NASA 2004 SBIR Phase 1 Solicitation

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
PRAGMASOFT, INC.
130 Elsmere Ave.
Delmar, NY 12054-4310
(518)439-8815

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
J. Scott Merritt
sbir@pragmasoft.com
130 Elsmere Ave.
Delmar, NY 12054-4310
(518)439-8815

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal responds to the urgent need for improved pilot interfaces in the modern aircraft cockpit. Recent advances in aircraft equipment bring tremendous resources within the reach of the today's pilot. Unfortunately, these advancements are often accompanied by increases in system complexity and pilot workload. In many cases, the detailed interaction required by modern avionics significantly interferes with the pilot's need to scan instrument gauges, maintain visual separation from other aircraft, and attend to other critical tasks.

To address these concerns, PragmaSoft's proposal combines innovations in robust speech recognition and interface design with powerful application language constraints to deliver highly effective voice interface solutions. Development efforts are carefully target at high workload pilot tasks to ensure substantial benefits and commercial acceptance. Initial product sales are leveraged to collect an extensive corpus of actual (in-flight) speech and operational data for subsequent research and development.

PragmaSoft believes that the lengthy and focused attention required to operate some aircraft devices presents an unacceptable safety risk to flight operations. The proposed innovations deliver effective and commercially attractive voice interface solutions that allow pilots to interact with their cockpit environment in a safer and more efficient manner.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Under subtopic A1.01, NASA requests "innovative technologies to improve airspace safety with a crew-centered focus ... [and] high potential for emerging as marketable products". PragmaSoft's proposal directly addresses this need by delivering advanced speech recognition technology that is commercially attractive to a wide spectrum of aircraft operators, and yields immediate benefits in safety and efficiency.

NASA's Small Aircraft Transportation System (SATS) program includes a mandate to demonstrate improvements in the ability of single pilots to function competently in complex airspace. This proposal provides an exceptional opportunity for NASA to demonstrate additional capability in support of these objectives.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed innovations deliver commercially attractive, speaker-independent, voice interface products that significantly enhance the safety and efficiency of advanced flight operations. Initial products are carefully targeted to specific applications to ensure substantial benefits and commercial acceptance. Non-certified versions of the product are configured for convenient use in a wide variety of aircraft, while certified versions are provided for permanent installation. The persuasive cost/benefit profile of these products ensures that a wide spectrum of aircraft owners and operators will finally enjoy the benefits of advanced speech recognition technology.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
PHYSICAL OPTICS CORPORATION
20600 Gramercy Place, Building 100
Torrance, CA 90501-1821
(310)320-3088

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Ranjit Pradhan
sutama@poc.com
20600 Gramercy Place, Building 100
Torrance, CA 90501-1821
(310)320-3088

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
To improve aviation safety, NASA requires crew-centric technologies that ensure appropriate situational awareness through improved information presentation. Presenting information by 3D display can significantly facilitate human perception and counteract biases and error-tendencies, leading to improved aviation safety. To address this NASA need, Physical Optics Corporation (POC) proposes to develop a new 3D COckpit Display (3D-COD) system for aircraft flight decks, based on fast scanning liquid crystal (LC) optics, to create a compact multiuser, multiperspective 3D display system that has no moving parts and requires no 3D glasses. This interactive system brings automultiscopic viewing to pilots and crew members on the flight deck, with a greater than 60 degree FOV, 2048x2048 resolution, 60 Hz flicker-free full-color, high-brightness, and crosstalk-free operation, introducing 3D display technology to the cockpit. The use of LC technology well developed for flat-panel LC displays, reduces cost and makes the system commercially attractive. In Phase I POC will develop a scaled-down version of the fast-scanning LC optics display system and demonstrate its 3D operation on a laboratory 3D testbed system. This testbed will be upgraded to a fully packaged optimized prototype in Phase II.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed 3D-COD display system will be used not only in the cockpit, but also for air traffic control, training, and multicraft airspace image displays, engineering design, training and simulation, and scientific visualization and analysis.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The 3D-COD technology has huge commercial potential. It will find applications in the engineering development and entertainment industries, particularly in theme parks, museums, and educational institutions. This technology can also address the multibillion dollar video game industry.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Metron Aviation, Inc.
131 Elden Street, Suite 200
Herndon, VA 20170-4758
(703)456-0123

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Terry Thompson
thompson@metronaviation.com
131 Elden Street, Suite 200
Herndon, VA 20170-4758
(703)456-0123

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Command and Control (C2) activities abound in the NAS, and significantly influence daily operations and overall NAS efficiency. Since C2 effects are so prominent, development of new operational concepts, and evaluation of proposed changes, requires simulation and modeling capabilities that include C2 effects. Metron Aviation leverages its extensive knowledge of the Command and Control (C2) functions of the National Airspace System (NAS) to develop models that enable realistic NAS simulations. The key innovations of this effort are 1) the implementation of models for NAS ATM C2 processes, and 2) the integration of these models with the NASA Langley Systems Analysis Branch's (SAB) Simulation Environment. The development leverages the following key capabilities: Metron Aviation's extensive experience supporting NAS C2 activities, and Langley's infrastructure for conducting NAS-wide simulations of air traffic. By developing this interaction we enable a system that allows researchers and analysts to evaluate current NAS operations and to investigate future technologies and concepts of operations. These users exploit the system's capabilities to observe NAS behavior and compare the benefits and impacts of operational concepts prior to pursuing implementation in the operational system.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Understanding of the system-wide impacts of NAS Command and Control is lacking in both operational practice and current research. This understanding is crucial for the evaluation of current/proposed future operations. Currently, NASA programs such as the Virtual Airspace Modeling and Simulation (VAMS) and the All-weather Capacity Enhancement NRA are developing system concepts to meet increasing air-traffic demand, reduce delays and improve safety/security. While evidence suggests that these techniques may provide significant benefit, NASA must accurately assess tradeoffs between such benefits and costs of implementation. Realistic NAS-wide simulations, including C2, are required to assess such operational concepts and technologies.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Estimates of ATM costs due to delays range from hundreds of millions of dollars to billions of dollars per year. Several research activities are being pursued to develop new concepts and technologies in an effort to meet the increasing demands. Many of these developments promise to be costly and laborious to implement, and the difficulty of adequately assessing the anticipated impacts creates significant risk operators and users of the NAS. Development of simulation capabilities and benefit assessment methods that include the effects of C2, creates significant commercial demand for accurate and robust C2 modeling capabilities.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
AEROTECH RESEARCH
11836 Fishing Point Drive, Suite 200
Newport News, VA 23606-4507
(757)723-1300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Paul A Robinson
paulrobinson@atr-usa.com
11836 Fishing Point Drive, Suite 200
Newport News, VA 23606-4507
(757)723-1300

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aircraft encounters with turbulence are the leading cause of injuries in the airline industry and result in significant human, operational, and maintenance costs to the airline community each year. A large contributor to the above injuries and costs is that flight crews do not have sufficient situational awareness of the location and severity of potential turbulence hazards to their aircraft. AeroTech will improve pilots' situational awareness of turbulence hazards by developing an integrated, graphical cockpit display of turbulence hazard information scaled to their specific aircraft. This display will negate the need for inference that is required to interpret current turbulence information. With better knowledge of turbulence hazards' severity and location, pilots will be able to avoid turbulence encounters or prepare for them by having all occupants seated with seatbelts on, thereby avoiding injuries. Phase I work will develop, based on pilot input, a concept of operations and a requirements document for this display, evaluate several potential turbulence hazard information sources, and define requirements for simulations to be carried out in Phase II. By the end of Phase II an intuitive and meaningful cockpit, turbulence hazard display will be developed and tested using simulations and operational flight evaluations.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
When the goals of the proposed R/R&D are met, this cockpit display and underlying system will directly contribute to the stated national goal of NASA's Aviation Safety Program (AvSP) of a 50% reduction in aviation accidents by 2007. This work will be completely aligned with other Turbulence Prediction and Warning System (TPAWS) efforts, as well as other efforts in the Weather Accident Prevention (WxAP) element.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
When the goals of the proposed R/R&D are met, this cockpit display system will provide pilots with improved turbulence hazard information allowing them to operate more efficiently and safely. Significant reductions in fuel waste and costs associated with injuries due to turbulence are expected to be major commercial drivers for this system. The market for this display is all Part 121 carriers (both domestic and international). Delta Air Lines is currently operationally evaluating several of the technologies whose outputs will be integrated into the proposed display and has also agreed to support the efforts of this proposal.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Cox and Company Inc.
200 Varick Street
New York, NY 10014-4875
(212)366-0200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Kamel Al-Khalil
alkhalil@coxandco.com
200 Varick Street
New York, NY 10014-4875
(212)366-0200

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal presents a dual approach to the development and certification of an alternative system for ice protection of turbine engine inlets. It combines a new generation low power ice protection system with a novel path to certification that is based upon requirements that turbine engines be capable of operation in a hail environment. Eliminated are requirements for high voltages and currents characteristic of all previous impulsive or expulsive deicing systems. It is postulated that if the engine can operate safely in the hail environment as defined by the FARs, then it can be expected to operate safely and economically in the presence of particles shed by the deicer which are demonstrably smaller and less hazardous than hail. Such a system presents a viable alternative to the use of hot air ice protection systems.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The system proposed is a viable alternative to bleed air ice protection for engine inlets. NASA has a national objective an overall improvement in the safety of aircraft operation. Protection of aircraft from exposure to icing environment is included in that charter. One of the most important trades involved in the development of icing conditions is between energy and icing performance. This trade has been shown that it can be addressed by the use of low power ice protection systems on lifting surfaces. It remains to apply these principles to engine inlets. This is the commercial promise of this system.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The system proposed is a viable alternative to bleed air ice protection for engine inlets. It should find wide application on turbine powered aircraft that are designed to achieve even greater efficiency of operation through the use of exclusively electrically powered systems, including ice protection. This "all electric airplane" concept has been under consideration for many years by NASA and other industry organizations. Indications gained from public disclosures by companies, especially Boeing, of the elimination of bleed air as a means of ice protection are firm indications of the intent to develop new technologies in support of more efficient aircraft.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Radiometrics Corp
2840 Wilderness Place, Unit G
Boulder, CO 80301-5414
(303)449-9192

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Fredrick Solheim
solheim@radiometrics.com
2840 Wilderness Place, Unit G
Boulder, CO 80301-5414
(303)449-9192

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aircraft icing continues to be one of the major safety and operational concerns of the FAA, elements of the military, and the foreign military and civilian counterparts. Attempts to develop methods to directly detect aircraft icing meteorological conditions have met with mixed success. Combining microwave radiometers with radars has shown great promise, but deficiencies of the radiometers have limited their value. In this proposed effort we will develop a fast sampling multifrequency profiling and dual polarization narrow beam radiometer system to overcome these deficiencies. In this proposed radiometer system, all beams are collinear and match the antenna gain pattern of weather research radars. The radiometer will have the capability of profiling (ranging) water vapor along the beam as well as discriminate ice and water phase hydrometeors. We will also develop a fast beam steering system to operate in concert with the radar. Phase II will produce a turnkey radiometric system, ready to deploy.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
NASA Glenn is actively researching methods of detecting aircraft icing conditions, and has performed and participated in a number of aircraft icing studies with their Twin Otter, radiometers, radar, and other sensing systems. The technology proposed herein greatly enhances the value of the important radiometric observations by enabling measurements that match the research radars at a number of radiometric frequencies.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The radiometric system developed herein, as well as being a valuable research tool, is to be operated with NEXRAD and Terminal Doppler Weather Radars (TDWRs) to detect and quantify cloud liquid water and ice in single- and mixed-phase conditions. In addition to detecting aircraft icing conditions, this quantification will enhance weather nowcasting and predictive capabilities.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2785
(301)294-5200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
George Zhao
xzhao@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2785
(301)294-5232

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Corrosion and fatigue induced metal-loss and cracks are common problems for missiles and aircraft structures. A wide range of field conditions such as humidity, temperature, stress, cathode potential, and coating conditions, etc. all contributes to the electrochemical reaction between the incipient corrosive agent molecule and the structural metal matrix. The weakened inter-atomic force leads to the material loss, pits or crack growth and eventually structural failure.

We propose a new approach to detect and characterize the corrosion and cracks in missile and aircraft structures. The technique consists of very small, low cost guided wave leave-in-place health monitoring sensors known as piezo-disks, innovative Correlation Analysis Technique (CAT) for fast defect sizing and localization, and a miniaturized local computing device with data acquisition and processing capabilities and wireless module for remote monitoring. It is envisioned the total cost of this system will be less than $1500.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The ability to detect and characterize the corrosion and crack in an early and accurate manner is critical for reducing cost and improving safety for many NASA systems such as propulsion system, aircraft frames and wings, etc. At the end of Phase 2, we will have a small, light weight, low cost, low power consumption and robust system with both hardware and software for defect detection and localization.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
In-situ health monitoring and fault diagnosis is equally important for many military and commercial systems such as aircraft, automobiles, trains, home appliances, nuclear reactors, etc. The system can either perform continuous monitoring for the critical high strength components or switch on-off when needed. We expect the market for this system to be at least 10 million dollars.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Metron Aviation, Inc.
131 Elden Street, Suite 200
Herndon, VA 20170-4758
(703)456-0123

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Jimmy Krozel
krozel@metronaviation.com
131 Elden Street, Suite 200
Herndon, VA 20170-4783
(703)456-0123

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Automatic Dependent Surveillance ? Broadcast (ADS-B) is an emerging Communications, Navigation, and Surveillance (CNS) technology that will vastly expand the state of the art in CNS in the National Airspace System (NAS). However, ADS-B is not currently secure and foolproof, and is currently vulnerable to abnormalities and deliberate contamination (spoofing). To address these problems, Metron Aviation, Inc. designs and develops an innovative software system that Verifies and Validates (V&V) the integrity of an ADS-B signal in real-time, independent of a secondary truth source of surveillance data. The system uses a suite of Kalman filters for short time horizon trajectory predictions, bearing signal tracking, a novel intent inference algorithm for reasoning about ADS-B intent data, and confidence assessment measures. The proposed technology addresses NASA's quest for technologies to harden aircraft CNS systems against abnormality and deliberate attack.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This ADS-B Verification and Validation system provides NASA Glenn's ACAST (Advanced CNS Architectures and System Technologies) with a technology that enables increases in capacity, efficiency, mobility and flexibility for users of the National Airspace System.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This ADS-B Verification and Validation system has potential to be included inside ADS-B equipment being sold by many vendors in the US and Europe, and is applicable to multiple data link technologies (Mode S 1090 MHz, VDL Mode 4, or Universal Access Transceiver (UAT)) used in remote regions like Alaska and Gulf of Mexico.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
BARRON ASSOCIATES, INC.
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2496
(434)973-1215

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Alec J.D. Bateman
bateman@barron-associates.com
1410 Sachem Place, Suite 202
Charlottesville, VA 22901-2496
(434)973-1215

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As the complexity of flight controllers grows so does the cost associated with verification and validation (V&V). Current-generation controllers are reaching a level of complexity that pushes the envelopes of existing V&V approaches, and without improved approaches there is little hope for affordable V&V of next-generation intelligent systems. Unfortunately, controller complexity and controller validation are required to ensure the safety of next-generation systems. Barron Associates proposes an aggressive plan of research to develop monitoring algorithms that estimate, in real time, safety margins of complex systems based on observed differences between the model used for controller development and actual flight data. The Phase I and Phase II research will focus on the flight test environment where these algorithms would allow the flight test engineer to monitor and revise the test plan in real time - skipping ahead in the buildup when safety is assured and avoiding test points where safety is questionable. The tool would also recommend test points that could help refine safety margin estimates for as yet unexecuted maneuvers. The result will be reduced flight test costs and improved safety. Phase I will develop a prototype approach and Phase II would implement the approach in a software tool.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The immediate NASA application is the Airborne Subscale Transport Aircraft Research (AirSTAR) test-bed at LaRC. This aircraft will provide an experimental flight test capability for Aviation Safety and Security Program (AvSSP) Single Aircraft Accident Prevention (SAAP) research pertaining to advanced control technology for failure accommodation and control under upset conditions. The SAAP algorithms are novel and complex, and many AirSTAR flight tests will be conducted at the edges of the flight envelope. The proposed research will be designed to address this need by providing real time monitoring and assurance, thereby improving the safety and reducing flight-test costs.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Non-NASA commercial applications fall under two categories: (1) other real-time testing of safety-critical systems, and (2) real-time monitoring of operational systems. Barron Associates is currently working with all three major airframers (Lockheed, Northrop, and Boeing) as well as the Navy and Air Force flight test centers to develop modeling, control, and advanced validation and verification (V&V) technologies for safety-critical systems. The tool developed in this SBIR address a unique need not being addressed by other current research, and will complement the tools already being developed by Barron Associates, Inc.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mosaic ATM, Inc.
1190 Hawling Pl
Leesburg, VA 20175-5084
(703)737-7637

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Chris Brinton
brinton@mosaicatm.com
1190 Hawling Pl
Leesburg, VA 20175-5084
(703)737-7637

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The aviation system of the United States of America is one of our national treasures. Very few elements of our culture capture the America spirit like aviation. Air transportation plays an absolutely vital role in our economy, and is also a core part of our high standard of living. But this importance of aviation in our society also makes aviation a highly desirable target for terrorists. Secretary of State Colin Powell has said that "no threat is more serious to aviation" than man-portable air defense systems (MANPADS). Although on-board defenses against MANPADS are being developed for commercial aircraft, these systems will not be deployed for many years and will be very expensive. The innovation proposed herein provides an information and decision support system to enhance security monitoring and patrolling around the perimeter of airports ? where the threat of MANPADS attacks is at its highest. This effort will merge the use of advanced airport surface surveillance data with decision support algorithms and security threat and vulnerability assessment methodologies to identify and alert security personnel regarding the airport perimeter areas of highest vulnerability and greatest access to targets of opportunity for MANPADS attacks or other terrorist activities.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The MANPADS threat against commercial aviation is real and must be addressed as soon as possible. A significant need exists for the Airport Perimeter Security Advisor (APSA) technology that will be developed through the conduct of this SBIR to complement airborne solutions. The APSA tool may be of interest to DHS, TSA, FAA, and airport authorities, in addition to local law enforcement responsible for patrolling the area around airports. This effort represents an excellent opportunity for NASA to leverage the already successful SMS program to provide additional benefits to the NAS through airport security improvements.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Commercial spin-offs of the APSA tool would focus on airport surface information display and management. Most airlines do not have sufficient information regarding the location of their aircraft and other assets on the airport surface. A commercial version of the APSA airport surface and terminal area map with dynamic flight information could be of significant commercial interest to the air carriers. Mosaic ATM is well positioned to obtain commercial funding from airlines to develop decision support tools to optimize the air carrier operation. Note that many air carriers already use SMS as an integral part of their daily operation.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Nokomis, Inc
6510 Brownsville Rd
Pittsburgh, PA 15236-3533
(412)650-6236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Walter J. Keller
wkeller@nokomisinc.com
6510 Brownsville Rd
Pittsburgh, PA 15236-3533
(412)650-6236

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The technology required to deploy Directed Energy Weapons (DEW) for use against hardened military targets may be constrained to just a few nations, but for soft targets like commercial aircraft and Air Transportation System (ATS) assets options are plenty for terrorists, organized crime or rogue states hoping to inflict harm. These devices are readily configured for covert operations favored by such groups. This work will identify, quantify and provide guidance to intercept RF, EMP and HPM weapons terrorists might deploy against the ATS. Designs within this group will be categorized by type of design, quantitatively analyzed to determine threat parameters and broken down into components that can be screened by ATS personnel. The end product of this work will directly improve the safety and security of the ATS.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The NASA Strategic Plan includes requirements to enable a more secure air transportation system through development of high-payoff technologies. The goal of this work is to directly deter potential terrorist attacks and contribute to improving the security of commercial aircraft and the ATS.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Commercial applications related to accurate prediction of electromagnetic threats are vast. Virtually, every government agency from federal to local authorities have the need to understand the threat posed by EMP and HPM weapons. Sooner or later terrorists, organized crime, or a foreign state will utilize an EMP or HPM weapon against an American target that will create fear in the commercial marketplace. There are very few corporations that have protected their computer assets to these threats. What CEO wants to find that 500 computers and his company's entire network would be destroyed by an electromagnetic attack?

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
FETCH TECHNOLOGIES
2041 Rosecrans, Suite 245
El Segundo, CA 90245-4789
(310)414-9849

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Steven Minton
Minton@Fetch.com
2041 Rosecrans, Suite 245
El Segundo, CA 90245-4789
(310)414-9849

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to improve the effectiveness of air cargo prescreening by
enabling background knowledge about companies and products to be used
for threat assessment. The Transportation Security Administration's
(TSA) current approach for pre-screening air cargo shipments is based
primarily on the Known Shipper Program, which has several
shortcomings. By combining sophisticated data extraction and
integration technology with state-of-the-art data mining capabilities,
threat assessment rules can be developed to help identify high-risk
cargo. However, threat assessment relies on having data about the
entities being assessed. In this project, we propose to develop novel
data aggregation methods to automatically gather information about
companies and products from corporate web sites, business directories,
and other internet sources. We can then augment primary data sources
(cargo manifest, database of past cargo shipments, package
characteristics such as weight and volume) with additional background
data (shipper and receiver information, shippable goods information)
to perform threat assessment, and thereby route high-risk cargo for
additional inspection. The use of this background data has great
potential to significantly improve the ability of the TSA to detect
vulnerabilities that may arise in the shipment of air cargo to, from,
and within the United States.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The potential NASA Commercial Application that will be enabled by this technology is the development of an air cargo pre-screening application. The technology produced in this proposal allows for the creation of a massive database of corporate and product information. This data, in conjunction with historical data on cargo manifests, provides a very rich dataset for data mining purposes. A threat assessment application that uses this dataset, in conjunction with the results of the data mining, will be a highly effective tool for pre-screening air cargo shipments.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The technology developed under this proposal has clear commercial value. We have existing customers using our web aggregation technology for market intelligence and competitive intelligence applications. Many of these customers have explicitly expressed their interest in unsupervised, site-independent approaches for collecting product data and corporate data via the web. In addition the technology is of direct importance to companies such as Dun & Bradstreet that currently aggregate corporate data using time-consuming, manual methods.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2785
(301)294-5200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Xiaodong Zhang
xzhang@i-a-i.com
15400 Calhoun Drive, Suite 400
Rockville, MD 20855-2785
(301)294-5269

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal presents a novel intelligent hierarchical approach to detection, isolation, and accommodation of primary aerodynamic actuator failures. The proposed architecture has three main components. First, a nonlinear fault diagnosis scheme is used to detect any fault occurrence and to determine the particular fault type. The proposed method can directly deal with nonlinear systems and nonlinear faults, unstructured modeling uncertainty, and new and unanticipated faults. Second, a controller module consists of a primary nominal controller and a secondary adaptive fault tolerant controller. While the nominal controller can be any existing conventional flight control system, the secondary neural network (NN) based adaptive controller is designed to accommodate primary control surface failures by utilizing control redundancy. A pseudo-control hedging method is used to prevent the NN from adapting to various actuation anomalies. Third, a reconfiguration supervisor makes decision regarding controller reconfiguration and control reallocation by using on-line diagnostic information. The proposed architecture is attractive in particular as a retrofit to previously certified flight control systems for improved flight safety. Our primary Phase 1 research objective is feasibility demonstration through extensive simulation studies. In Phase 2, we will refine the algorithms and develop the real-time control software.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
There are many potential NASA applications for this innovation, for instance, Integrated Vehicle Health Management systems, health monitoring of spacecraft, reusable launch vehicles, propulsion control systems, etc. Other potential applications include NASA systems such as valves, pumps, motors, Main Propulsion System, Thermal Control System, etc. The size of this market is not small and hard to estimate.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed approach can be used for applications such as military and commercial aircraft, unmanned aerial vehicles (UAVs), ships, submarines, motors, robots, and nuclear reactors, etc. The proposed fault diagnostics system can be extended to many other applications, such as pumps, gearboxes, motors, engines, etc. The Future Combat System (FCS) program and Joint Strike Fighter (JSF) program are also in significant need of diagnostics and fault-tolerant control technology.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
SenAnTech, Inc.
5444 Silver Creek
Columbus, OH 43228-9062
(614)571-2117

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Seung-Keon Kwak
senantech@yahoo.com
5444 Silver Creek
Columbus, OH 43228-9062
(614)571-2117

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this SBIR project, a reliable self-repairing Flight Control System (FCS) will be developed. To achieve this goal, an artificial Neural Network based Sensor Validity Monitoring, Verification and Accommodation (SVMVA) scheme will be developed. Initially, the Extended Back Propagation Algorithm (EBPA) or Learning Vector Quantization (LVQ) will be evaluated and employed as the on-line real time learning, monitoring and estimating tools. For a feasibility study, sample flight vehicle dynamics will be assessed. Then, an optimal on-line estimator for the flight dynamics will be shown by applying our unique input vector discrimination procedure and network optimization technique. In Phase I, an in-house numerical simulation tool for SVMVA will be developed to demonstrate the feasibility of our approach. As a result, it is expected that the new self-repairing Flight Control System based on SVMVA scheme will meet or exceed the NASA's requirement for their new flight vehicles. The most significant advantage of the new self-repairing Flight Control System is that the system is able to mask failed physical sensors by providing flight-worthy flight dynamics information to most FCS of flight vehicles without needing redundant sensors or excessive power, weight and space.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The SVMVA product will be very attractive to NASA's space exploration missions. By providing reliable backup information of space vehicle dynamics without additional physically redundant sensors in case of failure of the primary or secondary sensor systems, it will considerably reduce the weight, space, and power requirement of vehicles and reduce the vulnerability of vehicle operations.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The new reconfigurable flight control system based on Sensor Validity Monitoring, Verification and Identification (SVMVA) scheme has great potential for both commercial and military markets. The applications of the proposed technology and related products are not only limited in the aerospace industries but also extended to various military and civil fault detection and health monitoring markets. Aircraft engine industry is also potential markets. Real-time health monitoring of expensive and mission critical rotating component can save money and life. Consequently, its application includes virtually anything that requires detection of sensor and actuator conditions in broadband frequencies.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Brilliant Technology Inc
1500 Woodward Court
Brentwood, TN 37027-8641
(615)300-8481

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Kevin Tseng
KevinTseng@yahoo.com
1500 Woodward Court
Brentwood, TN 37027-8641
(615)300-8481

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposed project will attempt to develop a data analysis system for structural health monitoring on space structures. The data analysis software will be a key component in space vehicle health management system and can be used to in vehicle life prediction. The sensor data analysis algorithm is aimed at providing a modeling and simulation tool for data collected from a network of distributed sensors. The sensor network can be implemented via the state-of-the-art technology of distributed wireless dust network. A novel algorithm combining measurement data from the sensors and the analytical model based on the concept of finite element analysis is proposed and the feasibility of the algorithm to detect structural damage will be tested in this project. The project will focus on the impedance-based nondestructive damage evaluation technique. However, the algorithm can be extended to handle other types of sensor data such as acceleration and temperature. The data analysis system can monitor the performance of defective structural component in a space vehicle and issue proper warning for maintenance and repair. If the concept is tested successful, the algorithm can be further developed into a commercial software to be used for the structural integrity monitoring of many engineering applications.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed system can be used to monitor the integrity of a wide range of space structures. This system can be used to monitor the performance of metallic and non-metallic structural components and the space structural system. The structural health monitoring system will be a key component in space vehicle health management system and the data collected can be used to predict the remaining service life of the space structures. The system will be a valuable technology for the safety of future space exploration including manned and unmanned missions to the Moon, the Mars, and other long-rang space missions.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Since the proposed data analysis system is non-parametric meaning that the technology is not dependent on the geometry and material properties of the structures being monitored, the system can be used to monitor the structural integrity of one structural component, a sub-structural system, and the entire structural system. This technology can be applied to a very wide range of engineering applications. Examples of potential applications include automobiles, nuclear power-plant structures, and civil infrastructures such as the pipeline systems, bridges, and high-rise buildings. The system can be integrated into the vehicle health management system and life prediction system.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Kestrel Technology LLC
3260 Hillview Ave.
Palo Alto, CA 94304-1201
(650)320-8888

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Allen Goldberg
goldberg@email.arc.nasa.gov
NASA Ames Research Ctr, M/S 269/2
Moffett Field, CA 94035-1000
(650)604-4585

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Increasingly, critical flight functionality is implemented in software, but traditional (integrated) vehicle health management (IVHM) has primarily addressed hardware faults. All fielded software has residual errors, and the marginal costs to remove errors grow as the target residual error rate decreases. Our innovation is the development of tools, architectural concepts and software development methodologies to extend IVHM systems to detect, isolate and recover from software errors, as a cost effective way to increase the reliability and robustness of flight software. Software fault detection, isolation and recovery (SFDIR) fixes or contains the impact of faults and reduces the possibility of catastrophic loss. Each phase ? detection, isolation, and recovery ? raises new research challenges. This work addresses automated diagnostics of mission-critical avionics and middleware or software toolkits to lower the cost of developing online health monitoring applications. Our technical objectives are to detect, by code instrumentation, when the software state violates explicated safety constraints; using model-based reasoning and program analysis techniques, to trace from symptom to error source; and to recover from errors in a safe way preserving or replacing as much functionality as possible, and in all cases "to do no harm". This technology may also be applied to monitor potential security threats.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The potential applications of our innovation are generally to any system which requires high levels of safety and robustness. However, our work will focus on flight software for both aviation and space applications, including UAVs, military flight systems, and Exploration missions. Autonomy software in particular can benefit from this approach

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A natural follow-on to a successful Phase II effort would be a partnership with an organization developing flight software and to apply the technology to new flight software development.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
MetroLaser, Inc.
2572 White Road
Irvine, CA 92614-6236
(949)553-0688

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Thomas P. Jenkins
tjenkins@metrolaserinc.com
2572 White Road
Irvine, CA 92614-6236
(949)553-0688

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a versatile and affordable system to measure the average diameter of primary soot particles along with their mass concentration in aircraft engine exhausts. This work will expand upon our recent experience applying laser-induced incandescence (LII) to obtain the first successful quantitative measurements of spatially and temporally resolved, non-intrusive soot particle mass concentration in an aircraft engine test. The proposed system will take advantage of recent research suggesting that particle size can be obtained from the LII decay rate. Advances in laser and photodiode technology should enable compact, inexpensive components to be used. A simple calibration procedure will help minimize the requirements for operator expertise and training. Advanced, experimentally validated algorithms will be used to compute soot particle size and mass, with the results displayed in real time during an engine test. The tasks described in this proposal are essential steps leading to a versatile LII system that can be routinely applied to engine testing programs, and subsequently commercialized. Our goal is to develop an LII system suitable for widespread use; therefore, it will be portable, inexpensive, and easy to operate. The proposed Phase I effort will demonstrate the feasibility of this system.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A successful LII particle sizing and mass instrument could be used by NASA to quantify and classify particulate emissions by size from aircraft engines. Data obtained with the instrument could be used in conjunction with climate models in studies to predict the impact of aircraft-generated aerosols, thus helping to establish goals for aircraft particulate emissions. The LII instrument will complement existing aerosol mass spectrometers by providing in situ measurements of overall particulate mass; whereas the existing extractive sampling techniques contain an inherent uncertainty in the total mass due to loss in the sampling lines.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed technique will find commercial application in a variety of industries needing to comply with particle pollution standards. Examples include automobile, truck, diesel generators, marine and gas turbine industries. This market will eventually expand to include commercial airlines and automobile test stations.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Optimal Synthesis Inc.
868 San Antonio Road
Palo Alto, CA 94303-4622
(650)213-8585

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Padmanabhan K. Menon
menon@optisyn.com
868 San Antonio Road
Palo Alto, CA 94303-4622
(650)213-8585

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Traditional design methods for aircraft turbine engine control systems have relied on the use of linearized models and linear control theory. While these controllers can provide satisfactory performance, they do not exploit all the available knowledge about the nonlinear engine dynamics. Recent advances in computer-aided nonlinear control system design technology have made it feasible to design control systems using a detailed model of the engine. These nonlinear engine control systems have the potential to deliver a more precise control of the engine dynamics while satisfying multiple operational requirements.
Using a NASA-supplied engine model, Phase I research will develop a nonlinear engine control system that can deliver uniform performance over the entire operating region. Operation at multiple operating points and transitions between them will be demonstrated during the Phase I research.
Phase II work will develop a rapid-prototyping design environment for nonlinear engine control systems and real-time controller code generation for implementing the nonlinear control on engine control computer. Advanced engine control concepts such as active clearance control and adaptive engine control will also be demonstrated during the Phase II work. The design software and the control technology developed under the present SBIR will be commercialized during the Phase III research.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The rapid-prototyping software environment for nonlinear engine control design and real-time code generation developed under the proposed research will allow NASA to expeditiously examine the design tradeoffs in future engine development programs.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Nonlinear engine control systems will be able to exercise a more precise control over the engine dynamics, leading to better engine performance and life. The advanced control architecture may also allow better tradeoffs between engine performance and environmental specifications. The design software developed during the Phase II research will provide a rapid-prototyping capability for nonlinear engine control systems to NASA and aircraft engine developers.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
NexTech Materials, Ltd.
404 Enterprise Dr.
Lewis Center, OH 43035-9423
(614)842-6606

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Scott L. Swartz
swartz@nextechmaterials.com
404 Enterprise Dr.
Lewis Center, OH 43035-9423
(614)842-6606

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As solid oxide fuel cells (SOFCs) approach commercialization, interest in broader applications of this technology is mounting. While the first commercialized systems are being designed to provide 3-5 kW in stationary and automotive auxiliary power unit (APU) applications, military and aerospace users are already considering integrating SOFCs into larger, airborne systems with considerable commercial payback. SOFCs are aligned to displace inefficient, noisy, and polluting technologies such as diesel generators that will provide both economic and environmental motivation to prospective users. NexTech Materials proposes to develop sulfur-tolerant autothermal reforming (ATR) catalysts for fuel processors of SOFC systems that operate with sulfur-containing aviation (Jet-A) fuels. The Phase I work will focus on synthesis and characterization of novel composite catalysts, design and construction of a reactor for catalyst performance tests, and evaluation of the performance of experimental catalysts for autothermal reforming of Jet-A fuel. Phase II of the project will involve further optimization of catalyst formulations, scale-up of the catalyst synthesis technology, development of monolith-supporting technology for the catalysts, and evaluation of monolith-supported catalysts in prototype ATR reformers.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The primary application for the proposed catalyst technology is for fuel processing components of solid oxide fuel cell systems. One of the key limitations to near-term commercialization of SOFC systems for aerospace applications is the lack of catalyst materials that will allow SOFCs to operate on existing aviation fuels. With successful development of such catalysts, SOFC systems can be integrated with gas turbines in auxiliary power units for commercial jet airliners, with expected advantages of reduced fuel consumption and substantially lower emissions of NOX and other pollutants.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The catalyst technology will enable development of efficient and environmentally friendly SOFC based power generation systems for a number of military, automotive, and commercial applications involving operation on liquid hydrocarbon fuels (gasoline, diesel, propane, etc.). For example, all branches of the U.S. military have critical unmet needs for strategic field power generation systems operating on existing logistic (diesel) fuels. Sulfur-tolerant reforming catalysts are required for SOFC devices being developed for such applications. Further, the proposed catalysts will be applicable to fuel processors in SOFC systems being developed for auxiliary power units for cars, trucks and recreational vehicles.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
TechLand Research, Inc.
28895 Lorain Road, Suite 201
North Olmsted, OH 44070-4049
(440)716-9077

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Lois J Weir
techland@stratos.net
28895 Lorain Road, Suite 201
North Olmsted, OH 44070-4049
(440)716-9077

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Hypersonic propulsion research has been a focus of the NASA aeronautics program for years. Previous high-speed cruise and space access programs have examined the problems of inlet design for hybrid systems, mainly by addressing one part of the flight envelope only. The proposed program will leverage existing technology by utilizing design data for the high-speed inlet for a Mach 5 over-under turbojet/ramjet propulsion system. The proposed effort will identify a variable geometry system that will effect mode transition between modes. An experimental research effort will be designed, and requirements for the research hardware (aerodynamic design and functionality) will be developed sufficiently to commence mechanical design early in a follow-on Phase II effort. The objective of the Phase II effort will be to experimentally demonstrate operation of the dual-flow inlet system during mode transition.

Mode transition of hypersonic inlet systems with dual flow paths represents one of the greatest challenges facing hypersonic propulsion system designers. The proposed research will provide design approaches to these problems, for which few workable solutions have yet been identified. The innovations in hypersonic inlet design technology provided by this and follow-on research will provide enabling technology required to bring low-cost hypersonic flight closer to practical reality.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
NASA applications include hypersonic cruise or space access vehicles employing multi-mode propulsion systems with dual flow paths. Such systems include Rocket-Based Combined Cycle (RBCC) and Turbine-Based Combined Cycle (TBCC) systems.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Military hypersonic cruise vehicles, global access vehicles, or hypersonic missiles employing multi-mode propulsion systems.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Innovative Scientific Solutions Inc
2766 Indian Ripple Rd
Dayton, OH 45440-3638
(937)429-4980

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Sivaram Gogineni
sivaram.gogineni@wpafb.af.mil
2766 Indian Ripple Rd
Dayton, OH 45440-3638
(937)255-8446

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An experimental research program focusing on design, development, and testing of a novel nonequilibrium plasma ignition module is proposed. The ignition module will be based on the use of diffuse high-pressure transverse discharge technology recently developed at Ohio State using Air Force support. The proposed research is of critical importance for development of nonequilibrium plasma igniters modules for airplane jet engines. The primary objectives of the proposed research are (i) extending the use of the new nonequilibrium plasma ignition / flameholding method demonstrated in previous research by the current proposers to higher static pressures (up to P=0.5-1.0 atm), (ii) measuring the NOx emissions in the pulsed plasma stabilized flames and the plasma power budget, and (iii) studying the effect of the pulsed plasma on flame blow-off and relight. The proposed research will be conducted using gaseous hydrocarbon fuels. The results would have direct impact on development and the use of nonequilibrium plasma ignition modules for lean combustor operation and high altitude turbojet relight. The results would also elucidate kinetic mechanisms of plasma assisted ignition and flameholding.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Research performed during Phase I study will provide key experimental data which would help developing compact, low power budget nonequilibrium plasma ignition/flame stabilization modules to be used in commercial airplane jet engines. The use of these plasma ignition modules would make possible stable engine operation at low equivalence ratios, i.e. at the conditions when combustion becomes unstable. Engine operation at the lean conditions, using plasma flame stabilization, would also help reducing NOx emissions. Finally, the use of nonequlibrium plasma ignition modules would make possible high-altitude relight in case of a flameout.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Research performed during the proposed Phase I study will result in identification of realistic flow parameter range, including pressure, flow velocity, temperature, Mach number, and the equivalence ratios when nonequilibrium plasmas be efficiently used for ignition and flame stabilization. These results are of critical importance for future commercialization of plasma ignition technology for aero-propulsion applications. They will also significantly benefit research and development programs in both the commercial and on military aircraft industries. Considerable interest in using the results of the proposed research has been expressed by GE Aircraft Engines.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing, NJ 08618-2302
(609)538-0444

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Todd R. Quackenbush
todd@continuum-dynamics.com
34 Lexington Avenue
Ewing, NJ 08618-2302
(609)538-0444

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Noise mitigation for subsonic transports is a continuing high priority, and recent work has identified successful exhaust mixing enhancement devices that have demonstrated substantial capability for reducing aircraft engine noise in critical takeoff and landing conditions. Existing fixed-geometry versions of such devices, however, are inherently limited to optimal noise mitigation in a single operating condition and also can impose significant performance penalties in cruise flight. An adaptive geometry device using smart structures technology offers the possibility of maximizing engine performance while retaining and possibly enhancing the favorable noise characteristics of current designs. The proposed Phase I effort will demonstrate the feasibility of this concept, focusing on design and demonstration of variable geometry chevrons using rapidly maturing Shape Memory Alloy (SMA) actuation technology. This work represents an extension of prior successful development of solid state smart structures, though it will exploit new high temperature SMA (HTSMA) materials technology to enable the devices to operate in both low temperature (fan) and high temperature (core) exhaust flows. While important in its own right, this development also holds the promise of being the first step in development of a range of smart materials devices for a spectrum of aeropropulsion applications.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
By providing highly innovative concepts for propulsion system components for subsonic jet transports, the proposed effort will directly support a wide range of broad NASA goals including noise reduction and maximization of engine performance. The chief technical output of the effort will be enabling technology for a variable geometry devices to replace the promising but limited current generation of fixed-geometry chevrons. In addition, the integrated aero/thermo/elastic models of actuator performance to be developed will assist the development of concurrent engineering tools for analysis and design of propulsion flow control systems.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A successful Phase I/Phase II effort will open the door to prototype testing and eventual implementation of flight-qualified SMA adaptive chevron hardware. The most direct beneficiary would be next generation subsonic transports that could incorporate high-force, all-electric exhaust mixing control systems into power plants with an optimal balance of reduced noise and improved performance. Successful implementation in this application would also lead to spinoff developments in a number of actuation tasks, including aerodynamic controls and thrust vectoring as well as steering and outflow redirection for marine propulsion that would directly benefit both civil and military systems.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Technology in Blacksburg, Inc.
2901 Prosperity Rd.
Blacksburg, VA 24060-6644
(540)961-4401

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Jason M Anderson
janderson@techsburg.com
2901 Prosperity Rd.
Blacksburg, VA 24060-6644
(540)961-4401

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Techsburg is teaming with the Vibration and Acoustics Laboratory of Virginia Tech to propose a non-linear analytical tool for designing Herschel-Quincke (HQ) waveguide arrays for the purpose of attenuating upstream-propagating shock waves in a transonic turbofan engine inlet. Techsburg will be receiving endorsement and support for this research from the Goodrich Company who owns the HQ waveguide array concept. Thus far linear acoustic modeling has been used to design HQ waveguide arrays that have experimentally proven to be successful in attenuating far-field sound radiation from subsonic ducted fans. However, the large transonic turbofan engines used in most civil aviation aircraft today produce large amplitude bow shocks upstream of the fan rotor that nonlinearly scatter energy from the dominant BPF circumferential mode near the fan rotor to primarily lower engine order circumferential modes at the duct entrance, which produces the "buzz-saw" far-field acoustic signature. The non-linear design tool developed by Techsburg/Virginia Tech in Phase I will be used to design an optimal HQ waveguide array in Phase II that will be placed near the fan with the intention of attenuating the BPF circumferential mode in order to reduce scattered energy into lower engine orders that cause far-field "buzz-saw" noise.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The nonlinear model of the interaction between upstream propagating shock waves from a transonic turbofan aero engine and Herschel-Quincke waveguide arrays that Techsburg proposes for this Phase I research program can be utilized by NASA as an acoustic analysis and design tool for commercial transonic turbofan aero engines. This computer model could also be used for the analysis of other innovative passive and active noise control devices placed in intake ducts supersonic ducted fans. NASA could also couple the results of this in-duct nonlinear acoustic propagation model to far-field prediction codes such as the finite element based Eversman code.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Due to shock propagation in transonic turbofan engines, analysis and design of intake duct acoustic treatment requires nonlinear analysis. The nonlinear model of the interaction between upstream propagating shock waves from a transonic turbofan aero engine and Herschel-Quincke (HQ) waveguide arrays that Techsburg proposes for this Phase I research program serves this need for turbofan aero engine manufacturers. The HQ array technique is a particularly promising passive noise control technique owned by the Goodrich company, who like other engine manufactures currently desires a nonlinear analysis and design tool for innovative noise control technology.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
ESI US R&D
202 North Curry Street, Suite 100
Carson City, NV 89703-4121
(858)350-0057

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Bryce Gardner
bgardner@vasci.com
12555 High Bluff Drive, Suite 250
San Diego, CA 92130-3005
(858)350-0057

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal discusses the development and application of new methods of structural-acoustic analysis in order to address existing problems in aircraft interior noise prediction. The proposed methods are based on a hybrid modeling strategy that combines Finite Element Analysis (FEA) and Statistical Energy Analysis (SEA). Over the past five years, Vibro-Acoustic Sciences has devoted a considerable research effort towards the development of a framework for combining these two analysis methods. Recent research carried out by over the past two years has resulted in the development of a rigorous solution to this problem. The resulting Hybrid approach has been derived in general terms and validated for a number of simple structural-acoustic problems. However, the method has not yet been applied to aircraft interior noise prediction. A number of candidate aircraft interior noise problems have been identified which would benefit greatly from the use of the Hybrid method. The aims of the research described in this proposal are therefore: (i) to demonstrate the application of the Hybrid method to a number of existing aircraft interior noise problems, (ii) to develop the method to ensure it contains sufficient functionality to address practical aircraft interior noise problems and (iii) to demonstrate the value of the method in the prediction and reduction of noise in airframe systems.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
There is significant commercial potential for technology and software planned for the follow-on Phase II effort. The following market segments have been identified:
1) Commercial aircraft acoustic design ? flight deck, crew workstations and passenger cabin(s)
2) Commercial rotorcraft - flight deck safety and passenger comfort
3) Automobile interior noise ? sound package treatments, structure-borne noise, boom, etc.
4) Other transport vehicles ? railcars, ships, submarines, etc.
5) Consumer appliances in the home or office environment
6) Architectural/construction acoustics and noise control applications
7) Spacecraft random vibration environment prediction
8) Launch vehicle acoustic and vibration environment prediction

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
1) Aircraft interior noise research
2) Rotorcraft interior noise research
3) Manned spacecraft and on-orbit habitability research (eg. International Space Station)
4) Launch vehicle acoustic environment prediction
5) Spacecraft random vibration environment prediction
6) On-orbit spacecraft vibration environment

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing, NJ 08618-2302
(609)538-0444

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Daniel A. Wachspress
dan@continuum-dynamics.com
34 Lexington Avenue
Ewing, NJ 08618-2302
(609)538-0444

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal outlines a plan for enhancing and integrating new breakthrough technologies to provide accurate real-time noise prediction of V/STOL aircraft in maneuvering flight within a flight simulation environment. Loading, thickness and BVI noise sources, which often dominate the noise spectrum, will be predicted from first principles by coupling Continuum Dynamics, Inc.'s unique real-time full-span free-vortex wake model with Penn State University's innovative PSU-WOPWOP maneuvering flight noise prediction method. General rotorcraft configurations will be supported (e.g., tiltrotor, coaxial, tandem, main rotor/tail rotor) as well as ducted fan and powered lift aircraft. Other noise sources (e.g., broadband, engine, and self-noise) will be modeled using the most advanced empirical methods available today. Atmospheric absorption, spherical spreading, ground reflection, attenuation and acoustic phasing will be modeled through a direct coupling with Wyle Laboratory's state-of-the-art RNM code to provide accurate ground noise assessment required for low noise flight path planning. Further enhancements could lead to onboard flight management systems able to monitor and reduce ground noise levels in flight, a capability that would both improve public acceptance of V/STOL aircraft introduced into the National Airspace System and save the lives of military aviators operating rotorcraft in hostile territory.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
NASA is interested in the introduction of V/STOL aircraft into the National Airspace System to increase airport capacity but must address the impact of high noise levels on passenger and community acceptance. In this regard, the proposed effort directly responds to NASA's stated goal of developing new computational models to conduct detailed assessments of candidate concepts. The flight simulation tool will enable NASA to assess ground noise levels of potential concepts, to design low noise flight paths, and to evaluate the impact of noise control procedures on crew workload without the need for expensive flight tests.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed tool will offer aircraft developers and air traffic managers a method for analyzing low noise concepts in the design phase. The real-time capability will support design optimization trade studies. Heliports, airports, operators and the FAA will be able to utilize the tool in flight path planning, particularly that involving the introduction of V/STOL aircraft into the NAS. Eventual incorporation into onboard flight management systems will allow aircraft operators to monitor ground noise levels in flight. Currently there is no commercially available tool of this kind able to directly compute V/STOL noise at this high level of fidelity.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
SMD Corporation
4821 Shippen Court
Virginia Beach, VA 23455-4734
(757)519-9546

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Curtis R Mitchell
ozzy6fuller@netscape.net
4821 Shippen Court
Virginia Beach, VA 23455-4734
(757)519-9546

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this project advanced acoustic blankets for improved low frequency interior noise control in aircraft will be developed and demonstrated. The improved performance is achieved with a novel lightweight composite system that has been previously experimentally demonstrated on laboratory structures. The advanced blanket system will also satisfy new flammability and toxicity requirements with minimal integration issues. Work will be carried out with our partner NEVA Associates and acoustic material manufacturers to design commercial versions of the advanced blankets suitable for aircraft. Integration issues related to application in aircraft fuselages will be considered.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Potential NASA commercial applications of the new technology are throughout the US commercial and general aviation industry. The advanced blankets will result in quieter interiors of aircraft and also satisfy new flammability and toxicity requirements. The new blanket systems will thus increase the economic competiveness of the US aircraft industry worldwide.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Potential non-NASA commercial applications of the technology include reducing sound in defense aircraft, automobiles, industrial equipment as well as reduction of payload noise in launch vehicle fairings. The technology will result in a new, innovative passive blanket technology for noise control that will find general application in a multitude of products where low frequency noise control is important. The product will be of high economic benefit to many US industries that compete worldwide.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
ELECTRON ENERGY CORPORATION
924 Links Avenue
Landisville, PA 17538-1615
(717)898-2294

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Jinfang Liu
jfl@electronenergy.com
924 Links Ave.
Landisville, PA 17538-1615
(717)898-2294

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Previous high temperature magnetic bearings employed only electromagnets. The work proposed in this SBIR program seeks to utilize High Temperature Permanent Magnets (HTPM) developed by EEC. The use of HTPMs will improve efficiency since the majority of the static load on any bearing can be reacted by the flux of the permanent magnets.

The end product will be a high speed / high temperature / high load test platform for future development of high bearing, motor, generator and seal components. This capability will be of special benefit to the aerospace and process machinery industries. In addition the component demonstrations from this SBIR will provide designers with the confidence needed to integrate similar components in their high performance machinery.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
(a) High temperature magnetic bearings can be used for energy storage / attitude control flywheels for aerospace applications. High speed, vacuum operation and low bearing drag make magnetic bearings the best bearings for this application.

(b) High temperature magnetic bearings can also be used for gas turbine engines for aircraft applications. High temperature capability makes magnetic bearings a very attractive option for the new generation of high performance aircraft gas turbine engines which require bearings that will operate continuously at 1000 F. Bearing assemblies must supply damping to stabilize rotor dynamic vibrations along with providing support. Conventional bearing/dampers which utilize oils or elastomers will not operate at these high temperatures.

(c) Deep space exploration will require nuclear power utilizing Brayton and Sterling engines. The corrosive affects of potassium make it advantageous to totally "can" the process fluids so that seals are not required. The support for the shaft in a canned pump can only come from a magnetic bearing since its flux passes through the thin stainless steel can.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Magnetic bearings (MB) have gained wide acceptance for petrochemical industry compressors, turbo expanders and motors. Turbo-molecular vacuum pumps also employ magnetic bearings since they permit the flow passages to be canned to prevent leakage and achieve an improved vacuum.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Adherent Technologies
9621 Camino del Sol NE
Albuquerque, NM 87111-1522
(505)346-1685

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Ronald E. Allred
adherenttech@earthlink.net
9621 Camino del Sol NE
Albuquerque, NM 87111-1522
(505)346-1685

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Nano forms of graphite and carbon, such as flakes, worms, and tubes, can significantly modify the properties of polymers when used as reinforcements. Challenges remain in processing composites with these nano-reinforcements in the form of attaining uniform dispersions. Many of these difficulties are due to a lack of wetting of the nano-reinforcements by the polymer. Poor wetting is caused by the very low surface energy of the as-produced graphite nano-reinforcements. Opportunities exist for modifying the surface chemistry and energy of nano-reinforcements that will allow improved wetting and provide a means for chemical bonding at the interface with high temperature polymers such as PMR-II-50 polyimide. Two approaches for surface modification are proposed: (1) oxidative plasma treatments to populate the graphite surface with carboxyl and hydroxyl groups, and (2) bonding of polyimide oligomers to the nano-reinforcements using reactive coupling agents. Both of these approaches have proven successful with micron size carbon and graphite fibers and with nanofibers. As such, these treatments should result in nano-reinforced composites with superior mechanical properties and environmental durability.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The surface modified graphite nano-reinforcements will find use in numerous demanding applications. In particular, when combined with high temperature polyimide resins, they will be used in engine and propulsion applications to reduce weight and improve performance. They will also find uses with conventional fiber-reinforced composites to increase matrix properties.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
These unique nano-reinforcements will find many applications in structural composites for military and commercial aircraft, aerospace, chemical processing, and medical structures. The nano-materials markets are projected in the billions of dollars in the next decade, which will provide numerous outlets for the surface modified nano-reinforcements.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
UES Inc
4401 Dayton-Xenia Rd
Dayton, OH 45432-1894
(937)426-6900

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Amarendra K. Rai
arai@ues.com
4401 Dayton-Xenia Road
Dayton, OH 45432-1894
(937)426-6900

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Silicon based ceramics are the leading candidates for the high temperature structural components of the advanced propulsion engines. For such applications, one key drawback of silicon based ceramics is the volatilization of the protective silica scale in engine relevant oxidizing and water vapor environments at temperatures up to 1500 degrees C. Thus for the realization of silicon based ceramic components in advanced propulsion engines, environmental and thermal protective coatings will be needed. UES, Inc. proposes to develop a multifunctional environmental barrier coating concept utilizing advanced materials, coating design and coating processing technique for low thermal expansion silicon nitride. The performance and stability of the coatings developed in this program will be determined in relevant engine environments at temperatures up to 1500 degrees C. Based upon the test results coating design and process parameters will be further refined in Phase II.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Advanced Si based ceramics are the candidates for future NASA reusable space propulsion components. Robust environmental barrier coatings will be a critical part for successful introduction of advanced Si based ceramics and composites in future space vehicles.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Successful completion of the proposed technology through Phase I and Phase II effort will also enable the usage of Si based ceramics in the propulsion engines of Department of Defense vehicle applications. In the private sector, the proposed technology can be used in aircraft propulsion, and electric power generation, ceramic diesel and gasoline internal combustion engines.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
N&R ENGINEERING
6659 Pearl Road. #400
Parma Heights, OH 44130-3821
(440)845-7020

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
William Strack
bstrack@wowway.com
6659 Pearl Road. #400
Parma Heights, OH 44130-3821
(440)845-7020

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The work proposed herein would establish a concurrent design environment that enables aerospace hardware designers to rapidly determine optimum risk-constrained designs subject to multiple uncertainties in applied loads, material properties, and manufacturing processes. This means that the design process no longer would consist of a sequence of separate code invocations to: (1) obtain the geometry model, (2) determine the various loads, (3) determine performance, (4) perform a structural analysis, (5) perform design optimization, and (6) perform a probabilistic risk assessment. Instead, all of these functions would be automatically incorporated into a single framework using existing physics-based deterministic modeling codes and a set of computer-generated data transfer interfaces. Thus, a design engineer would be able to rapidly explore the design space to identify the minimum weight design that meets a given reliability constraint ? thereby avoiding both an overly conservative design and a too-risky design. For example, the software tools that implement this innovation could be used to determine the wall thickness of a launch vehicle's external cryogenic propellant tanks exposed to high but uncertain thermal and aerodynamic loads and with a reliability probability of 0.99999.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The work proposed herein would establish a concurrent design environment that enables aerospace hardware designers to rapidly determine optimum risk-constrained designs subject to multiple uncertainties in applied loads, material properties, and manufacturing processes. This means that the design process no longer would consist of a sequence of separate code invocations to: (1) obtain the geometry model, (2) determine the various loads, (3) determine performance, (4) perform a structural analysis, (5) perform design optimization, and (6) perform a probabilistic risk assessment. Instead, all of these functions would be automatically incorporated into a single framework using existing physics-based deterministic modeling codes and a set of computer-generated data transfer interfaces. Thus, a design engineer would be able to rapidly explore the design space to identify the minimum weight design that meets a given reliability constraint ? thereby avoiding both an overly conservative design and a too-risky design. For example, the software tools that implement this innovation could be used to determine the wall thickness of a launch vehicle's external cryogenic propellant tanks exposed to high but uncertain thermal and aerodynamic loads and with a reliability probability of 0.99999.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A fundamental architectural change in the design process is proposed that could revolutionize the ways many commercial designs are conducted that involve advanced technology and important uncertainties. For example, high-tech applications such as jet engines, central powerplants, artificial hearts, flight-qualified control system actuators, home heat pumps/air conditioners, automotive engines, and avionic circuit boards all require ultra-reliable, minimal-maintenance operation. Some of these operate in uncertain hostile environments and all involve a continuous stream of technical improvements with inherent uncertainties.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
TPL Inc
3921 Academy Parkway North, NE
Albuquerque, NM 87109-4416
(505)344-6744

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Charles D.E. Lakeman
clakeman@tplinc.com
3921 Academy Parkway North, NE
Albuquerque, NM 87109-4416
(505)342-4427

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Embedded wireless sensors of the future will enable flight vehicle systems to be "highly aware" of onboard health and performance parameters, as well as the external flow field and potential threat environments. Because there will be no opportunity to replace batteries on a regular basis, these systems will have to rely on energy harvesting strategies to convert ambient energy into electrical energy to provide long-lived power. TPL proposes to develop a MEMS-scale power system that will combine TPL's patented volumetric electrochemical micro-devices (microbatteries and microsupercapacitors) with energy harvesting for long lived power. Volumetric electrochemical devices are a unique and critical feature of our approach, which provide energy storage capabilities and high power density to minimize the total volume and footprint of the micropower system. The proposed effort will evaluate designs combining microbatteries, microsupercapacitors and energy harvesting devices with respect to the trade-offs between size, maximum power, duty cycle, and energy source availability. TPL's partner, the Johns Hopkins University Applied Physics Laboratory (JHU/APL), brings expertise in the space arena, and will provide technical guidance and advice on sensor requirements, integration and packaging for space. This partnership will be critical to realizing space-qualified devices.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
MEMS, and microsystems in general, will enable miniaturized accelerometers, gyroscopes, and numerous other innovative sensors and actuators. Furthermore, the advancement of wireless communication technologies opens the possibility of completely wireless systems, eliminating the cost, weight and potential for failure of conventional wiring. These systems will find application in structural health monitoring for various aerospace vehicles including robotic probes, space shuttles, and aircraft. All these devices will need a small size source of electrical power. The proposed innovative devices will provide a novel, low-cost solution to this need.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
As with many NASA-funded innovations, there are numerous civilian as well as defense applications for small form-factor, environmentally benign electrochemical power sources. As microsystems find wider use in government and consumer applications, such as active RFID tags, sensors for industrial process control, chem./bio agent detection, power in a small size package will become critical.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Cornerstone Research Group Inc
2750 Indian Ripple Road
Dayton, OH 45440-3325
(937)320-1877

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Benjamin A. Dietsch
dietschba@crgrp.net
2750 Indian Ripple Road
Dayton, OH 45440-3325
(937)320-1877

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cornerstone Research Group Inc. (CRG) proposes to develop an advanced reflexive structure system to increase the survivability of aerostructures. This reflexive system will mimic the pain withdrawal reflex on which the human body relies. The proposed reflexive system will incorporate a continuous health and performance monitoring system via an embedded dielectric film, an adaptive composite structure based on CRG's shape memory composite material (Veritex^TM), and an intelligence system which will be interfaced with both the health/performance sensors and the adaptive structure. When activated, Veritex^TM will recover its structural integrity via shape recovery and a novel healing process. These features enable the use of Veritex^TM as an adaptive structure in the proposed reflexive system. The development of a reflexive system for aerostructures will enable increased safety and security and demonstrate a better understanding of integrated performance systems. This reflexive technology could find immediate implementation on all current and future UCAV systems and future implementation on platforms such as the International Space Station, Lunar, and Martian habitats.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Supporting NASA's Aeronautics Enterprise, this project's technologies directly address requirements for enhanced aircraft safety and survivability. These technologies will enable conceptual flight vehicle/platform designs integrating smart, intelligent, and adaptive flight vehicle capabilities. The International Space Station, Lunar, and Martian habitats are all examples of structures that will benefit from a reflexive system.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This project's technologies developed for NASA systems would directly apply to systems operated by other government and commercial enterprises. Government systems that would derive the same benefits would include, but not be limited to, aircraft structures, marine structures, shelter structures, and many other structural systems operated by all agencies of the Department of Defense. This technology's attributes for reflexive repair should yield a high potential for private sector commercialization for reflexive systems for many types of structures that see combat environments.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
American GNC Corporation
888 Easy Street
Simi Valley, CA 93065-1812
(805)582-0582

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Ching-Fang Lin
cflin@americangnc.com
888 Easy Street
Simi Valley, CA 93065-1812
(805)582-0582

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of this SBIR Phase I project is to develop and demonstrate a low cost, lightweight, miniaturized Integrated Collision Avoidance Enhanced GN&C System for Smart Air Vehicles. The proposed system takes advantage of the latest Commercial-Off-the-Shelf (COTS) components, American GNC Corporation's products and patents to achieve an integrated, guidance, navigation, and control (GN&C) micro system for air vehicles, which is capable of assisting aircraft pilots to avoid approach and collision with ground/water and other near objects in flight. The various data from the IMU, GPS chipset, terrain data base, magnetometer, and object detection sensors are processed to produce collision warning audio/visual messages and collision avoidance guidance commands in a closed-loop system. In this Phase I project, the feasibility, as well as functions, specifications, hardware architecture, algorithms and software of the proposed system will be investigated, simulated, and demonstrated.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The product developed in this project, Integrated Collision Avoidance Enhanced GN&C System is applicable to several commercial applications including Air Traffic Management (ATM), smart vehicles, and intelligent transportation systems.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
In addition to the potential applications for NASA's Enabling Concepts and Technologies program, the proposed GN&C system is also well-suited?due to its small size, low cost, and light weight?to a wide range of NASA systems, including: remote sensing platforms, extravehicular robotic systems, telerobotics, and UAVs.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
SenAnTech, Inc.
5444 Silver Creek
Columbus, OH 43228-9062
(614)571-2117

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Seung-Keon Kwak
senantech@yahoo.com
5444 Silver Creek
Columbus, OH 43228-9062
(614)571-2117

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this SBIR project, a new Morphing Flight Control Surface (MFCS) will be developed. The distinction of the research effort is that the SenAnTech team will employ our innovative High Deformable Mechanism (HDM) to develop MFCS. The utilization of energy is the important concern to accomplish this research goal. Energy is chosen because it provides a mechanism where all concepts can be represented and judged in a consistent fashion. Ultimately, this research will provide a novel methodology for predicting the type, placement, and operation of actuators and sensors for aerial vehicles that incorporate large-scale shape changing for the improved flight performances. The MFCS will consist of hardware, software and processing units. The actuators, sensors, wiring, signal conditioning and, associated electronics will be selected as required. Modern systems technology like controllability and observability of the system will be examined for the optimal actuator and sensor placements. Also, shaped or digitized electrode technology will be applied to measure the spatial energy distribution of the deformable wing.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The new proposed Morphing Flight Control Surface (MFCS) can be used in future morphing control surfaces for NASA's experimental flight vehicles (manned or unmanned). This innovative system will assist to achieve the precision control, robust stability and future multi-mission capabilities including the ability to loiter (reconnaissance) and then dash (move quickly to another point).

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The direct result of this research will be a valuable asset to defense industry in the support of future multi-mission flight vehicles. Since mission adaptive air vehicles are presently being pursued by every major defense contractor, including Lockheed Martin, Northrop Grumman, and Boeing, the research proposed in this document will have lasting benefits to the aerospace industries as well.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Rolling Hills Research Corporation
420 N. Nash Street
El Segundo, CA 90245-2822
(310)640-8781

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Michael F Kerho
mike@RollingHillsResearch.com
420 N. Nash Street
El Segundo, CA 90245-2822
(310)640-8781

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An important mission for NASA is the development of revolutionary flight concepts and technology. The development of Micro unmanned air vehicles (Micro-UAVs) and Mars aircraft has received considerable attention in recent years. Unlike conventional aircraft and UAVs, Micro-UAVs and Mars aircraft suffer from operation in an extremely low Reynolds number flight regime. Both Micro-UAVs and Mars aircraft can have operational Reynolds number regimes from 20,000 to 120,000. At these extremely low Reynolds numbers, the aerodynamic flow features are dominated by laminar separation and separation bubble effects, which are the primary source of poor performance in both drag and maximum lift for this class of vehicles. It is proposed to use a robust and powerful active transition fixing technique to eliminate the effects of these large separation bubbles and provide revolutionary performance as of yet unobtainable by this class of ultra low Reynolds number vehicles. By artificially transitioning the flow upstream of the laminar separation bubble, the bubble itself can be eliminated resulting in a greatly reduced drag. The increased resistance to separation of a simple turbulent boundary-layer can pay revolutionary dividends at these very low Reynolds numbers.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The enhanced active transition fixing technology will provide revolutionary performance for ultra low Reynolds number vehicles including Micro-UAVs and Mars Aircraft. Additionally, low Reynolds number propeller based propulsions systems will also greatly benefit from this technology. Finally, the technology can provide significant performance improvements for any low Reynolds number system suffering from laminar separation issues. Considering NASA's recent emphasis on Mars Exploratory aircraft and its designs for small Micro-UAV designs, the NASA commercial applications potential for the technology is excellent.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The enhanced active transition fixing technology will provide revolutionary performance for ultra low Reynolds number vehicles including Micro-UAVs and Mars Aircraft. Additionally, low Reynolds number propeller based propulsions systems will greatly benefit from this technology. Finally, the technology can provide significant performance improvements for any low Reynolds number system suffering from laminar separation issues. Considering the recent proliferation of small and Micro-UAVs designs, its commercialization potential is excellent. RHRC will be able to license the active transition fixing technology or provide a complete ultra low Reynolds number airfoil design or design services for customers.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing, NJ 08618-2302
(609)538-0444

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert M. McKillip, Jr.
bob@continuum-dynamics.com
34 Lexington Avenue
Ewing, NJ 08618-2302
(609)538-0444

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Two novel flight control actuation concepts for UAV applications are proposed for research and development, both of which incorporate shape memory alloy (SMA) wires as prime movers. These actuators promise considerable savings in weight, power, and volume over existing electomechanical and hydraulic systems. Incorporation of these actuators within lifting surface structure, or as trailing edge control devices, would greatly simplify the actuation systems of these aircraft, thereby permitting greater payload fraction, increased range, enhanced robustness, and/or smaller vehicle size, and thus reduce both operational and fixed system costs. Choice between the two actuation concepts for a particular installation represents a tradeoff in actuation system bandwidth and power availability, and thus the same vehicle may include both systems depending upon the particular functional requirements. These actuators represent a derivative technology from a previous Army SBIR Phase I/II effort directed at providing in-flight helicopter blade tracking using actively controlled trailing edge tabs, and thus have been designed to have low mass and low power requirements from their inception. Since they lack any physical hinge joints, they may be embedded directly within aircraft lifting surfaces, eliminating interference drag associated with control deflection.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
NASA has a need for advanced control actuation and systems to support long endurance high-altitude UAV applications. This technology would help mitigate known issues with reduced aeroelastic stability of such high altitude platforms, as well as provide vehicle robustness (load alleviation) to atmospheric gusts. Its all-electric actuation and lack of moving parts (i.e., no discrete hinges) enhances the actuator's capability to support longer duration UAV missions planned by NASA for the future.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The actuators developed here could support DoD applications and commercial aircraft uses for UAV flight control and ancillary functions such as deploying flaps, landing gear and doors that house optics or weapons. They have a minimum number of moving parts, are extremely lightweight for the actuation stroke and force they provide, and utilize modest electrical power. In one configuration, electric power is only required to switch the actuator between discrete positions, making this actuator ideally suited for flap deployment and/or trim tab applications. These devices may also be used as auxiliary trim systems and flight control units for manned aircraft.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
FLUID FLOW TECHNOLOGIES, L.L.C.
4311 Valli Vista
Colorado Springs, CO 80915-1035
(719)591-7113

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Greg Glatzmaier
greg.glatzmaier@pcisys.net
4311 Valli Vista
Colorado Springs, CO 80915-1035
(719)591-7113

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposed work will develop a new method and mechanism for generating wing stroke motion of any shape and orientation. The mechanism will provide power, lift and flight control to small aircraft in a single integrated unit. The key innovation is the means by which wing motion is generated without the use any complex mechanical components. Wing motion of any shape and orientation can be generated with this mechanism. The arrangement of wings is such that the mechanism is mechanically balanced and exerts no net torque or force on the aircraft. This method is applicable to small UAVs (uninhabited aerial vehicles) and will provide them with a simple and reliable means of producing power, lift and flight control. The versatility of this mechanism is expected to provide UAVs with high maneuverability. This method will be most valuable for UAVs that are used as planetary aircraft as well as for general surveillance and reconnaissance.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This simple mechanism and electronics will result in long-term reliability, low manufacturing cost and a scalable design. Its mechanically balanced operation will provide a UAV platform which is capable of producing very stable and steady flight. This feature will be valuable for all applications including aerial imaging. Small-scale UAV designs will lead to a product that has low mass, volume, and power consumption. All of these features are of great value for use as planetary aircraft. This mechanism will also be a valuable research tool for flight testing UAV wings and studying the aerodynamics of insect flight.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Terrestrial markets for small UAV may become extensive. Military markets include surveillance, reconnaissance, positioning and targeting applications. Surveillance and reconnaissance applications extend to non-military markets including law enforcement. Private markets include a wide range of possibilities such as aerial access, inspection, and imaging of locations that are inaccessible to personnel within power plants, chemical plants, manufacturing facilities and other complex structures. The benefits that are provided by a small, maneuverable UAV could be of great value to a variety of manufacturing industries which use large and complex facilities.

SMALL BUSINESS CONCERN (Name, E-mail, Mail Address, City/State/Zip, Phone)
Zona Technology Inc
7430 E. Stetson Drive, Suite 205
Scottsdale, AZ 85251-3540
(480)945-9988

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dario H Baldelli
dario@zonatech.com
7430 E. Stetson Drive, Suite 205
Scottsdale, AZ 85251-3540
(480)945-9988

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA Technology proposes to develop an enhanced model updating nonlinear system identification (MUNSID) methodology by adopting the flight data with state-of-the-art control oriented techniques. The end product is a flight data enhanced MUNSID/ZAERO toolbox for accurate predictions of flutter and limit cycle oscillation (LCO) instabilities.

The enhancement employs control oriented techniques, namely, model uncertainty, linear fractional transformation framework, mu-analysis and nonlinear operators identification, to adopt the emerging aeroelastic flight-test data. This toolbox augments the current match-point solution approach using the mu-analysis method with identified nonlinear operators. The procedure calls for ZAERO's high-fidelity linear aeroelastic model to be tuned quickly with available aeroelastic/aeroservoelastic, AE/ASE, flight data sets, while block-oriented models are used to highlight the underlying nonlinear structure of the AE/ASE system. This framework is capable of accounting for several nonlinearities including those due to aerodynamics, structures, control/actuator, and/or geometry. The toolbox will be used as the next-generation flutterometer to predict the onset of AE/ASE instabilities. Two case studies, simple and complex dynamic ASE systems, are proposed to validate and verified this advanced control-oriented concept. This enabling technology will be invaluable to the flight test community by extending the current industry modeling tools to include nonlinear operators identified from wind-tunnel/flight-test data.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A model updating software tool for a general nonlinear AE/ASE system stability boundary prediction is still non-existent. NASA/DFRC has been working for many years towards achieving a software package that would predict the onset of AE/ASE instabilities with a high factor of safety for efficient envelope expansion. The proposed MUNSID/ZAERO toolbox is aimed at providing an expedient on-line prediction capability that integrates with current NASA procedures in the control room. The toolbox will be especially valuable during flight tests of the F/A-18 AAW, the F-15 IFF, the X-45 HyperX, the ERAST, and even future RevCon projects.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
ZONA's business plan for this toolbox will follow