Phase I, Agave BioSystems and the Universities Space Research Association, propose to develop next generation smart adsorbents using novel carbon nanotube (CNT)-based structures for the adsorption and destruction of potentially toxic air contaminants. Since CNTs have extremely high surface area, can be readily modified with metals or functional groups, and can function without the mass transfer limitations of traditional activated carbon, they are an ideal material for integration into spacecraft air handling systems. Our goal is to build upon the unique structural and chemical nature of carbon nanotubes to generate a new generation of smart adsorbents. The exceptionally high mass transfer properties of these in situ grown carbon nanotubes should reduce problems of current filters such as pore clogging or limited accessible material.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Low-gravity environments are particularly susceptible to dust nuisance and hazard. In near 0-g, dust and particulate matter in general can float or become attached to nearly any accessible surface and can enter nearly any mechanical device or electronic module, potentially wreaking havoc. In fact this is one of the main causes for false fire alarms aboard the international space station. More recent reinvestigation of moon dust has shown that it consists of both micron and submicron (ultrafine) particles. The ultrafine material is of particular concern as the health dangers represented by such material on Earth are well known, being regulated by the EPA's PM2.5 rule. The super high surface area coupled with the reactive nature of the material then mandates its filtration from EVA related systems and generally from within spacecraft and space habitats.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Volatile organic compounds present one of the major environmental problems today. Filters for airborne particulate matter are essential in many instances, including air purifiers, respiratory protection equipment and clean rooms. In the manufacturing sector, semiconductor manufacturing requires ultra-high filtration. Not surprisingly sub-micron sized particles are the most difficult to remove. Within the consumer market, pollen from a variety of grasses, flowers and trees creates misery for millions across the US. Applications for this technology include indoor filtration systems to remove VOCs from indoor air streams, personal protective gear for workers exposed to occupationally high levels of industrial chemicals, and equipment for military personnel, firefighters and other public health officials who may come into contact with toxic air contaminants while dealing with the aftermath of industrial spills and leaks.readily removed from a water processing system would have dramatic advantages over existing methods.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Mainstream Engineering Corporation
200 Yellow Pl
Rockledge, FL 32955-5327

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Universities Research Association
10211 Wincopin Circle, Suite 500
Columbia, MD 21044-3432

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russell Davis
rwd@mainstream-engr.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The energy generation and storage for modern-day sensor networks, communications, and electronics presents a variety of unique challenges. To achieve the long-duration missions away from Earth as outlined in the Vision for Human Exploration in Space, these energy storage systems will need to undergo a dramatic increase in their specific energy densities. Recently, Mainstream has made startling advances in the area of high energy-density batteries using carbon nanotube (CNT) electrodes. However, theory suggests that silicon actually possesses an intercalation capacity that is an order of magnitude above that of carbon. If this is able to be translated into added capacity, it would truly revolutionize Li-ion electrochemistry and energy-storage technologies in general. The Universities Space Research Association has recently developed a process of growing silicon nanorods and has agreed to team with Mainstream for this Phase I STTR effort. This Phase I focuses on developing and testing electrodes comprised of both silicon and carbon nanostructures in Li-ion batteries. Because the basic battery chemistry will not be affected, safety will not be compromised.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
High energy density batteries have potential space and air-based applications that are simply too numerous to list. The primary benefit of any such battery for NASA is that it will permit NASA greater flexibility in planning future missions to meet new long-term objectives. Specific potential applications include orbiters and satellites, deep space missions, instrumentation balloons, and communication equipment.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Independent marketing studies have confirmed a significant commercial application for CNT batteries; the commercial electronics battery market currently produces millions of lithium-ion batteries per month with end applications as diverse as watches, palm pilots, cell phones, hearing aides, and pacemakers. Larger applications such as electric vehicles, space satellites for cellular communications, air-based platforms, hybrid vehicles, and tractor-trailer fleets will have need of advanced silicon and CNT electrode batteries as well.

TECHNOLOGY TAXONOMY MAPPING
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
HPN Software Consultant, Inc.
18519 Egret Bay, Suite 1509
Houston, TX 77058-3353

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Stanford University School of Medicine
701A Welch Road, Suite 1128
Palo Alto, CA 94304-0000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mr. Lac Nguyen
lac.nguyen1@jsc.nasa.gov

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In integrating the following three significant components for its research/research and development (R/R&D) effort, the power of this candidate Phase I project will be demonstrated through the Collaborative Virtual Environment Simulation Tool (CVEST): 1. Software Application Development Toolkit 2. Physiological Hardware Interface 3. Technology Integration Manager The multi-faceted CVEST development environment operates as a plug-and-play interface to various software and hardware products specializing in virtual reality-based simulation development. The final Phase I demonstration will feature the muscular mass/tissue deformation within a digital virtual human interface (DVH) to show performance data (physiological, biomechanical, etc). This STTR Phase I candidate project will concentrate on some new physiological hardware/haptic devices to produce tactile feedback to the user. These range from gross or large object reporting to more fine-grain/granular tactile sensing to thermal sensing devices. In addition, a COTS-based Global Position System (GPS) will be analyzed as wireless tracking source for the user. For NASA and commercial domains, this Phase I simulation facility, with its physiological/biomechanical functionality, could be implemented in software and integrated to enable realistic simulations of the forces exerted on and by users (astronauts, divers, etc.) as they work in various environments.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Although more applications could be established, the STTR Phase I candidate PI has identified specific areas within the NASA domain that could experience more immediate implementation and thus benefit. The primary beneficiaries of this STTR Phase I project will the following NASA organizations: 1) Mission Operations -- Immersive training for mission and flight control support can be deployed for more effective results. 2) Engineering and Robotics -- Critical hardware advances will provide impetus for more innovative solutions to problems in orbital and space exploration circumstances as well as focusing on robotic technology implementation. 3) Life and Medical Sciences -- More creative hardware implementation and medical visualization and training will result as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ability to merge a wide variety of technologies, OpticFlex, biosensors, biomechanics software, enhanced by incorporating haptic response and autostereoscopic rendering to allow domain objects (NASA, oil/gas, medical, financial, automotive, etc.), could effectively simulate more real-world scenarios in both NASA and commercial/academic environments. This system would provide critical support to operator/situational awareness in key delivery of enhanced robustness and intelligence in simulation of task scenarios. For example, assimilating complex training scenarios with various gravitational force settings and functionalities would distinguish the Phase I results from other products as a viable commercial mission simulation or training visualization product. The innovative 3D visualization and simulation robotic scenario management would, in concert with the 3D man-in-the-loop concept would make feasible realistic collaboration between other virtual humans and robotic entities in synthetic environments within NASA and/or non-NASA settings.

TECHNOLOGY TAXONOMY MAPPING
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Intelligence
Mobility
Manipulation
Perception/Sensing
Teleoperation
Operations Concepts and Requirements
Simulation Modeling Environment
Autonomous Reasoning/Artificial Intelligence
Computer System Architectures
Data Input/Output Devices
Human-Computer Interfaces
Software Tools for Distributed Analysis and Simulation
Sensor Webs/Distributed Sensors
General Public Outreach
K-12 Outreach
Mission Training
Highly-Reconfigurable

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NVE Corporation
11409 Valley View Road
Eden Prairie, MN 55344-3617

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Oregon State Univeristy
312 Kerr Administration Building
Corvallis, OR 97331-2140

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Albrecht Jander
jander@eecs.oregonstate.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this SBIR Phase I research project is to develop batteryless, wireless magnetic sensors with orthogonal frequency coding (OFC). These sensors will be based on surface acoustic wave (SAW) technology already in common use in microwave filters and signal processing elements for communications devices. We will develop new magnetostrictive structures to be combined on-chip with SAW devices to create innovative magnetic field sensors that can be individually interrogated from a distance with a microwave reader. Combining the magnetostrictive materials with OFC SAW transponders will provide new sensor capabilities that are compatible with the orthogonal frequency coding scheme recently demonstrated under NASA funding. The novel magnetic field sensors will be individually coded, inexpensive to manufacture, and require no on-board power?making them ideal for distributed and embedded monitoring technologies, for both government and commercial use.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NVE Corp. foresees a variety of applications for these sensors within NASA. These wireless sensors would have a particular advantage over other magnetic sensors in applications (including retrofit situations) where installing wires is expensive, inconvenient or hazardous. Applications of these sensors will include: * Remote magnetic field sensing * Remote sensors for nondestructive evaluation and structural health monitoring. * Remote current sensors * Remote position sensors, level sensors and rotary encoders * Remote proximity switches

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non NASA applications are similar to the NASA applications. The sensors can be used for nondestructive evaluation of both aircraft and sea-going vessels (military and commercial), industrial control, robotics, automotive sensors, power line monitoring, and structural health monitoring of civil structures.

TECHNOLOGY TAXONOMY MAPPING
Perception/Sensing
Telemetry, Tracking and Control
Airport Infrastructure and Safety
Instrumentation
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Sensor Research & Development Corporation
1718 Winchester Rd.
Annapolis, MD 21409-5851

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Central Florida
4000 University Boulevard
Orlando, FL 32816-8005

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Matthias Hamsch
jhines@ieee.org

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the development of passive wireless surface acoustic wave (SAW) based liquid level sensors for NASA application to cryogenic liquid level sensing. Orthogonal Frequency Coded (OFC) SAW devices have been demonstrated as passive wireless temperature sensors in NASA Contract NNK04OA28C, and are being further developed under NNK05OB31C. The proposed liquid level sensors will use damping of the acoustic wave caused by mass loading of the liquid to produce fast, reversible liquid level sensors. The proposed research will apply the results of ongoing work on OFC sensors and will evaluate their operation as liquid level sensors in selected liquids of interest at cryogenic temperatures. Issues to be investigated include the stability of various SAW substrates when exposed to various (extreme and gradual) temperature changes, the effects on device integrity and performance of thermal cycling to cryogenic temperatures, and the effects of device exposure to various liquids and the reversibility thereof. The result of the proposed research will be an understanding of potential failure mechanisms in SAW sensors used at cryogenic temperatures, knowledge of the required operating parameters to ensure device reliability under likely operating conditions, and demonstration of the use of OFC SAW sensors for liquid level detection.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application for the proposed sensors would be in a wireless multisensor system for liquid level measurement in storage tanks for cryogenic liquids. With uniquely identifiable sensors, this system could use low cost sensors mounted at numerous levels within a tank to remotely detect the presence (and therefore for terrestrial tanks the level) of liquid within the tank. Wireless sensor interrogation requires only one tank penetration for the transceiver antenna, minimizing heat transfer pathways. Resolution of liquid level is fine due to small sensor size. The proposed sensors could also monitor temperature in the headspace above the liquid.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
While the market size for potential applications needs to be evaluated, it is clear that the proposed sensors can be used commercially for liquid level monitoring within storage tanks for volatile liquids, and to monitor temperature in the headspace above such liquids. Since OFC SAW sensors operate over a wide range of temperatures, commercial applications may include both cryogenic and higher temperature liquid storage. Passivation of the sensor surface may make this approach feasible for use in caustic volatile liquids. Reversiblity of sensor response when the liquid level in the tank drops requires the liquids monitored to be volatile.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Fluid Storage and Handling
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Sensor Research & Development Corporation
1718 Winchester Rd.
Annapolis, MD 21409-5851

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Central Florida
4000 Central Florida Boulevard
Orlando, FL 32816-8005

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jacqueline Hines
jhines@ieee.org
1718 Winchester Rd.
Annapolis,  MD 21409-5851

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the development of passive surface acoustic wave (SAW) based hydrogen sensors for NASA application to distributed wireless hydrogen leak detection systems. Orthogonal Frequency Coded (OFC) SAW devices have been demonstrated as passive wireless temperature sensors in NASA Contract NNK04OA28C, and are being further developed under NNK05OB31C. The proposed hydrogen sensors will use a novel OFC SAW device structure, combined with Palladium nanocluster film elements to produce fast, reversible, highly sensitive hydrogen sensors capable of detecting a wide range of hydrogen concentrations at room temperature. The proposed research will utilize results from Argonne National Labs on the formation of Pd nanocluster films on self-assembled siloxane monolayers on glass. These optimized nanocluster films demonstrated hydrogen sensing from 25 ppm to over 2% hydrogen, with response times of milliseconds, complete reversibility, and no baseline drift at room temperature. The films experience large conductivity changes due to the hydrogen induced lattice expansion of the Pd nanoclusters and the quantum nature of conduction in nanocluster films. The performance of the SAW device will change in response to a change in conductivity of this film. Issues including SAM formation on piezoelectric substrates, nanocluster film deposition, and simulation of device performance will be evaluated.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application for the proposed sensors would be in a wireless multisensor system for hydrogen leak detection. With uniquely identifiable sensors, such a system could use low cost sensors mounted at numerous locations to remotely detect hydrogen leaks in real time. This system could continuously monitor "boot" air for leaks, and remotely alert personnel and/or trip alarms or initiate protective action if a leak is detected. The extreme sensitivity of these films to low levels of hydrogen, and their ability to operate reversibly without baseline drift at room temperature, should provide an advanced warning capability for leaks.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The primary potential commercial applications for the proposed hydrogen sensor relate to fuel cell monitoring, and to hydrogen generation, delivery, and storage monitoring. Given the emerging use of hydrogen as a fuel for automotive and fleet vehicles, there is a need for hydrogen sensors to monitor the safe handling of hydrogen. Presently, it is not clear if wireless operation would necessarily be beneficial in a sensor for these applications. However, the high sensitivity, fast response times, reversibility, wide range of hydrogen concentration sensed, low cost, and small size would make the proposed sensors applicable to these emerging market segments.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Fluid Storage and Handling
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Ceramics Research, Inc.
3292 E Hemisphere Loop
Tucson, AZ 85706-5103

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Arizona Board of Regents, University of Arizona
888 North Euclid Avenue, #515
Tucson, AZ 85719-4824

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Anthony Mulligan
amulligan@acrtucson.com
3292 E Hemisphere Loop
Tucson,  AZ 85706-5103

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Significant advances in several key technologies such as material sciences, manufacturing, miniaturization, and active flow control suggest that the time has come to address the issue of affordable General Aviation (GA). These new technologies when combined with advanced avionics and propulsion concepts will make GA affordable and ecologically sustainable. With a greater ease of vehicle operation, GA can become available to a much larger clientele and provide strong impulses for the aerospace industry. When a large number of new technologies are combined in a revolutionary way, validation of the entire system at the design and development stage becomes highly desirable. We propose building and flight testing a dynamically scaled model of NASA's GA demonstrator that will feature many important elements of the new GA concept.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed 1/3 scale model will be a test-bed for testing of the dynamical behavior of the envisioned Next Generation Aviation Demonstrator (NGAD). It will also serve as a low-cost/ low-risk test-bed for novel technologies such as high lift devices, circulation control, and tail-fan propulsion. The proposed development and flight test program should demonstrate that scaled models can considerably reduce the cost and risk involved when developing radically new aircraft concepts.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In addition to the research goals of the dynamically scaled NGAD, ACR will be able to directly benefit from the design and initial development of a light UAV airframe. Just like the goals of the full scale NGAD, the dynamically scaled model will have significant advantages over current light UAV designs. Noise reduction and safety are two of the biggest advantages. In a military context, most UAVs of this class are extremely loud, and can be heard long before being detected by other means. The shrouded fan and enclosed engine of the NGAD will both reduce and shift the noise signature of the aircraft. In civilian UAV applications, noise reduction shares the same value as it does in regards to tail-fan aircraft. Another advantage of the shrouded fan design is safety. By enclosing the propeller, the greatest danger to the ground crew of a UAV is removed.

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

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
James R Gloudemans
2309 Clipper Street
San Mateo, CA 94403-1005

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Georgia Tech Research Corp.
505 10th Street, NW
Atlanta, GA 30332-0420

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
James Gloudemans
jrcloud@gmail.com
2309 Clipper St
San Mateo,  CA 94403-1005

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Innovators working to revolutionize air travel through personal aviation pioneers need innovative aircraft design tools. Vehicle Sketch Pad (VSP) is an aircraft geometry tool for rapid evaluation of advanced design concepts. VSP will be extended to include support for the modeling of aircraft structural layout and a modular system for integrating engineering analyses. These modifications will allow VSP to unify geometry, aerodynamics, and structures in the early design of advanced concepts. VSP will be released as open-source; a community for its development will be initiated and fostered. Open distribution will ensure that VSP is available to all, thereby supporting personal aviation innovators, universities, NASA, and the whole aerospace industry. This will enable a new level of fidelity and accuracy in personal aircraft design needed to meet the aggressive goals required for the success of personal air vehicles. An improved and open VSP will catalyze personal aviation by supporting breakthroughs in noise and cost reduction and ease of operations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed improvements to VSP will greatly benefit NASA and will find widespread application. Truly multidisciplinary design of revolutionary concepts will be enabled by the new structural layout and analysis launch pad capabilities. Aerodynamics and structures will be unified by a common geometry engine capable of rapidly generating complex configurations for design. All NASA vehicle design efforts, from personal aviation to space exploration, stand to benefit from this improved tool. While NASA already has access to VSP, NASA will benefit from the open-source release of VSP. The open-source model creates an environment in which every party benefits from the growth of the community. An open geometry platform will allow NASA to collaborate more closely with partners in industry and academia.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed improvements to VSP have many applications to the commercial sector. In addition to supporting the personal air vehicle community, VSP will find application with general aviation and the aerospace industry at large. In delivering an open source aircraft design platform, common ground is established for the development and integration of engineering analyses. Small businesses have historically been unable to afford advanced engineering software tools. Recently, industry has demonstrated an unwillingness to develop and maintain software tools over a long period of time. Industrial capability is decaying and the cost to outsource solutions is rising. The open release of an improved VSP will provide commercial entities, small and large, with an advanced software tool. In founding an open community, the longevity of VSP is ensured; so long as the tool is useful to the community, they will persist. Direct commercial opportunities will result from the successful open release of VSP including training, custom development, and consulting services around the open-source platform.

TECHNOLOGY TAXONOMY MAPPING
Airframe
Simulation Modeling Environment
Human-Computer Interfaces
Software Tools for Distributed Analysis and Simulation
General Public Outreach
K-12 Outreach

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luna Innovations Incorporated
2851 Commerce Street
Blacksburg, VA 24060-6657

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Virginia Polytechnic Institute and State University
460 Turner Street, Suite 306
Blacksburg, VA 24060-3362

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Roger Duncan
submissions@lunainnovations.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the future, exploration missions will benefit greatly from advanced metrology capabilities, particularly structural health monitoring systems that provide real time in situ diagnostics and evaluation of structural integrity. Safety- and mission-critical components and systems will be instrumented with embedded sensors to provide a real-time indication of health, helping to ensure that America's space exploration remains safe and cost efficient. One of the most promising technologies for accomplishing this is fiber-optic sensors. Due to their light-weight and multiplexing potential, fiber-optic sensors are highly desirable for employment in this fashion. However, most COTS devices are bench sized units and are too large and heavy to be overly attractive for space applications. To address this shortcoming, Luna Innovations proposes to develop a compact, light-weight, low-power consumption, multi-parameter distributed sensor system based on the OFDR technique. The interrogator will incorporate optical ASIC technology, highly integrated tunable VCSEL technology, and state-of-the-art integrated processing technology to dramatically reduce the size, weight, and cost and to dramatically increase the performance and robustness relative to COTS OFDR interrogator units. This interrogator will interface with fiber-optic strain, temperature, and shape sensor arrays, enabling simultaneous interrogation of a multitude of sensors, dramatically reducing the per sensor cost of instrumentation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The interrogator as well as the sensors will be designed to perform in the high stress and hostile conditions expected on launch vehicles and space environments. The resulting miniaturized, ruggedized device will thus be capable of operation in high vibration environments, resulting in a high reliability device that will have great utility as a portable multi-parameter sensing unit. Such instrumentation could continuously provide distributed strain, temperature, and shape measurements in a space environment. Strain measurements, for example, could yield information on highly-stressed or fatigued structural members, enabling condition-based maintenance. Direct measurement of shape and position will be a unique capability enabled by the proposed device. Recently, Luna has demonstrated the ability to make accurate high-spatial resolution 3D shape and/or position measurements with a tri-core optical fiber containing FBG arrays in each core. Thus, the proposed instrumentation system will provide NASA a highly useful and unique tool in its metrology toolbox.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting miniaturized, ruggedized sensing unit will achieve a unique blend of reliability and reduced cost which will have great utility as a field-portable sensing unit. Such units could prove invaluable in many field monitoring applications. The long term monitoring of civil structures using distributed fiber-optic sensing arrays would be realized by a low-profile, permanently installed interrogator. It is anticipated that this technology will find use in many health monitoring applications as a sensing network in air-, land-, and sea-based military vehicles. In addition, the oil & gas industry, already employing distributed FBG sensing technology for long term monitoring of production wells, would be a natural market for the developed technology.

TECHNOLOGY TAXONOMY MAPPING
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Solar
Tethers
Human-Robotic Interfaces
Integrated Robotic Concepts and Systems
Manipulation
Perception/Sensing
Teleoperation
Control Instrumentation
Airframe
Airlocks/Environmental Interfaces
Erectable
Inflatable
Kinematic-Deployable
Launch and Flight Vehicle
Large Antennas and Telescopes
Modular Interconnects
Structural Modeling and Tools
Tankage
Fluid Storage and Handling
Instrumentation
Portable Data Acquisition or Analysis Tools
Optical
Sensor Webs/Distributed Sensors
Ceramics
Composites
Metallics
Multifunctional/Smart Materials
Aircraft Engines

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Bossa Nova Technologies LLC
606 B Venice Blvd
Venice, CA 90291-4863

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Boston University
110 Cummington Street
Boston, MA 02215-2407

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
bruno Pouet
bpouet@bossanovatech.com
606 B venice Blvd
Venice,  CA 90291-4863

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This STTR Phase I project describes the development of a high-performance, robust, portable, and compact laser ultrasonic system for multi-purpose Non-Destructive Evaluation (NDE). Laser ultrasonic has now become a valuable tool for on-line inspection, demonstrating its advantages in the steel and aerospace industries. Non-destructive laser ultrasonic inspection equipments use large size laser components. They are not designed for light-weight, portable and power sensitive applications. Currently, NDE of space transportation vehicles is primarily carried out on the ground, between missions but for future space missions, more inspection will need to be performed in space in order to monitor the aging process of the structure and to insure its integrity. For inspection during space flight, the NDE equipment must be compact, lightweight, easily operated by human with limited mobility or robot, and exhibits low power consumption. To satisfy these requirements we proposed to develop a laser ultrasonic inspection system integrating an amplitude-modulated continuous wave laser source for high efficiency generation and a multi-channel random-quadrature interferometer for robust and highly sensitive detection. The proposed system takes advantage of fiber technology for both the generation and the detection in order to achieve a compact, portable and versatile inspection system.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed system will be designed to satisfy the size, weight and power requirements for NDE systems to be embarked during space mission. The primarily target is the NDE during space flight, but it will also be applicable to on-the-ground NDE. Potential NASA applications covers a variety of NDE inspection needs, including the detection of subsurface inclusions and surface breaking cracks, the inspection of wiring and detection of cracks in the insulation, characterization of coating materials and bonding properties.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential non-NASA commercial applications include ground based aircraft and spacecraft inspection, the inspection and characterization of thin films and coatings, residual stress measurement, fatigue crack detection, and the inspection of metallic and composite plates.

TECHNOLOGY TAXONOMY MAPPING
Laser
Optical
Photonics

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
3TEX, Inc.
109 MacKenan Drive
Cary, NC 27511-7903

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Southern Illinois University Carbondale
Center for Advanced Friction Studies
Carbondale, IL 62901-6899

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Keith Sharp
sharpk@3tex.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A clear need exists for the next generation of Ceramic Matrix Composites (CMC) for Thermal Protection Systems (TPS), propulsion hardware, and other high temperature applications. No "off-the-shelf" materials and/or processes capable of meeting NASA's goals are available, yet completely integrating a unique combination of commercially available or nearly commercially available technologies can meet NASA's goals. The basic elements of the proposed approach focus on refining 3-D fiber architectures, instituting semi-conductor industry controls on the CVI process, forming a gradient interphase between the matrix and fibers, and relying on molecular level modeling results to predict thermal stability. Both 3-D woven and 3-D braided preforms will be designed and manufactured to control the resultant pocket size and shapes to reduce voids during infiltration. Pulsed CVI with an improved out-gas control system will both form a gradient interphase that reduces the CTE mismatch induced internal loads between fiber and matrix and provide a more perfect microstructure while improving processing speed. CMC test articles will be compared to previous work on molecular level thermal modeling for Phase I. Phase II will deliver optimized design and manufacturing processes capable of making impact tolerant, long fatigue life, high temperature CMC's.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Target NASA markets would be: - TPS structures for next generation Shuttle, Mars and Lunar mission modules, heat shields. Leading edges for hypersonic SSTO vehicles - Propulsion system components, such as nozzles, pump covers, pump components, - Acreage for external combustion engine designs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Target markets would be: - Gas Turbine Engine Components ? Medium to large market with some R&D money available, though less R&D money than the TPS structures. Performance is a driver, so a premium would be paid for additional performance. Main components where 3TEX should offer advantage are guide vanes for all engines and exhaust flaps for those with afterburners. - Chemical processing (pump components, stirrers, heaters) ? Medium to large market, with some premium available for corrosion resistance. - Industrial burners ? Large market, though very competitive on price and little to no R&D money available.

TECHNOLOGY TAXONOMY MAPPING
Ceramics
Composites
Multifunctional/Smart Materials

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Florida International University
11200 SW 8th St (MARC 430)
Miami, FL 33199-0001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John O'Dell
scottodell@plasmapros.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Molybdenum has been identified as a promising material for many high temperature NASA applications due to its high melting temperature, resistance to liquid metals, resistance to hot hydrogen, high thermal conductivity, and relatively low density. However, molybdenum's ductile to brittle transition temperature is above room temperature, which makes fabricating complex components extremely difficult by conventional fabrication techniques. Recent, advancements in Vacuum Plasma Spray (VPS) forming technology have enabled the fabrication of complex molybdenum and molybdenum-rhenium components. However, further increases in performance could be gained by the development of higher use temperature molybdenum alloys. During this investigation, innovative dispersion strengthened, molybdenum-rhenium alloys will be developed using VPS forming techniques and through the proper selection of advanced transition metal (TM) based ceramic dispersoids. These alloys have the potential to operate at temperatures greater than 1800?C for extend durations.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential NASA applications include, but are not limited to nuclear power generation and propulsion, chemical propulsion, high temperature furnace cartridges, crucibles for microgravity processing, heat pipes, heat shield applications, high temperature electrical contacts, heat exchangers, high temperature creep resistant structures and components.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Additional commercial technologies include, aerospace and defense industries, nuclear power generation, welding electrodes, x-ray targets, warhead penetrators, shielding applications, high temperature furnace components, heat exchangers, heat pipes, etc.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Nuclear (Adv Fission, Fusion, Anti-Matter, Exotic Nuclear)
Metallics
Nuclear Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Hypercomp Engineering, Inc.
1080 North Main, Suite #2
Brigham City, UT 84302-0505

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Utah State University
1415 Old Main Hill
Logan , UT 84322-1415

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jared Noorda
jaredn@hypercompeng.com
1080 North Main, Suite #2
Brigham City,  UT 84302-0505

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
HyPerComp Engineering Inc. (HEI) and Utah State University (USU) propose to develop technology for lightweight composite materials for use in composite structures suitable for both cryogenic and damage tolerant environments. The proposed effort will incorporate previous work performed by HEI in the cryogenic performance of composite materials as well as previously developed improved impact technologies for micro-meteor/space debris survivability. The application of filament wound composite pressure vessels in pressurized storage tanks at cryogenic temperatures has been undertaken at HEI and NASA MSFC with promising results. Likewise, HEI has been conducting research and has patented, jointly with NASA MSFC, a robust impact resistant composite pressure vessel technology. This technology shows great promise in its resistance to performance degradation from impacts, such as those that might be experienced in the space environment in the form of micrometeoroids and space debris. Both of these technologies have been characterized for lightweight composite pressure vessels separately. However, little if any understanding currently exists of their combined potential for both cryogenic and impact resistant composite structures applications, of those including, composite overwrap pressure vessels (COPV's). The combination of the foregoing cryogenic technology with an impact resistant, robust composite pressure vessel technology would be studied. Further, we believe, that combining these two technologies will provide a baseline technology from which to develop a dual-use composite structure. This would be to ensure the integrity of the light weight composite structures, such as cryogenic fuel is stored in an orbiting depot, when exposed to the harsh environment a spacecraft will be expected to encounter during the life of its mission.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications for the technologies we propose researching and developing would be light weight composite structures that could be used for reliable and safe cryogenic propellant (i.e. fuel depots) storage and robust structures and tankage capable of withstanding micrometeoroid and space debris impacts

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial pressure vessel industry is always hungry for improvements in performance (i.e. weight) and safety. There has been some significant discussion on the usage of cryogenic pressure vessels for efficient gaseous fuel storage, particularly with regard to the transportation of large volumes of gaseous fuels such as CNG. The improvement in environmental robustness of cryogenic capable light weight pressure vessels will be noted by the commercial industry and this technology will be incorporated into specialized application.

TECHNOLOGY TAXONOMY MAPPING
Propellant Storage
Tankage
Fluid Storage and Handling
Portable Life Support
Composites
Energy Storage

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
CFD Research Corp
215 Wynn Dr.
Huntsville, AL 35805-1926

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Mississippi State University
Box 9637 300 Butler Hall
Mississippi State, MS 39762-9637

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sarm Rani
jls@cfdrc.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this STTR, an innovative, efficient and high fidelity computational tool to predict radiative heat transfer will be implemented in the LOCI framework. Radiative heat transfer in rocket engine combustion can play a significant role in determining engine performance and combustor wall heat loading. Radiation will also become increasingly important as hydrocarbon-based fuels are used in rocket propulsion as alternatives to hydrogen, for in-situ propellants, and in the development of nontoxic fuels for reaction control thrusters. Currently there is no radiation modeling capability in the LOCI framework, the basis for codes used by NASA and their contractors to design and analyze rocket engines. CFDRC has teamed with Mississippi State University (MSU), the original developer of LOCI, to develop the needed radiation module. In Phase I, the well-established Control-Angle Discrete Ordinates Method will be implemented for solving the Radiative Transfer Equation. This module will be used in the combustion code, CHEM, and tested with proven gray and nongray gas radiation models to establish the framework for future development and to demonstrate the feasibility of radiation modeling using LOCI. In Phase II, efforts will focus on developing increasingly accurate and robust nongray gas models such as the narrow band models, Weight-Sum-of-Gray-Gases method, and the innovative Full Spectrum Correlated k-distribution model.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The LOCI radiation module will enable NASA and government contractors to better design and analyze rocket engine combustion systems, including new cryogenic rocket engines needed for In-Space Propulsion. At the end of Phase II, NASA will have a comprehensive suite of radiation modeling capabilities that will help design safer and more efficient rocket-propelled vehicles of the future. The software will be a final deliverable to NASA, and will be in open source format. The LOCI module will be implemented into a NASA selected CFD code, LOCI-CHEM, and can also be added to other LOCI-based codes such as LOCI-STREAM.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Design and optimization of combustors using CFD tools is standard practice in both the rocket and gas turbine industries. Industrial combustion system designers are particularly interested in prediction of pollutant emissions, but poor radiation modeling limits the effectiveness of current CFD tools. The market value and commercial impact of the proposed development is expected to be significant because of its high fidelity, computationally efficiency, and utility for a wide range of combustion problems. The proposed development will also be of interest in the furnace, heater and boiler industry.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Simulation Modeling Environment

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sierra Engineering, Inc.
603 E. Robinson, Suite 7
Carson City, NV 89701-4046

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Purdue University, Sponsored Program Services
302 Wood St.
West Lafayette, IN 47907-2108

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Curtis Johnson
cwj@sierraengineering.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Sierra Engineering and Purdue University propose to leverage combustion stability testing, already funded and planned for the second and third quarters of next year at Purdue, by developing a non-intrusive plume instrument capable of detecting combustion instability and testing it during combustor firings. Purdue has previously created the combustor and demonstrated unstable combustion operation. Sierra will apply its experience with plume signature prediction and plume signature tailoring to model the combustor response and estimate the high frequency variations in the combustion process that feeds the instabilities. Both Sierra and Purdue have expertise in combustion instability and the mechanisms that cause it. This expertise will be used to develop a methodology, based on plume observations, to estimate combustion burning response and, hence, predict combustion stability margin. During a Phase II STTR, more testing and higher fidelity instrumentation will mature the methodology for future application to NASA test facilities. Successful completion of this project will provide a non-intrusive tool for detecting and diagnosing combustion instability that is superior to current intrusive methods.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Current NASA roadmaps point towards development of new hydrocarbon fueled engines. Whether the new engines use kerosene or methane, both fuels have led to unstable combustor designs in the past; therefore, combustion stability will be important to NASA in the future. Improved combustion stability diagnostic tools, especially ones that are non-intrusive to the combustor hardware, can be an important part of this future development. If the technology proposed here works, complete combustor bomb test campaigns (which can be dangerous) may be eliminated with potential cost savings of millions of dollars. Application of this technology to other combustion issues, such as combustion efficiency, can improve engine-specific impulse, which would improve overall CEV performance.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Successful application of this technology can be important to many other organizations that develop combustors, not only those in liquid rocket engines. Combustion stability has plagued solid rocket motor development as well as air breathing aircraft engines and commercial burners. An improved methodology to assess stability margin and diagnose problems could be applied throughout the combustor industry. The Missile Defense Agency is also researching more accurate ways of typing threat missiles. Data and instrumentation design developed in this effort could be directly used in developing new typing instrumentation and methods based on high frequency intensity variation.

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Testing Facilities
Optical
High-Energy
Power Management and Distribution
Thermodynamic Conversion

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
2L Research
190 Green Valley Road
Owens Cross Roads, AL 35763-9726

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Alabama
Box 870104
Tuscaloosa, AL 35487-0104

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
LUIS TREVINO
trevino@hiwaay.net

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposal outlines a research program for developing a novel soft-computing technology composed of an Artificial Immune System and Bayesian Belief Networks for monitoring, knowledge and information processing, and decision support infrastructure for testing of rocket engines of future spacecrafts. An engine failure during test operations may cause catastrophic results for the test article, supporting infrastructure, and potentially to supporting resources. The ability to effectively monitor health and status of a testbed and test article during a test firing and to take corrective measures for peak performance and improving reliable operations is of utmost importance. Using an existing SR-30 Jet Engine testbed utilizing artificial intelligence control techniques, novel algorithms are being developed by The University of Alabama that can function under faulty sensor conditions, can work effectively with thousands of sensors at high data rates, are self-checking, and are self-correcting can be of further support. The proposed effort builds on an existing joint MSFC/University of Alabama project where NASA's NSSTC is only funding graduate student research. This proposal will further enhance technology research for realization and synthesis of needed advanced algorithms in larger scale test platforms for propulsion health management, thereby furthering educational research addressing NASA's education missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology will help NASA test programs with advanced test platforms with improved abilities to monitor, process knowledge and system information, infer about system state, and provide supporting information for performing real time decisions. The technology is widely applicable to complex robust systems such as a rocket jet engine and supporting test infrastructures. For the test environment, insuring that reliable engineering data and supporting information from the test facility is provided to test personnel will further enable them to make qualified real time decisions. This will further guarantee mission success and further insure safety to the test article. Cases such as premature engine shutdowns, pump cavitation, propellant leaks, and numerous problems inherent in cryogenic environments (i.e., with sensors and data) are costly and pose risk in social acceptance of current and future space-based programs. Other non-propulsion (complex) systems can certainly benefit from the core technologies proposed.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
For improving commercially based test systems and their operations, the proposed technology will help provide a deeper ability to monitor, process knowledge and system information, infer about the system states, and aid personnel in their critical decisions during all phases of test operations. Such information may entail system parameter adjustments, critical reconfiguration of the test article, or halting all operations for safety concerns. Advanced methods such as intelligent agents, behavioral networks and more for better test environments for: - Facility and Test Article Health-Monitoring Technologies - Improvement in Ground-Test Operations, Safety, Cost- Effectiveness, and Reliability - Application of System Modeling to Ground Test Operations in a Resource Constrained Environment Technology Beneficial to Industry: ? Nuclear & coal-fired power plants systems ? Space capitalists seeking commercial application for space travel ? Manufacturing processes: oil & gas refineries, textile, automotive, mining, etc. ? Transportation systems (i.e, aviation, locomotive).

TECHNOLOGY TAXONOMY MAPPING
Operations Concepts and Requirements
Simulation Modeling Environment
Training Concepts and Architectures
Testing Facilities
Autonomous Reasoning/Artificial Intelligence
Data Acquisition and End-to-End-Management
Data Input/Output Devices
Expert Systems
Human-Computer Interfaces
Portable Data Acquisition or Analysis Tools
Software Tools for Distributed Analysis and Simulation
Sensor Webs/Distributed Sensors

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cook's Advanced Energy Conversion, LLC
109-A Garrard Road
Starkville, MS 39759-2001

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Mississippi State University
205 Research Park
Mississippi State, MS 39762-0000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jagdish Singh
singh@dial.msstate.edu
109-A Garrard Road
Starkville,  MS 39759-2001

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA/ Marshall Space Flight Center (MSFC) needs sensors that can be operated on rocket engine plume environments to improve NASA/SSC rocket engine performance. In particular, NASA/MSFC would like to develop sensors to monitor the performance of rocket engines. The measurement of soot volume fraction and soot particle size can be employed to develop a sensor for on-line, real-time measurements to characterize the performance of hydrocarbon rocket engines and study the effects of the rocket engine exhaust on the environment. The goal of this proposed effort is to develop a laser-induced incandescence (LII) sensor, which is able to provide near real time measurement of soot concentration in the engine plume. During Phase I, a LII system based on telescopic collection optics for remote applications will be designed. The experimental parameters will be evaluated to achieve optimum response time and sensitivity. The study from Phase I will provide the necessary information to improve the phase II prototype design to achieve millisecond response time and better sensitivity. In Phase II, a prototype fieldable LII system will be developed and tested at MSFC and will be delivered to NASA/MSFC for further testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The LII sensor will be an advanced, non- intrusive, real-time, diagnostic tool which will be used for rocket engine testing. The sensor can provide an indication of engine performance and efficiency of the combustion process and effects on the environment of the engine testing. It will be needed to develop new hydrocarbon rocket engines. The sensor can monitor the performance of the rocket engine by monitoring the soot volume fraction and soot particle size in the plume. It can also be used to evaluate new rocket engine fuel and help to develop new engines that are needed for the President's vision for US Space Exploration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A compact, low cost, miniaturized LII sensor can be designed for non- NASA applications to monitor soot volume fraction and soot particle size in various engine exhausts. The sensor's non-intrusive, near real time performance capabilities will have a number of environmental applications. It can be used to inspect diesel engine vehicles on the road to satisfy EPA requirements for soot emission from the engine. It can also be used to monitor the exhaust of certain chemical industries and combustion based power plants. This sensor will be very useful in monitoring large populated cities with heavy traffic to provide an indication of the health status of the atmosphere.

TECHNOLOGY TAXONOMY MAPPING
Chemical
Optical

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Massachusetts Institute of Technology
77 Massachusetts Avenue
Cambridge, MA 02139-4301

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Olivier de Weck
deweck@mit.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Currently, the state-of-the-art in space asset tracking and information management is bar-coding with relational database support. To support NASA's need for reliable and low-cost asset management, Payload Systems Inc. and MIT propose to develop Rule-based Analytic Asset Management for Space Exploration Systems (RAMSES) ? an intelligent space exploration environment in which information is shared and automatically harmonized among disparate data sources. This information is then combined with mathematical models and rule-based analysis to produce meaningful data for asset tracking and intelligent decisions. The combined data will communicate with analytic models that provide analyses, estimates, predictions and plans. This intelligent space exploration environment will be equipped with sensors, radio frequency identification (RFID) equipment and sophisticated information infrastructures to make full use of multiple data streams.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The prime commercial application for the RAMSES system is for asset management for space exploration systems. Primarily, this is aimed at Lunar and later Mars exploration with human crews. The architecture of RAMSES can be easily adapted to other applications that involve multiple distributed assets, agents with extraordinary time and resource constraints, and the need for comprehensive data logging and database management.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The system could be used for military outpost establishment and remote exploration bases on Earth. The system could also be used in the planning and management of assets in complex search and rescue scenarios.

TECHNOLOGY TAXONOMY MAPPING
Data Acquisition and End-to-End-Management

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Redefine Technologies
44 Linn Lane
Golden, CO 80403-9708

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
The Regents of the University of Colorado
UCB 572, 3100 Marine Street, Room 481
Boulder, CO 80309-0572

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Steve Wichman
steve@redefine.com
44 Linn Lane
Golden,  CO 80403-9708

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
T3RSS is the system engineer's tool that allows a systematic approach to ensuring that even if one or more failures occur in a single component or subsystem, then the subsystem will continue to function and most, if not all, mission objectives can still be achieved. T3RSS does this by using a Configuration Manager for a Dynamically Reconfigurable System (CMDRS). This piece of logic employs a Mission Survivability Assurance Algorithm (MSAA) for the subsystem. Should radiation, manufacturing or even launch damage render a particular region of the FPGA temporarily or permanently unusable while on orbit, then the MSAA can shift the critical logic to a new region, or even to a new FPGA altogether. The shifting logic uses a network of components to maintain the ability of each logic block to communicate with the required memory and hardware. Ensuring that needed logic is always available ensures that the satellite can maintain 100% mission survivability even during failures.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Mr. Clint Patrick is the Reconfigurable Computing point of contact for NASA at Marshall Space Flight Center. He currently leads two programs that may benefit from the research that Redefine Technologies is doing with T3RSS. He has expressed his full support of our research in an attached letter. The first program, Fault Tolerant Avionics, is researching the feasibility of including a single, reconfigurable FPGA as a 'common spare'. This spare would be a backup for the other avionics boards on the aircraft: if one goes down, the functionality of that system would be passed to the spare to take over in real-time. The T3RSS concept is directly applicable to this program because the same goals are being investigated. The second program is in support of Radiation-Hardened Electronics for Space Exploration (RHESE). Their self-training, autonomous, neural network is currently configured to run on powerful CPUs. The speed and power savings of moving this processing to logic would mean better performance out of the network, however, the size of each neuron implies that a 'shifting' or 'time-multiplexing' of logic within each FPGA would be needed. The on-demand and priority-driven algorithms developed for T3RSS to ensure the modules are where they're needed, when they're needed, could be the enabling technology for the redesign of this system.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
10.2 Potential Military Applications The Air Force's Operationally Responsive Space (ORS) is an initiative to build the technologies required to have a more reactive space industry. The goal is to integrate the spacecraft and payload, select and load software, charge battery, fuel spacecraft, integrate to launch vehicle, and launch with eight days. While this capability is far in the future, the technologies and methodologies are being developed today. They've taken first steps towards this goal (i.e. satellite developed within 12 months). However, one of the biggest delays was testing and validating hardware and software. T3RSS can help in both validating a hardware configuration as well as giving the developers a chance to quickly add new capabilities that didn't exist before. 10.3 Potential Non-NASA Commercial Applications Space Micro Inc. and Design_Net Engineering have expressed interest in the T3RSS concept. All three commercial manufacturers use FPGAs in their civil, military and commercial space programs. All three would benefit from an increased survivability rate that they can advertise with their products.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Kestrel Technology LLC
4984 El Camino Real #230
Los Altos, CA 94022-1446

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Jet Propulsion Laboratory
4800 Oak Grove Dr., MS 301-270
Pasadena, CA 91109-8001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Allen Goldberg
goldberg@kestreltechnology.com
3260 Hillview Ave.
Palo Alto,  CA 94304-1201

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
With embedded software becoming ever more complex, assuming that it behaves perfectly is not realistic. The adaptation of fault protection concepts to embedded software is attractive, particularly in the context of the fault containment and health management capabilities provided by ARINC 653. In Phase II we shall develop tools to define simple, verifiable models that characterize the software with respect to its interface behavior, resource usage, and data reasonableness. We shall provide a software framework to instrument and monitor the software as it executes in both test and operational environments. When a deviation from the model is detected, a simple remediation action, including a hard or soft component reset is invoked. These tools will be integrated into ARINC 653 to support fault detection and recovery in an operational context, and the Eclipse software development environment for application in a test and verification context such as DSIL and engineering analysis context such as CEAL. Further we shall produce a methodology to assist in certification of instantiations of our software fault protection framework.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Software errors have had adverse effects on NASA missions. Project Constellation has stringent requirements to recover from mission- and safety-critical faults. As such ISHM plays an important role. Yet ISHM methods for detecting and recovering from software errors are not well-developed. The approach developed in Phase I is targeted to Constellation and builds on the ARINC 653 Application Executive, which has been selected for use on the CEV. Further, we supply tools to be integrated into DSIL and CEAL that aid in test and verification of Constellation software.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Our key innovation is a certifiable, efficient, and effective concept for detecting and recovering from software faults. These concepts have relevance and application to any safety-critical embedded software system, including automotive, plant control, and medical systems. ARINC 653 has been widely adopted for use in both commercial and military avionic. We propose a realization of our fault protection concept as an extension of the ARINC 653 health management framework.

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Virginia
PO Box 400195
Charlottesville, VA 22904-4257

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason Burkholder
burkholder@bainet.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of this STTR effort is to evaluate and demonstrate the potential for well-designed, strategically-located synthetic jet actuators to provide improved aircraft safety by: (1) delaying wing stall and improving aircraft controllability at high angles of attack and (2) providing low-cost actuation redun-dancy to improve controllability in the event of a mechanical control surface failure. Delaying flow separa-tion (i.e., wing stall) and providing "back-up" control power could allow an aircraft to recover from adverse conditions (due to a control surface failure, pilot/autopilot error, etc.) that would otherwise result in a loss of control. Flow control studies have shown that synthetic jet actuators are efficient devices for controlling separated internal and external flows. However, an obstacle to the widespread application of synthetic jet actuators for practical flight control is that modulated input signals to achieve closed-loop flow control objectives have been shown to be complex. Barron Associates, the University of Virginia, and the University of Wyoming propose to develop a software toolbox for the creation of adaptive control systems for actuators having complex, nonlinear dynamics. The Phase II effort will culminate in a wind tunnel test that quanti-fies the safety improvement potential offered by adaptively-controlled synthetic jet actuators.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed research effort clearly offers the potential for a significant leap in vehicle performance, op-eration, safety, cost, and capability. The technology will require a Phase III demonstration in an actual-flight environment to fully characterize and validate the performance that is predicted in simulation and demonstrated in wind tunnel experiments in Phase II. The research is particularly relevant to NASA's Intelligent Flight Control System (IFCS), which has the objective of enabling a pilot to land an aircraft that has suffered a major systems failure or combat damage, and also to the Single Aircraft Accident Preven-tion thrust of the Aviation Safety Program in which Barron Associates has participated for a number of years. The adaptive control system toolbox will have widespread application to traditional and newly-emerging flight control system actuation technologies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Adaptive active flow control methods could enable significant advances for numerous aerospace sys-tems, including military fixed-wing aircraft, unmanned air vehicles, projectiles, and commercial and gen-eral aviation aircraft. The vast array of corporations and federally-funded entities currently engaged in active flow control research creates the potential for a large contract R&D market. Furthermore, active flow control technology provides a natural complement to other advanced intelligent vehicle control prod-ucts already under development at Barron Associates. The most direct commercialization route is via collaboration with the major airframers. Fortunately, Bar-ron Associates has strong, existing working relationships with these companies. As parallel research advances at the major aerospace companies, BAI will pursue commercialization and collaboration oppor-tunities. Although it is difficult to predict the rate of advancement of the ongoing research activities upon which future commercialization may depend, even a relatively small market can play a significant role in our growth as a company.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Migma Systems, Inc.
1600 Providence Highway
Walpole, MA 02081-2553

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Louisiana State University
Department of Mechanical Engineering
Baton Rouge, LA 70803-6413

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bo Ling
bling@migmasys.com
1600 Providence Highway
Walpole,  MA 02081-2553

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Under NASA Phase I funding, we have developed a system for the ball bearing fault detection and identification. Our system can effectively identify multiple fault modes related to the evolution of friction within the contact in the coated ball bearings. To detect bearing faulty modes, we have developed a new bispectrum and entropy analysis method to capture the faulty transient signals embedded in the measurements. To classify the fault modes, we further developed a set of stochastic models using hidden Markov model (HMM) and Gaussian mixtures. Test results using lab experiment data have shown that our system can identify coated ball bearing fault modes in near real-time. In Phase II, we will further develop and test our system developed in Phase I for spacecraft mechanical parts health monitoring and mitigating actions. A thorough understanding of the failure mechanisms of the moving parts will emerge by the end of the Phase II effort, as well as the methodology to prevent catastrophic failure while in orbit. Algorithms developed in Phase I/II will be implemented in C/C++. Effort will be focused on the accuracy, autonomous, speed and efficiency of the system. The Boeing Company has teamed with us for Phase II effort.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate benefits for NASA will be the reliable operation of many precision machinery used in tracking systems satellites, telescopes and other space instruments require very stringent position accuracy – in the range of microns. Our system will make it possible for these enormously expensive systems to operate reliably with little or no maintenance and long service-life duration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Our technologies can also be used for commercial industries. For example, process industry represents a major industrial segment, including oil refinery, gas, metals & mining, food processing, pulp & paper, power, pharmaceutical, etc. Our core technologies can be used in the process industry where many rotation machines are placed in the field. These instruments are either connected in a local network or connected to the central control room. Our bearing health monitoring system can be used to monitor and perform real-time diagnosis for the process systems where instruments and control equipment are placed across the entire plant. Our system can help the plant operators avoid unnecessary costly shutdowns.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Invocon, Inc.
19221 I-45 South, Suite 530
Conroe, TX 77385-8746

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Colorado
572 UCB
Boulder, CO 80309-0572

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kevin Gifford
gifford@rintintin.colorado.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Integrated Data Assimilation Architecture (IDAA) addresses the fundamental problem of command, control, and communications systems interoperability. Interoperability of Explorations systems is necessary to improve reliability, reduce complexity, increase software and hardware reusability, and enable multi-developer / multi-agency support. The IDAA architecture consists of a software component, the BioNet middleware, and a hardware component, a Mobile Data Acquisition and Communications processing System (MDACS). Development and advancement of the BioNet middleware was the primary focus of the Phase I STTR effort. Continued BioNet middleware development will occur as a proposed Phase II activity along with the development of the MDACS generic hardware platform. From a functional perspective, the BioNet middleware provides a standards-based command and control capability, while the MDACS provides a generic space-rated hardware platform for general-purpose computations and communications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Potential near-term NASA applications of the proposed architecture include vehicle health monitoring of the Shuttle and CEV, structural and environmental monitoring in and around the International Space Station (ISS), and crew medical monitoring. As part of the Exploration Directorate, proximity networks could easily be deployed on the Moon and Mars, with inherent interoperability and coexistence capabilities even when provided by multiple sources. Such networks could include imagery collection, crew communication, remote sensing nodes for scientific applications, robotic command and control, and environmental and safety monitoring of crew habitats.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of the proposed architecture for use by NASA on the International Space Station and for Exploration-class missions has significant application to commercial space-based and terrestrial markets, including military network centric warfare applications, homeland security, satellite data systems, medical instrumentation and the healthcare industry, and industrial facility monitoring.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ENTECH, Inc.
1077 Chisolm Trail
Keller, TX 76248-7000

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Auburn University
231 Leach Center
Auburn University, AL 36849-5320

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mark O'Neill
mjoneill@entechsolar.com
1077 Chisolm Trail
Keller,  TX 76248-7000

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ENTECH, Auburn, NASA, and others have recently developed a new space photovoltaic array called the Stretched Lens Array (SLA), offering unprecedented performance (>80 kW/cu.m. stowed power, >300 W/sq.m. areal power, and >300 W/kg specific power) and cost-effectiveness (>75% savings in $/W compared to planar arrays). SLA achieves these outstanding attributes by employing flexible Fresnel lenses for optical concentration (e.g., 8X), thereby minimizing solar cell area, mass, and cost. SLA's small cell size (85% less cell area than planar high-efficiency arrays) also allows super-insulation and super-shielding of the solar cells to enable high-voltage operation and radiation hardness in the space environment. Recent studies show that SLA offers a 3-4X advantage over competing arrays in specific power for many NASA Exploration missions, and that SLA is ideally matched to Solar Electric Propulsion (SEP) applications, which can save NASA >$10 billion for lunar exploration cargo transportation. In Phase II, ENTECH and Auburn will perform critical ground tests, including an advanced solar concentrator (1 kW, 600 V, color-mixing lenses, multi-junction cells) direct-driving a Hall-effect electric thruster, and SLA/thruster plume interaction tests. After Phase II, SLA for SEP technology will be ready for flight testing in preparation for many NASA, DOD, and commercial missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The 600 V Stretched Lens Array (SLA) for Solar Electric Propulsion (SEP) technology being developed under this STTR program will have major applications for near-term and far-term NASA Exploration Missions. One major NASA application is SLA for SEP technology applied to reusable cargo tugs, not only for near-term robotic and human missions to the moon, but also for longer term missions to Mars and beyond. One reusable cargo tug using SLA for SEP technology can save NASA over $3 Billion in launch costs alone, compared to conventional chemical propulsion delivery of 110 metric tons of cargo to the lunar surface over a five year period. Other NASA applications of SLA for SEP technology include orbit maintenance for the International Space Station, orbit raising or lowering of spacecraft for science missions in orbit about the earth, moon, planets, or asteroids, and primary propulsion for large-scale deep space science missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Many additional non-NASA applications for the proposed SLA for SEP technology also exist, from LEO to GEO orbit raising for commercial communication satellites to repositioning of DOD space assets to meet specific mission requirements. In addition, several of the new entrepreneurial space and near-space companies are working with our SLA team on near-term large-scale commercial applications of the high-voltage radiation-tolerant SLA for both their SEP and their non-SEP missions. Finally, the Missile Defense Agency (MDA) is also funding development of the radiation-hardened SLA for critical National security applications in space, including DOD spacecraft capable of withstanding the effects of man-made threats, including ground-based lasers or nuclear detonations in low earth orbit. SLA offers unique and substantial survivability benefits over all competing solar array technologies for critical future National security space missions.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Powder Solutions
10010 Cucklebur Circle
Houston, TX 77095-6964

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Northwestern University
633 Clark Street 2-545
Evanston, IL 60208-2900

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dean Baker
stbaker2000@cs.com
10010 Cucklebur Circle
Houston,  TX 77095-0001

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
During the phase I program Northwestern and APS, Inc., have manufactured several different materials systems that are lighter than Beryllium and stiffer than Aluminum. These high specific strength materials are also easily fabricated into larger shapes or even net shape processed. The mechanical (tensile and modulus) and thermal physical (CTE, thermal conductivity) property data for several systems never before manufactured, will be presented as well as fabricated coupons, mirrors, structures and other parts will be available for review. Several different diameter parts ranging for 3" to 11" have been demonstrated. These various extremely lightweight systems are easily machined, threaded/joined and have highly variable properties, including variations of thermal conductivity, and radiation hardening/protection capabilities. Phase II will continue with this success for mirrors an dlightweight structure.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Other applications where newly developed high stiffness, light weight materials are desirable include UAV and ultralight airship applications. UAV payloads are extremely mass sensitive and therefore would benefit from stiff, yet light materials that can be readily machined into optical components and structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Lightweight structure, mirrors, insulation, shielding, HES, TAFIR, and Next genreation shuttle

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Decisive Analytics Corporation
1235 South Clark Street, Suite 400
Arlington, VA 22202-4361

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Louisiana State University
Office of Sponsored Programs, 330 Thomas Boyd Hall
Baton Rouge, LA 70803-0001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Fiske
david.fiske@dac.us

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Our proposal and the Phase I work completed under it addressed these NASA-identified needs by providing software infrastructure that provides physical scientists a "plug-and-play" architecture in which they can insert their "physics kernels" and exploit very large existing code bases for the computer science aspects of the problem. In particular, our STTR product provides cutting-edge adaptive mesh refinement (AMR) capabilities, and our Phase I results demonstrate the ability of our software architecture to run existing physics code with the newly incorporated AMR driver. Our innovative solution to the problem delivered significant value to NASA at a relatively small cost by combining existing open source tools. In Phase I, we built an interface, which we call Parca, between the Paramesh computational libraries, developed at NASA GSFC to support AMR computations in the area computational hydrodynamics, and the Cactus computational toolkit, which is an infrastructure package developed by Louisiana State University that provides a "plug-and-play" framework for cross-institution and cross-disciplinary scientific codes. Both of these software packages have large user bases in the areas of computational fluid dynamics and numerical general relativity, and both had existing users at NASA GSFC. Prior to our Phase I work, there was no way these user communities to collaborate directly, leading each user group to redevelop software already available in the other user community.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
We have a three-thrust Phase III plan that include both entering new business areas and including the Parca brand software developed under this proposal to our existing business areas. Each of the three thrusts, (1) Parallel Scientific, (2) ComputinSensor resource management and mission planning, and (3) Science and engineering applications of MHD have applications in NASA. In particular, the LISA mission already has concrete plans to use our software starting with integration of the Phase I product almost immediately. In addition, the proposal lists customers in the DOD and DHS with who we already have contract or with whom we have pending proposals who are potential customers for this software.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
By combing the Parca software developed under this proposal with existing technologies developed under other funding, DAC will transition software developed under the Phase I and Phase II contracts to customers in the Department of Defense and the Department of Homeland Security. The applications include the dynamic and automated planning of routes for UAVs, and the placement of chemical and biological sensors for both military and homeland defense applications. In addition, DAC will begin entering the scientific computing market by offering "premium service" applications on top of open source community software tools. These services will augment the existing scientific software and make it more accessible to a wider user community.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Agave BioSystems, Inc.
PO Box 80010
Austin, TX 78708-0010

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Universities Space Research Association
10211 Wincopin Circle, Suite 500
Columbia, MD 21044-3432

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joel Tabb
jtabb@agavebio.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In completing the Phase I SBIR, Agave BioSystems and the Universities Space Research Association, have successfully demonstrated proof of concept for the use of novel carbon nanotube (CNT)-based structures as next generation smart adsorbents for the adsorption and destruction of potentially toxic air contaminants. Since CNTs have an extremely high surface area, can be readily modified with metals or functional groups, and can function without the mass transfer limitations of traditional activated carbon, they are an ideal material for integration into spacecraft air handling systems. In the Phase II program, we will build upon the unique structural and chemical nature of carbon nanotubes to construct a prototype system utilizing these smart adsorbents.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's next generation spacecraft will have a totally redesigned air purification (or climate control system) and a major concern is that this system will not be able to deal with the low levels of ammonia and carbon monoxide generated during long space flights. Therefore, in addition to adsorption and degradation of VOCs, the development of a versatile CNT-based system that can be used to adsorb and release ammonia, and also remove CO by oxidizing it into CO2 would be ideal. In addition to routine removal of low ambient level CO produced through normal metabolic activity, a second important operational scenario is an excursion with high CO levels, > 10 ppm possibly greater than 100 ppm, arising from a fire. For this situation, a catalyst with high activity and storage capacity, such as this novel CNT-based system, is critical to reduce high transient levels within minutes before incapacity or death occurs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
An example of the commercial importance for CO removal is in fuel cell power generation. Generally in fuel cells, the reformate gas typically contains 0.5 – 2% by volume CO. It is imperative to lower the concentration of CO because it is a catalyst poison for the gas-diffusion anode. Volatile organic compounds present one of the major environmental problems today. Filters for airborne particulate matter are essential in many instances, including air purifiers, respiratory protection equipment and clean rooms. In the manufacturing sector, semiconductor manufacturing requires ultra-high filtration. Applications for this technology include indoor filtration systems to remove VOCs from indoor air streams, personal protective gear for workers exposed to occupationally high levels of industrial chemicals, and equipment for military personnel, firefighters and other public health officials who may come into contact with toxic air contaminants while dealing with the aftermath of industrial spills and leaks.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
HPN Software Consultant, Inc.
18519 Egret Bay, Suite 1509
Houston, TX 77058-3353

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Stanford University School of Medicine
701A Welch Road, Suite 1128
Palo Alto, CA 94304-0000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
lac nguyen
lac.nguyen1@jsc.nasa.gov
18519 Egret Bay, Suite 1509
Houston,  TX 77058-3353

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In integrating the following three significant components for its research/research and development (R/R&D) effort, the power of this candidate Phase II project will be demonstrated and developed the following 1. Software Application Development Toolkit for Simulation and Training 2. Physiological Hardware/Software Interface for Dynamic Balance Trainer. 3. A Data Glove and control system captures the motion of the Robonaut hand and finger The multi-faceted CVEST development environment operates as a plug-and-play interface to various software and hardware products specializing in virtual reality-based simulation development. The final Phase II demonstration will feature to show the CVEST toolkit for the CEV Seat design concept This STTR Phase II candidate project will concentrate on some new physiological hardware/software devices to produce a Dynamic Balance Trainer System to improve Post-flight Locomotor Performance. Lastly STTR Phase II candidate project will develop and demo a prototype concept device to capture the positional and rotational of the Robonaut hand

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
o Virtual CEV cockpit design o Virtual Emergency scenarios based on doffing/donning of space suit in the CEV cockpit o Enhancement of the Dynamic Balance Trainer to Improve Post-flight Locomotor Performance o Assembly of Space Station truss sections o Inspection, analysis/planning, and maintenance/repair of Space Shuttle tile and other protective systems o Exploration, remote mission operation, and data/sample collection sample from other planet by Robonaut o Extravehicular missions (space walk, truss repair, solar array correction, etc.) assisted by Robonautic systems

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
SubSea's ROV technologies will be able to perform the following capabilities: Underwater exploration Underwater pipeline laying and deployment CVEST simulations that would feature the following: Robonaut assisting a virtual Fire Fighter in performing hazardous tactics where humans could be threatened by fire and/or smoke exposure Robonaut rescuing victims from building collapse

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Sensor Research & Development Corporation
Unit 2, 1195 Baltimore-Annapolis Blvd.
Arnold, MD 21012-1808

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Central Florida
4000 University Boulevard
Orlando, FL 32816-8005

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Leland Solie
leesolie@asrdcorp.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the continued development of passive wireless surface acoustic wave (SAW) based liquid level sensors for NASA application to cryogenic liquid level sensing. Orthogonal Frequency Coded (OFC) SAW devices have been demonstrated as passive wireless temperature sensors in NASA Contract NNK04OA28C, and are being further developed under NNK05OB31C. The liquid level sensors use damping of the acoustic wave caused by mass loading of the liquid to produce fast, reversible liquid level sensors. The Phase I research successfully demonstrated operation of these devices as liquid level sensors in selected liquids of interest at cryogenic temperatures. Stability of selected commercially available SAW devices was confirmed, both when exposed to various (extreme and gradual) temperature changes, and upon repeated exposure to liquid nitrogen. The reversibility of the device response was confirmed. Phase I demonstrated the technical feasibility of using these sensors for cryogenic liquid level monitoring of low to moderate pressure liquids (under 500 psi). Phase II will result in prototype product development.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application for the proposed sensors would be in a wireless multisensor system for liquid level measurement in storage tanks for cryogenic liquids. With uniquely identifiable sensors, this system could use low cost sensors mounted at numerous levels within a tank to remotely detect the presence (and therefore for terrestrial tanks the level) of liquid within the tank. Wireless sensor interrogation requires only one tank penetration for the transceiver antenna, minimizing heat transfer pathways. Resolution of liquid level is fine due to small sensor size. The proposed sensors could also monitor temperature in the headspace above the liquid.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
While the market size for potential applications needs to be evaluated, it is clear that the proposed sensors can be used commercially for liquid level monitoring within storage tanks for volatile liquids, and to monitor temperature in the headspace above such liquids. Since OFC SAW sensors operate over a wide range of temperatures, commercial applications may include both cryogenic and higher temperature liquid storage. Passivation of the sensor surface may make this approach feasible for use in caustic volatile liquids. Reversiblity of sensor response when the liquid level in the tank drops requires the liquids monitored to be volatile.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Sensor Research & Development Corporation
Unit 2, 1195 Baltimore-Annapolis Blvd
Arnold, MD 21012-1808

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
University of Central Florida
4000 Central Florida Boulevard
Orlando, FL 32816-8005

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jacqueline Hines
jhines@asrdcorp.com
1718 Winchester Rd.
Annapolis,  MD 21409-5851

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the continued development of passive orthogonal frequency coded (OFC) surface acoustic wave (SAW) based hydrogen sensors for NASA application to distributed wireless hydrogen leak detection systems. These novel sensors use an OFC SAW device structure, combined with Palladium (Pd) nanocluster film elements and hydrophobic self assembled monolayer (SAM) coatings to produce fast, reversible, highly sensitive hydrogen sensors capable of detecting a wide range of hydrogen concentrations at room temperature. The technical feasibility of these sensors was clearly demonstrated in Phase I. The Pd films experience conductivity changes due to the hydrogen induced stretching of the Pd nanoclusters and the quantum nature of conduction in nanocluster films. The performance of the SAW device will change in response to a change in conductivity of this film. Rapid (under 1 second) room temperature detection of hydrogen was observed, with complete reversibility of response. Compatibility of film conductivity with acoustic wave propagation and detection of changes in film conductivity using variations on SAW device delay were confirmed. Manufacturing compatible processes for SAM deposition and patterning were developed. The successful elimination of the potential technical risks accomplished in this Phase I effort provides a sound basis for further development of these sensors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA application for the proposed sensors would be in a wireless multisensor system for hydrogen leak detection. With uniquely identifiable sensors, such a system could use low cost sensors mounted at numerous locations to remotely detect hydrogen leaks in real time. This system could continuously monitor "boot" air for leaks, and remotely alert personnel and/or trip alarms or initiate protective action if a leak is detected. The extreme sensitivity of these films to low levels of hydrogen, and their ability to operate reversibly without baseline drift at room temperature, should provide an advanced warning capability for leaks.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial market for the proposed hydrogen sensors is extremely promising. Sensors will be needed for hydrogen leak detection in hydrogen storage, transport, and distributed hydrogen forming facilities, and for residential and automotive fuel cell applications. Use of hydrogen as a fuel for automotive and fleet vehicles is already emerging. Major automotive manufacturers see residential and industrial fuel cell use as a means to increase production volumes and lower costs. The high sensitivity, fast response times, reversibility, wide range of hydrogen concentration sensed, low cost, and small size would make the proposed sensors applicable to these emerging market segments.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Ceramics Research, Inc.
3292 E. Hemisphere Loop
Tucson, AZ 85706-5103

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Arizona Board of Regents, University of Arizona
888 North Euclid Avenue, #515
Tucson, AZ 85719-4824

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Andrew Osbrink
aosbrink@acrtucson.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Our proposed future Phase II activities are aimed at developing a scientifically based "tool box" for flight research using scaled models. These tools will be of great use for GA companies in the design, development, and FAA approval of future general aviation (GA) aircraft, in particular also when novel technologies such as active flow control, circulation control, etc. are being considered. We will demonstrate that time, cost, and risk associated with the development and flight testing of future GA aircraft and GA relevant technologies, can be greatly reduced by performing part of the flight research program using dynamically scaled models. As part of the proposed activities we will design, construct, and perform flight research with a 1/3 dynamically scaled model of the Cirrus SR22.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed "tool box" for scaled model research (dynamically scaled models, CFD and FE codes, high performance computing, wind and water tunnel capabilities) will be of great use for NASA and fits perfectly with respect to NASA's strategic goal to develop new technologies for general aviation, e.g., for achieving a breakthrough with regard to efficiency, affordability, safety, etc. (as expressed by NASA's strategic sub-goal 3E and NASA's Research Opportunities in Aeronautics program). NASA is already developing dynamically scaled modeling technology focusing on large passenger airplanes (Boeing 757). Emphasis of the NASA program is on studying the post-stall and spin dynamics of large transport airplanes.Therefore, with our focus on GA aircraft (allowing larger scaling of the models) considerable synergisms could result from our collaboration with NASA. NASA also has a strong interest and many research activities in passive and active flow control. The proposed flight test program using scaled aircraft for investigating flow control strategies will therefore enable collaboration with NASA in this area.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
With the tools, expertise, resources, and capabilities developed in Phase II we will be able to provide "Services for Scaled Flight Research". We will first focus on the needs of GA companies and provide state-of-the-art scaled flight research services. We will offer all necessary tools (dynamically scaled modeling, CFD and FE codes, high performance computing, wind and water tunnel tests) and will thus provide services to GA companies in the development of new products and technologies. Thus we can offer scientifically based scaled flight research services prior to prototype development. The immediate goal is to focus on the GA industry for small aircraft (4-6 passengers) with the Cirrus SR22 as a prototypical current, state-of-the-art airplane in this category (Cirrus already suggested an immediate use of our proposed scaled model approach for investigating stall/spin entries and a look at the effect of leading edge droop on spin resistance). Then we plane to move down and up the scale, for example: light sport aircraft (LSA, 2 passenger single engine), twin engine very light jets (VLJ, 4-8 passenger jets), business jets, and small regional jets. Small GA companies generally do not have the experience and resources to develop such scaled model testing expertise because it would not be economically sensible since development and testing is only needed at certain phases of airplane development.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Luna Innovations Incorporated
1703 South Jefferson Street, SW, Suite 400
Roanoke, VA 24016-4909

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Virginia Polytechnic Institute and State University
460 Turner Street, Suite 306
Blacksburg, VA 24060-3362

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Roger Duncan
duncanr@lunainnovations.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In the future, exploration missions will benefit greatly from advanced metrology capabilities, particularly structural health monitoring systems that provide real time in-situ diagnostics and evaluation of structural integrity. Safety- and mission-critical components and systems will be instrumented with embedded sensors to provide a real-time indication of health, helping to ensure that America's space exploration remains safe and cost efficient. One of the most promising technologies for accomplishing this is fiber-optic sensors. Due to their light-weight and multiplexing potential, fiber-optic sensors are highly desirable for employment in this fashion. However, most commercial fiber-optic sensor interrogators are bench sized units and are too large and heavy to be easily integrated for space-based applications. To address this shortcoming, Luna Innovations proposes to develop a compact, light-weight, multi-parameter distributed fiber-optic instrumentation system based on the OFDR technique. The interrogator will incorporate photonic integrated circuit technology, a highly integrated swept-wavelength laser, and state-of-the-art integrated processing technology to dramatically reduce the size, weight, and cost and to dramatically increase the performance and robustness relative to existing technology. This interrogator will interface with fiber-optic strain, temperature, and shape sensor arrays, enabling simultaneous interrogation of a multitude of sensors, dramatically reducing the per sensor cost of instrumentation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The interrogator as well as the sensors will be designed to perform in the high-stress and hostile conditions expected on launch vehicles and space environments. The resulting miniaturized, ruggedized device will thus be capable of operation in high-vibration environments, resulting in a high-reliability device that will have great utility as a portable multi-parameter sensing unit. Such instrumentation could continuously provide distributed strain, temperature, and shape measurements in a space environment. Strain measurements, for example, could yield information on highly-stressed or fatigued structural members, enabling condition-based maintenance of the crew exploration vehicle or composite over-wrapped pressure vessels.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The resulting instrumentation system is expected to be extremely attractive in a number of commercial applications. For example, the long term monitoring of civil structures using sensor arrays would be enabled by a permanently installed interrogator. In addition, technology is expected to find use in many health monitoring applications as a sensing network in air-, land-, and sea-based military vehicles. The proposed instrumentation is also expected to have applications within the medical field, permitting the deployment of Luna's novel shape sensing capability for tracking the relative position of catheters and colonoscopes used for minimally invasive medical procedures.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
HyPerComp Engineering, Inc.
1080 North Main, Suite #2
Brigham City, UT 84302-0505

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Utah State University
1415 Old Main Hill
Logan , UT 84322-1415

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jared Noorda
jaredn@hypercompeng.com
1080 North Main, Suite #2
Brigham City,  UT 84302-1470

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The intent of the proposed effort is to investigate the detailed composite material performance characteristics after being subjected to cryogenic temperatures and impact damage. HyPerComp Engineering, Inc. (HEI) and Utah State University (USU) further propose to correlate these characteristics to composite overwrapped pressure vessels (COPVs) and demonstrate the correlation through actual COPV testing. This will result in a safer, more reliable design for high performance COPVs in a cryogenic environment. HEI and USU also propose to study the cryogenic bond necessary between composites and aluminum for thin walled aluminum lined COPVs to prevent the buckling of the aluminum during depressurization. This intent will be demonstrated by actual pressure vessel testing.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications for the research proposed herein would include the following: • Cryogenic storage vessels. The research proposed herein is applicable to earth-based and space-based cryogenic storage vessels. • Habitat structures. The research proposed herein is applicable to space-based habitat and other structures manufactured with fiber-reinforced composite material. • Space-based cryogenic COPVs. It is probable that COPVs utilized in space will experience impact damage due to micrometeoroids and other space debris. The research proposed herein will assist the COPV designer by identifying the effects of impact damage and developing mechanical property allowables for the designer. • Thin walled aluminum COPVs for cryogenic storage. The research proposed herein will assist the development of maintaining the bond between composite and thin walled aluminum to prevent the aluminum liner buckling during depressurization.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA commercial applications for the research proposed would include the following: • LH2 fuel cell. HEI is currently executing a contract for LH2 storage for a vehicle application. In fact, HEI has completed six (6) other contracts for similar applications. The research proposed herein will aid the mobile fuel cell industry safety and reliability. • Vehicular CNG storage. HEI have completed as many as ten (10) contracts for CNG storage applications. These applications were primarily for vehicular applications. The research proposed herein will aid the safety and reliability of the CNG vehicle market. • Environmentally-friendly earth-based cryogenic fluid storage. Composite structures do not react to environmental corrosion as do the typical cost efficient metals such as steel. Therefore, composite structures do not require painting, paint stripping, and repainting which is very unfriendly to our environment. • Safer earth-based cryogenic fluid storage. Due to the high strength of composite materials, little raw material is required to perform draconian structural feats when compared to typical cost efficient metals. Therefore, the manufacturing and movement of large composite pressure vessels is much less expensive and much safer to the technicians performing the manufacturing and moving of such vessels.

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Mississippi State University
Box 9637 300 Butler Hall
Mississippi State, MS 39762-9637

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Sarma Rani
sxh@cfdrc.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Radiative heat fluxes are important in the design of launch vehicles for Project Constellation. In this Phase II STTR, CFDRC and its partner Mississippi State University will develop an innovative, comprehensive, high fidelity radiation module in the LOCI CFD framework that will enable NASA to design/analyze heat transfer challenges that include radiation. In Phase I, CFDRC/MSU successfully demonstrated the feasibility of developing a radiation module in LOCI-Chem. A preliminary module was developed that included a gray gas model, as well as simplified nongray gas and particulate radiation capabilities. Following successful implementation and validation, LOCI-Chem with the radiation module was successfully applied to a Solid Rocket Motor (SRM) plume on a launch pad as a demonstration case. The proposed Phase II effort continues the development by: 1) implementing more accurate, robust nongray gas and particle radiation models, 2) increasing tool-fidelity by developing innovative methodologies to minimize modeling uncertainties, 3) formally verifying the module using the Method of Manufactured Solutions (MMS), and 4) validating the module and applying it to cases of direct relevance to NASA. NASA, ATK, and Pratt & Whitney Rocketdyne will be beta testers of the software in Phase II, and provide user feedback. At the end of Phase II, a final version of the software with full documentation will be delivered to NASA.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The LOCI radiation module will enable NASA and government contractors to design and analyze rocket engine flows with gaseous and particle radiation. As part of Project Constellation, NASA/MSFC is embarking upon the design of Ares launch vehicles, in which radiative heat fluxes from the solid rocket booster (SRB) plume to the launch pad must be considered. For Ares-V, challenges exist in simultaneously predicting the multiple plume environments, including gas-generator dumps, RSRM-V plume and overall heat transfer to the base of the first stage. These and other applications involving radiative heat transfer can be successfully analyzed by the end of Phase II.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The LOCI-Chem radiation module will have a wide appeal to rocket engine manufacturers and universities developing rocket engine technology (e.g., Purdue, Penn State, UAH, etc.) under the CUIP Program. The LOCI suite of codes (e.g., LOCI-Chem, LOCI-Stream, etc.) has become an important design/analysis tool at NASA, and NASA's primes are beginning to show interest and use the LOCI codes, such as ATK, Pratt & Whitney, and Aerojet. A support letter is included from ATK, showing their intent of assessing the LOCI-Chem radiation module. A stand-alone radiation module will also be developed for commercialization in other CFD codes. Pratt & Whitney Rocketdyne has expressed interest in implementing the stand-alone radiation module into their in-house CFD code, and purchasing the module following successful demonstration (support letter included). Another source of revenue will come from implementing the radiation module into CFDRC's DREAM code, a next generation combustion LES code for gas turbine combustor/augmentor analysis.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Sierra Engineering, Inc.
603 E. Robinson Suite 7
Carson City, NV 89701-4046

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Purdue University, Sponsored Program Services
302 Wood St.
West Lafayette, IN 47907-2108

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Curtis Johnson
cwj@sierraengineering.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Sierra Engineering Inc. and Purdue University propose to develop a non-intrusive plume instrument capable of detecting and diagnosing combustion instability. This Stability Diagnostic System (SDS) will be designed, assembled, and tested during this effort. The SDS will include a high-speed video camera and multiple photodiode detectors for observing the plume. It will also include a software package, which will aid in analyzing the plume data and in determining the acoustic modes of the instability. To ensure that the system works properly, Sierra and Purdue will leverage an oxygen/kerosene combustor, developed under AFRL funding, to operate with unstable combustion. Technology previously developed at Purdue will be used to modify the engine's injector so that the combustion instability occurs. The dirty (soot laden) plume produced by this combustor better simulates the conditions present in full-scale hydrocarbon fueled engines. Finally, the methodology for predicting combustion response from plume observations, developed under the Phase I effort, will be matured. The SDS system and accompanying software will be delivered to NASA for future application on NASA test facilities. Successful completion of this project will provide a non-intrusive tool for detecting and diagnosing combustion instability that is superior to current, intrusive methods.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Current NASA roadmaps point towards development of new hydrocarbon fueled engines. Whether the new engines use kerosene or methane, both fuels have led to unstable combustor designs in the past; therefore, combustion stability will be important to NASA in the future. Improved combustion stability diagnostic tools, especially ones that are non-intrusive to the combustor hardware, can be an important part of this future development. If the technology proposed here works, complete combustor bomb test campaigns (which can be dangerous) may be eliminated with potential cost savings of millions of dollars. Application of this technology to other combustion issues, such as combustion efficiency, can improve engine-specific impulse, which would improve overall CEV performance.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Successful application of this technology can be important to many other organizations that develop combustors, not only those in liquid rocket engines. Combustion stability has plagued solid rocket motor development as well as air breathing aircraft engines and commercial burners. An improved methodology to assess stability margin and diagnose problems could be applied throughout the combustor industry. The Missile Defense Agency is also researching more accurate ways of typing threat missiles. Data and instrumentation design developed in this effort could be directly used in developing new typing instrumentation and methods based on high frequency intensity variation. Entrepreneur rocket company developers often have many resources at their disposal, but ability to assess and solve combustion stability problems is not one of them. A stability diagnostic system will be very valuable to these organizations as they are confronted with the stability issue.

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Massachusetts Institute of Technology
77 Massachusetts Avenue
Cambridge, MA 02139-4301

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Olivier de Weck
deweck@mit.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Payload Systems Inc. (PSI) and the Massachusetts Institute of Technology (MIT) were selected to jointly develop the Rule-based Analytic Asset Management for Space Exploration System (RAMSES) in this NASA STTR project. This system implements a modular layered architecture that enables automated multi-level asset tracking and management for both space and ground applications based on state-of-the-art RFID technology. The main advantages of this system over current bar-code based asset tracking are: (i) significant time savings through automation, (ii) real-time remote status monitoring through the internet, and (iii) rule-based analytics for proactive asset management. In Phase 2 we propose to redesign the Smart Container by taking advantage of Generation 2 RFID tag technology, lightweight RFID readers and batteries as well as integrating container technologies in a more tight and robust manner. We plan to build a total of three (3) smart containers to demonstrate scalability of the system and interaction among containers. The RAILS software will be upgraded to provide enterprise-level capabilities such as user authentication, inventory and item time history analysis, and an expanded analytic rule set. Testing will be conducted both in the laboratory and in the field to demonstrate seamless three level tracking (container level, room level, outdoors). Finally, we will perform a detailed RAMSES cost/benefit analysis and market survey in preparation for Phase 3.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The design-driving NASA commercial application for the RAMSES system is for asset management for space exploration systems. Primarily, this is aimed at ISS, Lunar, and later Mars exploration with human crews. NASA commercial applications also abound for Earth-based implementations, which are also within closer reach due to the less stringent technical and certification requirements. The architecture of RAMSES can be easily adapted to other applications that involve multiple distributed assets, agents with extraordinary time and resource constraints, and the need for comprehensive data logging and database management.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
We anticipate that there are other applications that are more near term both within NASA and beyond, and in military and commercial sectors. The system could be used for humanitarian aid in remote locations, military outpost establishment, and remote exploration bases on Earth. The system could also be used in the planning and management of assets in complex search and rescue scenarios. Generally, RAMSES excels when the movement of assets is somewhat dynamic, unpredictable and where it occurs across multiple levels (in and out of containers, shelves, rooms, etc.).