NASA 2004 SBIR Phase 2 Solicitation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Physical Optics Corporation, EP Division
20600 Gramercy Place, Building 100
Torrance,CA 90501-1821

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Physical Optics Corporation (POC) proposes to develop a 3D cockpit display (3D-COD) system for improved pilot situational awareness and safety in 3D airspace by overcoming the inherent limitations of 2D information presentation. The proposed display will be automultiscopic and will be based on a projector, a stationary holographic optical element screen integrated with a high-speed electro-optical scanner and high-speed electronics with a software interface to NASA systems. This minimum 8-in. diagonal drop-down head-up display with no moving parts will present six or more perspective views to air crew members, forming integrated virtual volumetric 3D images viewable over a 60 degree horizontal field of view. In Phase I POC designed a laboratory prototype and successfully demonstrated the feasibility of the proposed system by assembling a single-user monochrome 3D-COD prototype. In Phase II POC will further develop the true 3D display technology and construct a fully functional system that will project distortion-free, 400-600 lumen, full-color, virtual volumetric 3D images at a 30-60 Hz video rate for real-time user interaction with the images, each from his or her own perspective.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The crew-centered 3D-COD system will find applications in NASA Synthetic Vision Systems to significantly enhance air safety through improved pilot situational awareness by information presentation in 3D. This system will benefit air traffic control, simulation, training, 3D design, and multicraft airspace image displays.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The 3D-COD technology has huge commercial potential, and will find applications in engineering development and entertainment, and particularly in theme parks, museums, and educational institutions. Niche applications include visual tools for medicine, and for design and development of complex machinery and systems.

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Terry Thompson
thompson@metronaviation.com
131 Elden Street, Suite 200
Herndon,VA 20170-5422

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In an effort to cope with air traffic demand growths and changing demand patterns, FAA, NASA, and industry have developed a number of simulation tools to model future concepts of air traffic management. Among these is the Systems Analysis Branch (SAB) simulation environment of NASA Langley. The current tools would greatly benefit from the portrayal of the daily preemptive Command and Control (C&C) activities performed by FAA and air carrier traffic managers. These actions significantly influence daily operations and overall NAS efficiency. Development of new operational concepts and evaluation of proposed changes requires simulation and modeling capabilities that include C&C effects. This understanding is crucial for the evaluation of current or proposed operations. Metron Aviation uses its extensive experience with and research of C&C to implement a model of NAS-wide ATM (C&C) actions and to integrate the resulting module into NASA Langley's SAB simulation environment. The final product adds realism to future aircraft movement simulations performed by NASA Langley and admits exploration of new concepts that involve air traffic flow management.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Understanding of the system-wide impacts of NAS C&C is lacking in both operational practice and current research. This understanding is crucial for the evaluation of current or proposed operations. Currently, NASA programs such as Next-Generation Air Transportation System (NGATS/JPDO), Small Aircraft Transportation Systems (SATS), Revolutionary Aerospace Systems Concepts, Virtual Airspace Modeling and Simulation (VAMS), and All-weather Capacity Enhancement NASA Research Announcement (NRA) are developing system concepts to meet increasing air traffic demand, reduce delays, and improve safety/security. Realistic NAS-wide simulations, including C&C, are required to assess emerging operational concepts and technologies, since they all assume some component of human-mediated C&C. Omitting this from the simulations risks missing important system behaviors that must be included in the development of the operational concepts and technologies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Estimates of ATM costs due to delays range from hundreds of millions to billions of dollars per year. Several research activities being pursued to meet the increasing demands in air travel promise to be costly and laborious to implement, and the difficulty of adequately assessing the anticipated impacts creates significant risk for operators and users of the NAS. Development of simulation capabilities and benefit assessment methods that include the effects of C&C creates significant commercial demand for accurate and robust C&C modeling capabilities.

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

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

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 a cockpit Turbulence Hazard Decision Aid that provides them with integrated, graphical turbulence hazard information scaled to their specific aircraft. This display will remove 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 II work will develop a prototype decision aid, based on the Phase I CONOPS and results, and then evaluate the prototype in both a PC simulation and a flight simulator. By the end of Phase II a meaningful, Integrated Turbulence Hazard Decision Aid will be developed and tested, paving the way for flight evaluations and commercialization in Phase III.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
When the goals of the proposed R/R&D are met, this cockpit, Integrated Turbulence Hazard Decision Aid will contribute to NASA's Aviation Safety and Security Program's (AvSSP) current national goals of a 25-50% reduction in weather-related accident causal factors and a 25 to 50% reduction in turbulence-related injuries. This work and the developed decision aid will be completely aligned with NASA's Turbulence Prediction and Warning System efforts, and NASA's Aviation Weather Information goal of enabling pilots to avoid atmospheric hazards by providing them timely, accurate, and intuitive weather information. It is also very consistent with the stated goals of the Integrated Flight deck Information Systems element of the Phase II AvSSP. Increased awareness of atmospheric turbulence provided by the decision aid may also add value to the NASA Airspace Systems program's goals of enabling "through technology development and transfer, major increases in the capacity and mobility of the air transportation system."

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
When the goals of the proposed R/R&D are met, this cockpit Turbulence Hazard Decision Aid will provide pilots with improved turbulence hazard information allowing them to operate more efficiently and safely. Significant reductions in costs associated with injuries due to turbulence and in fuel waste due to inefficient operations in and around turbulence are expected to be major commercial drivers for this system. The market for this decision aid is all Part 121 carriers (both domestic and international), cargo aircraft, corporate jets, and some high-end general aviation aircraft (an estimated 55,000+ Part 121 and corporate aircraft alone by 2023). Delta Air Lines was instrumental in the Phase I work and is supporting the Phase II work with evaluation pilots and flight simulators. Delta is "very interested in seeing the Integrated Turbulence Hazard Decision Aid developed to fruition" and could be a very strong advocate for the technology in Phase III.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cox and Company, Inc.
200 Varick Street
New York,NY 10014-4875

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation 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, and will require a two magnitude lower power.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The system proposed is a viable alternative to bleed air ice protection for engine inlets. The number of NASA applications is not so large as the number of commercial applications. However, 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 APPLICATION(S) (LIMIT 150 WORDS)
The market for electric powered ice protection is confirmed as a result of recent decisions by major aircraft manufacturers. Clearly, the movement to replace conventional bleed air ice protection for lifting surfaces is well underway. Even though the new electro-thermal de-icing systems present improvements in efficiencies of operation, the requirement still exists for use of anti-icing systems on the engine inlets. The substitution of de-icing systems for anti-icing on engine inlets offers an opportunity for another order of magnitude improvement in the power required to protect engine inlets. This is possible by the use of a mechanical de-icing system that repeatedly sheds ice particles that are small in comparison to the FAR hail and rain environments to which the engine is qualified. The use of a de-icing system as a means of protecting not only lifting and stabilizing surfaces but engine inlets as well will result in overall operating efficiencies beyond any improvement offered to date.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Radiometrics Corporation
2840 Wilderness Place, Unit G
Boulder,CO 80301-5414

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
f solheim
solheim@radiometrics.com
2840 Wilderness Place, Unit G
Boulder,CO 80301-5414

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 ground-based microwave radiometers with radars has shown great promise, but deficiencies of the radiometers have limited their value. In our Phase I effort we have determined solutions to several technical challenges in the design of a narrow beam multi-waveband radiometer that is to operate in concert with weather radars. We have also calculated optimum eigenfrequencies for detection of aircraft icing conditions. In Phase II we will construct a turnkey fast sampling multifrequency profiling and dual polarization narrow beam radiometer system. In this 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. The turnkey radiometer system and documentation are deliverables.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA 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 sample volume of research radars at a number of radiometric frequencies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ground-based radiometric system developed herein, as well as being a valuable research tool, is to be operated with radars such as NEXRAD and Terminal Doppler Weather Radars (TDWRs) to detect and quantify cloud liquid water and ice in single- and mixed-phase conditions aloft. In addition to detecting icing conditions enroute and in approach regions, the system can forewarn and nowcast the need (or lack of need) to apply deicing solutions in advance of departure, creating savings and reducing delays. This quantification will also enhance weather nowcasting and predictive capabilities. This large aperture narrow beam radiometer design is also applicable to characterizing and quantifying satellite link loss due to atmospheric absorption, and Radiometrics has had several inquiries for such a design in wavebands from 8 to 32 GHz, demonstrating a commercial market for this application.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Barron Associates, Inc.
1410 Sachem Place, Suite 202
Charlottesville,VA 22901-2496

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
As the complexity of flight controllers grows so does the cost associated with verification and validation (V&V). Current-generation controllers are reaching levels of complexity that push the envelopes of existing V&V approaches, and further increases in controller complexity are required to provide the operational capabilities desired for next generation systems. Without improved approaches, there is little hope for affordable V&V of next-generation intelligent systems and, unfortunately, controller validation is required to ensure the safety of these systems. Barron Associates proposes an aggressive plan of research to develop monitoring algorithms that estimate, in real time, safety margins of complex feedback systems based on observed differences between the model used for controller development and actual flight data. The Phase II research will focus on the flight test environment where these algorithms will allow the flight test engineer to monitor and revise the test plan in real time - accelerating the test-matrix buildup when safety is assured and avoiding test points where safety is questionable. The tool will 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.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed software tool will be a key enabling technology for safe and efficient flight testing of any advanced air vehicle, manned or unmanned. The key area of application will be aviation safety and security, where the Phase II product will facilitate the safety of flight testing advanced fault-tolerant and damage-adaptive controllers for which design-time V&V assurances may be less complete than for traditional controllers (e.g., Lockheed's AIMSAFE as part of AvSP and Dryden's PCA system). In particular, the intended initial application of the tool will be for the AirSTAR sub-scale flying test-bed. The AirSTAR is intended to allow testing that is too high risk for manned aircraft, and effective safety monitoring is especially important in this high-risk environment. Flight tests involving NASA's full-scale 757 will also benefit from the technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA aerospace applications include flight testing of advanced military systems such as JSF, J-UCAS, retrofit reconfigurable controllers for F-18 and other aircraft, the Helicopter Advanced Control Technologies (HACT) system, and next-generation rotorcraft fuel and engine control systems. Barron Associates is currently providing advanced control and V&V technology to all of these programs. Significant commercial potential for the technology exists as well. Initial demonstration on AirSTAR will provide a foundation for using the tool in tests of commercial transport aircraft. An even larger potential market is in unmanned aerial vehicles. There are a large number of unmanned vehicles currently being developed for both military and civilian applications, and these vehicles frequently utilize advanced control systems that represent relatively high risk. Flight test programs of such vehicles could thus benefit substantially from the proposed software tool.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Brilliant Technology, Inc.
1500 Woodward Court
Brentwood,TN 37027-8641

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kevin Tseng
Kevin.Tseng@tBrilliant.com
1500 Woodward Court
Brentwood,TN 37027-8641

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 focuses on integrating the new mesh sensor network technology into structural health monitoring. The data analysis system can monitor the performance of defective structural component in a space vehicle and issue proper warning for maintenance and repair. The concept has been tested feasible in Phase I. During Phase II, the algorithm will be further developed into a commercial software to be used for the structural integrity monitoring of many engineering applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 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 APPLICATION(S) (LIMIT 150 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: (Firm Name, Mail Address, City/State/ZIP, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing,NJ 08618-2302

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

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 (chevrons) that have demonstrated substantial capability for reducing aircraft engine noise in critical takeoff and landing conditions. Existing fixed-geometry chevrons, 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 chevron using embedded smart structures technology offers the possibility of maximizing engine performance while retaining and possibly enhancing the favorable noise characteristics of current designs. Phase I identified a promising candidate for a variable geometry chevron using high force Shape Memory Alloy (SMA) actuators. Building on coupled CFD/finite element modeling predicting successful performance, subscale demonstration-level actuated chevrons were constructed that yielded the required deflections in both benchtop and low speed wind tunnel tests. Phase I also identified and tested new high temperature SMA (HTSMA) materials technology to enable the devices to operate in both low temperature (fan) and high temperature (core) exhaust flows. The proposed Phase II effort will continue development of this technology and demonstrate extension of this concept to operation at full-scale stiffness levels and at realistic dynamic pressure and temperature conditions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
By providing highly innovative concepts for propulsion system components for subsonic jet transports, the proposed effort will directly support a range of NASA goals, including flight demonstration of noise alleviation technologies. The chief technical output of the effort will be enabling technology, design data, and prototypes for a variable geometry devices to replace the promising but limited current generation of fixed-geometry chevrons. Extensions of this HTSMA device technology could also permit powerplant performance optimization for prospective high altitude long endurance aircraft, as well as broadly applicable methods for analysis and design of smart-materials-based propulsion flow control systems.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A successful Phase I/Phase II effort will open the door to prototype testing and eventual implementation of 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 for both civil and military applications such as high speed aircraft and missile systems.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ESI US R&D
202 North Curry Street, Suite 100
Carson City,NV 89703-4121

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Bryce Gardner
Bryce.Gardner@esi-group-na.com
202 North Curry Street, Suite 100
Carson City,NV 89703-4121

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of the project is research and development of methods for application of the Hybrid FE-SEA method to aircraft vibro-acoustic problems. 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 APPLICATION(S) (LIMIT 150 WORDS)
? Aircraft interior noise research ? Rotorcraft interior noise research ? Manned spacecraft and on-orbit habitability research (e.g. International Space Station) ? Spacecraft random vibration environment prediction ? Launch vehicle acoustic and vibration environment prediction ? On-orbit spacecraft vibration environment ? Random vibration analysis of large optical space science platforms

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
? Commercial aircraft acoustic design ? flight deck, crew workstations and passenger cabin(s) ? Commercial aircraft insulation, isolation and damping package weight management and optimization ? Commercial rotorcraft - flight deck safety and passenger comfort ? Automobile interior noise ? sound package treatments, structure-borne noise, boom noise, etc. ? Heavy equipment acoustic design ? Noise and vibration analysis of other transport vehicles ? railcars, ships, submarines, etc. ? Sonar detectability of submarines ? underwater noise radiation ? Consumer appliances in the home or office environment ? Architectural/construction acoustics and noise control applications ? Acoustic materials design and research ? Recreational vehicles ? noise prediction/reduction ? HVAC

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SMD Corporation
4821 Shippen Court
Virginia Beach,VA 23455-4734

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Curtis Mitchell
cmitchell@smdva.com
4821 Shippen Court
Virginia Beach,VA 23455-4734

TECHNICAL ABSTRACT (Limit 2000 characters, approximately 200 words)
The objective of the proposed Phase II research effort is to develop advanced composite blankets for improved sound reduction in aircraft structures. Phase I successfully demonstrated the use of advanced blankets for sound transmission suppression and the applicability of the technology to aircraft interior noise control perpetuating a license agreement with a major U.S. Fortune 100 company to aggressively and expeditiously pursue product commercialization. The highest performing advanced blanket resulted in ~5 dB reduction in radiated power from an aircraft test panel. Reductions are broadband with an effective frequency range from approximately 100 to 1000 Hz resulting in decreased vibration and radiated acoustic levels across this range. The small 6-10% weight has acoustic benefits far greater than standard mass law effects. In Phase II attachment, temperature, and installation effects will be studied. Additionally, analytical design tools will be developed to automate the design process for practicing engineers making it possible to work from basic concepts and application requirements/specifications to achieve a final product which can be readily manufactured. Together the proven design concepts of Phase I and those proposed in Phase II represent the future in aircraft insulation in terms of acoustic performance, cost, weight, airframe integration, and passenger safety.

POTENTIAL NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
NASA applications for advanced aircraft blankets with improved low frequency sound transmission attenuation compliment all aircraft and aviation agenda. The commercial potential is extensive throughout the US commercial and military markets resulting in an immediate economic competitive advantage of the US aircraft industry worldwide. They are cost effective, compact, lightweight, configurations not only satisfying the latest toxicity and flammability requirements, but benefiting from minimal integration issues due to similarities in shape and form of current blanket systems. We will work closely with our team members of NEVA Associates, Boeing Aircraft Company and the relevant blanket product supplier to determine the application requirements and limitations and product manufacturing parameters respectively.

Potential applications include NASA's Airspace Systems Program and Vehicle Systems Program. Both would benefit from overall reduction in cabin noise levels in aircraft transport vehicles. Additional applications include space vehicles and structures such as the Space Station and the Space Shuttle.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (Limit 1500 characters, approximately 150 words)
Successful execution of this project will result in an immediate and widespread application throughout the US commercial and general military industries. During Phase II, professional relationships will be built with material and blanket product suppliers to determine application requirements, limitations, and manufacturing parameters. SMD has discussed the details of the advanced concept with a major material manufacturer who currently supplies a variety of products to the US military for use in personnel protection and they have agreed to provide viability assessments and probable route to market for the most promising SMD candidate materials.

Market segments which will benefit from advanced blanket concepts are divided into military, architectural, industrial, commercial, and original equipment manufacturers (O.E.M.s). Some potential Non-NASA Applications include: (1) Military: Fabric Shelters, Naval Engine Noise, HVAC, Hummer Noise Control, Mobile Medical Units and Hospitals (2) Industrial: Manufacturing Fans, Blowers, Compressors, CNC's, HVAC (3) OEM: Trucks/Tractor Trailers, Commercial Floor Cleaners, Bank Equipment, Compressors.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Electron Energy Corporation
924 Links Avenue
Landisville,PA 17538-1615

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jinfang Liu
jfl@electronenergy.com
924 Links Avenue
Landisville,PA 17538-1615

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Previous high temperature magnetic bearings employed electromagnets only. The work proposed in this SBIR program seeks to utilize High Temperature Permanent Magnets (HTPM) developed by EEC. This will improve efficiency since the majority of the static load on any bearing can be suspended by the magnetic field of the HTPM. The end product will be a high speed/high temperature/high load test platform for the future development of 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 APPLICATION(S) (LIMIT 150 WORDS)
Following are potential NASA commercial applications for high temperature magnetic bearings: (1) Enable lighter weight, higher temperature gas turbine engines and other machinery to operate effectively in hostile, high temperature environments such as the surface of Venus, and for propulsion and energy storage. (2) Power generation systems for space needs in Brayton cycle and other systems. (3) High temperature motor-generators (4) Deep space exploration that requires nuclear power utilizing Brayton and Sterling engines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High temperature magnetic bearings operate at high temperature under vacuum with low bearing drag, and would benefit use in aerospace applications for energy storage/attitude control flywheels. High temperature magnetic bearings can operate continuously at high temperatures and therefore could be used in turbines for advanced Army tanks engine designs as well as in turbines and expansion engines used in the chemical processing industries. High temperature magnetic bearings operating at and above 1000<SUP>o</SUP>F could be used in aircraft generators directly integral to high-pressure regions of aircraft engines in advanced designs. Additionally, high temperature magnetic bearings can be used in turbomachinery in conventional power generation applications.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Phase I results showed that two surface treatments, oxidative plasma and reactive finishes, are effective means of modifying the surface chemistry of exfoliated graphite nanoflakes. The surface modifications provide a more compatible surface energy for dispersion in polymers and create well-bonded interfaces with the polymer matrix. In order to be cost effective for NASA and commercial applications, the surface treatment processes need to be applied on a large scale. In the Phase II program, both treatment methods will be scaled-up to semi-continuous processes. Custom equipment will be fabricated to process large quantities of treated nanoflakes. The resulting treated nanoflakes will be characterized for surface chemistry and morphology and processed into polymer composites and continuous carbon fiber-reinforced polymer composites. The composites will be characterized for conductivity, thermal and mechanical, and diffusion barrier properties. It is expected that these composites will find applications as fuel cell bipolar plates, composite cryogenic storage tanks, and in light weight structures for aerospace, military, and transportation.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Nanomaterials are emerging as the next materials revolution. They have proven to greatly modify conventional materials properties at low loadings. As such, they will find many applications within NASA's mission such as fuel cells, cryogenic storage tanks, and structural composites for vehicles like the reusable launch vehicle.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The advantages of nanomaterials that make them attractive for NASA use also make them attractive for use in commercial specialty composite materials. Nanomaterials are already being applied in automotive applications. Additional uses in aerospace, military, medical, and sporting goods will follow like they have with continuous fiber composites. The low cost of the treated graphite nanoflakes will ensure that they attain a large market share.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
N&R Engineering
6659 Pearl Road, #400
Parma Heights,OH 44130-3821

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vinod Nagpal
vnagpal@nrengineering.com
6659 Pearl Road. #400
Parma Heights,OH 44130-3821

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The work proposed herein would develop a set of analytic methodologies and a computer tool suite enabling aerospace hardware designers to rapidly determine optimum risk-constrained designs subject to multiple physics-based 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 an excessively risky design. Moreover, the methodology would also rollup component-level uncertainties to the system level for multiple components -- thereby enabling a system level reliability constraint to be imposed at the component level. Advanced techniques will be developed including methods to: (a) determine confidence bounds on reliability predictions, (b) efficiently determine response surfaces, and (c) use physics-based progressive failure modeling. The software tool could be used, for example, to determine the wall thickness of a launch vehicle's external cryogenic propellant tanks exposed to high but uncertain thermal and aerodynamic loads with a reliability of 0.99999.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A broad spectrum of design problems involving parts/subsystems/systems required to attain mission-critical reliability levels at minimum weight, yet subject to major technical uncertainties. These problems typically involve high temperature/high stress propulsion systems and range from single part designs such as novel CMC turbine blades used in advanced rocket engine turbopumps and jet engines to complete systems such as the unconventional propulsion concepts proposed for future space vehicles (e.g., nuclear thermal rockets, nuclear-electric, and solar-electric systems). These applications include conceptual designs where future technology status is uncertain as well as operational systems that experience variances in operating conditions and manufacturing fidelity. The final product will be a suite of software tools that accelerate the design/analysis process, take the grunt work out of the typical engineering tasks of transferring/converting data streams from one application code to another, and capture the intrinsically probabilistic nature of design problems. This will enable engineers and managers to spend more of their time interpreting results and making wise decisions as well as yield a physics-based design-to-reliability solution.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A fundamental architectural change in the design process is proposed that could revolutionize the way many commercial designs are conducted that involve advanced technology and important uncertainties. For example, high-tech applications such as nuclear-powered 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. The software tool developed in this effort would accelerate these design processes while simultaneously yielding more reliable, cost-effective products.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
TPL, Inc.
3921 Academy Parkway North, NE
Albuquerque,NM 87109-4416

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Charles Lakeman
jelopez@tplinc.com
3921 Academy Parkway North, NE
Albuquerque,NM 87109-4416

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 micropower system that will combine TPL's patented microbatteries and microsupercapacitors with vibrational energy harvesting for use with wireless structural health monitoring (SHM) systems. The solution proposed will include all components required for a complete power supply for wireless SHM sensors, including proprietary power regulation and conditioning circuitry that draws very low power. TPL is a leader in designing and manufacturing power for light weight, minimum volume, minimum footprint, wireless systems. TPL's effort has been supported by Goodrich Fuel and Utility Systems whose expertise with Structural Health Monitoring will provide guidance on sensor requirements, integration and packaging. These relationships will facilitate realizing devices that will meet end-user requirements, and provide a commercialization pathway for Phase III.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are numerous applications for wireless sensors in aerospace to reduce the weight and cost of future flight vehicles. NASA's interest in structural health monitoring, in particular, extends to air and space vehicles, fixed wing and rotorcraft, satellites, inter-planetary mission vehicles, and high altitude, long endurance (HALE) vehicles. For wireless sensors in general, NASA applications will extend from remote sensing on earth, climate and meteorological monitoring, and geolocation in planetary exploration.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There is a myriad of non-NASA applications that have been discussed throughout this proposal; but for structural health monitoring, they include bridges, buildings (particularly high value, or sensitive buildings such as nuclear power or chemical plants), seismic detection, and ships (e.g. oil tankers or other vessels carrying cargoes that may be harmful if spilled). Other applications of wireless sensors extend into medical, industrial manufacturing (inventory management, process control), agricultural, domestic (smart house), and automotive (some estimate up to 1trillion automotive sensors in 2010 including tire pressure monitors and stability control).

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Cornerstone Research Group, Inc.
2750 Indian Ripple Road
Dayton,OH 45440-3325

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Benjamin Dietsch
dietschba@crgrp.net
2750 Indian Ripple Rd.
Dayton,OH 45440-3638

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Cornerstone Research Group Inc. (CRG) will develop an advanced reflexive structure technology system to increase the survivability of future systems constructed of lightweight composite structures. Application of this innovation will apply to a broad selection of high performance systems ranging from aircraft and spacecraft to habitats for space stations and interplanetary exploration. The control system for the reflexive structures will mimic the pain withdrawal-reflex on which the human body relies. This is important because rapid response is critical to survivability. The proposed reflexive system will incorporate a continuous health and performance monitoring system via embedded piezoelectric sensors, an adaptive composite structure based on CRG's shape memory composite material (Veritex<SUP>TM</SUP>), and an intelligence system which will be interfaced with both the health/performance sensors and the adaptive structure. When activated, the adaptive composite will recover its structural integrity via shape recovery and a novel healing process. The development of a reflexive structural system will enable increased safety and security and demonstrate a better understanding of integrated performance systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This project's technologies directly address requirements for smart, adaptive structures with intelligence for enhanced survivability of air and space platforms. These technologies offer an effective solution to improving structural survivability through integration of multi-functional materials into a single structural system. Benefits of this technology could be widespread throughout NASA platforms including interplanetary habitats, the International Space Station, unmanned air vehicles, and personal air vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Government systems that would derive the same benefits would include but not be limited to military and commercial aircraft operated by the Department of Defense (DoD), commercial airlines, and the general aviation community. This technology's attributes for active sense and respond structural recovery should yield a high potential for private sector commercialization for active structural health monitoring and management in several types of space-based and terrestrial structural systems. Lockheed Martin, Boeing, and Vought Aircraft Industries have documented their interest in this commercialization opportunity.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel technique for controlling transition from laminar to turbulent flow in very low Reynolds number conditions has been developed. Normally flows with Reynolds numbers in the range of 20,000 to 120,000 are dominated by laminar separation bubbles and are difficult to transition without using very large traditional trip devices, such as distributed roughness. Additionally, these traditional trips are sized for one flow condition and are either not effective at off-design conditions or create a large device drag penalty. RHRC's innovative transition control technology is capable of transitioning flow across a wide range of low Reynolds number conditions without resizing or incurring an off-design performance penalty. The system also produces minimal device drag. The novel transition control technology was shown to reduce trip drag penalties by as much as 35% to 60% when compared to correctly sized traditional trips, and increasing to as much as 190% at off-design conditions. In addition, the system can be implemented without external power. The commercialization potential for the technology is extremely promising, with applications such as micro unmanned air vehicles, high-altitude long-endurance aircraft, Mars exploratory flyers, and propeller systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed transition control technology (TCT) has significant potential application in several NASA programs. The TCT system could be fielded in several NASA aircraft unmanned systems, including micro-UAVs, high-altitude long-endurance remotely operated aircraft (HALE-ROA) for reconnaissance, and Mars exploratory aircraft. NASA designers will be eager to exploit the advantages of the current TCT technology in both airfoil designs and propeller systems. The transition control technology will deliver revolutionary performance as compared to traditional designs in a low risk package. The system will be applicable throughout NASA's high altitude unmanned and micro-UAV aviation community.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercialization potential is excellent for a robust and reliable low Reynolds number transition control system. Potential customers include the U.S. Military and radio control aircraft hobbyists. The U.S. military has begun to dramatically increase its use of unmanned aircraft. With electronic payloads becoming increasingly smaller, the opportunity for the application of micro-UAVs to military missions will increase. The revolutionary performance offered by the TCT technology for this class of vehicles will make the technology extremely appealing. The hobbyist market, particularly in the area of propellers and airfoils for radio-controlled aircraft, is a prime candidate for use of this technology. Airfoils and propellers designed using RHRC's transition control technology will provide radically enhanced performance. Both commercial suppliers of hobby aircraft and the military micro-UAV community will find the technology extremely appealing, allowing significant commercialization potential.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Two novel flight control actuation concepts for UAV applications are proposed for prototype 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 APPLICATION(S) (LIMIT 150 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 APPLICATION(S) (LIMIT 150 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: (Firm Name, Mail Address, City/State/ZIP, Phone)
Zona Technology, Inc.
9489 E. Ironwood Square Drive, Suite 100
Scottsdale,AZ 85258-4578

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dario Baldelli
dario@zonatech.com
9489 E. Ironwood Square Drive, Ste 100
Scottsdale,AZ 85258-4578

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ZONA Technology (ZONA) proposes to develop an enhanced model updating nonlinear system identification (MUNSID) methodology that utilizes flight data with state-of-the-art control oriented techniques. The MUNSID toolbox augments the current match-point solution approach using the mu-analysis method with identified nonlinear operators. The procedure calls for a high-fidelity linear aeroelastic model to be tuned quickly with available aeroelastic/aeroservoelastic flight data sets, while block-oriented models are used to highlight the underlying nonlinear structure of the dynamic system. This framework is capable of accounting for several nonlinearities including those due to aerodynamics, structures, control/actuator, and/or geometry. Specifically, this on-line Flutter/LCO predictor can be used to accurately estimate a supercritical LCO case if the global nonlinear dynamic behavior is described throughout a hardening nonlinearity, as well as a more dangerous dynamic behavior, denoted as subcritical LCO, could be developed if a global softening nonlinearity is identified. The devised MUNSID Toolbox will become the flight control engineer's "every day tool" to predict on-line Flutter/LCO phenomena. In Phase II, MUNSID will be updated with fast and computationally efficient routines for system modeling, LFT representation, identification of nonlinearity, estimation of uncertainty, and stability analysis. Deliverables include the MUNSID production software including a GUI, a library of S-functions, and the related user manuals.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Nonlinear identification, modeling and analysis software for aeroservoelastic instability clearance is still non-existent, leading to cautious and expensive flight test procedures. The proposed toolbox will become a standard analysis package for aeroservoelasticity. 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 toolbox is aimed at providing an expedient on-line prediction capability that integrates with current NASA procedures in the control room. The methodology for a nonlinear Flutter/LCO predictor tool will complement and enhance the current capability for predicting instabilities during envelope expansion. The MUNSID Toolbox will be applicable to flutter envelope expansion programs of military, civil transport as well as general aviation aircraft where the design is aeroelastically dominated or the potential exists for aeroelastically induced instabilities.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
ZONA's business plan for this toolbox will follow the existing ZAERO product/service strategy. The toolbox will be marketed towards the flight test applications on a wide class of aerospace vehicles: (a) USAF's UAV/UCAV, joint-wing sensor craft, (b) Next generation Micro Air Vehicle (MAV) with enhanced control/maneuver capability, (c) DARPA Morphing aircraft program, and (d) Boeing's 787 and executive jet designs of Cessna, Raytheon, etc. Potential customers for the MUNSID Toolbox include engineers in the automotive industry, developing suspension and powertrain systems, aerodynamic developments for race cars, as well as for nautical engineers doing ship design and analysis, particularly mitigating vibrations and high acoustic noise due to large motors. Other areas of application include aircraft carrier vibration issues, analysis of power blackout, and in flight dynamics for complex flying control systems for manned and UAV. It will be a powerful tool for the aerospace industry performing health management within the health monitoring of flexible extraterrestrial vehicles and in vibration analysis for large solar panels and/or antennas in satellites. In addition, the MUNSID toolbox is envisioned as a diagnostic measure technology for the neural control of the cardiovascular system in humans.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Research South, Inc.
555 Sparkman Dr, Suite 1612
Huntsville,AL 35816-0000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Lawrence Spradley
lws@hiwaay.net
555 Sparkman Dr. Suite 1612
Huntsville,AL 35816-0000

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovations proposed are twofold: 1) a robust unstructured mesh movement method able to handle isotropic (Euler), anisotropic (viscous), mixed element (hybrid) and generalized polyhedral unstructured grids for CFD applications, particularly, CFD-based design optimization, and 2) a robust method to automatically insert high quality anisotropic prismatic (viscous boundary layer) cells into any existing CFD mesh. All objectives in Phase I were met and all tasks were completed as proposed. The methods worked very well for both 2D and 3D geometries, for tetrahedral, hexahedral, and general polyhedral element types, and for the simple viscous meshes. In Phase II, we will extend the software into a general purpose package for use by NASA, other Government agencies, and commercial customers. We will implement our 3D viscous mesh generation method including a general solution-adaptive meshing capability. We will develop the software necessary to compute sensitivity derivatives of the mesh operations. Two important software design goals for our final Phase II software are ease-of-use and convenient access to its functionality. We will develop two types of user interfaces: graphical access (for the end-user) and programming access (for integration with flow solvers). We will assemble all of the methods developed in Phase II into a single, coherent, design-oriented, product-version code with extensive focus on incorporating a parallel processing capability into the software. The verification & validation plan will follow the industry-standard approach now used by commercial software houses and will include an extensive set of NASA-relevant test cases. The software will be documented and delivered to NASA. The Phase II software has significant potential for commercialization and sales in the non-Government sector.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This software package is a major improvement in the power and quality of software design tools available and represents an enormous benefit to NASA. The resulting software product is a major advance in the state-of-the-art and will represent the first breakthrough in this technology area in many years. This will provide NASA with a powerful software tool to perform very efficient and rapid design assessment of evolving next generation space vehicles. Our software adds critical functionality to unstructured grid CFD software already in use at several NASA Centers including: NASA Dryden's unstructured adaptive-mesh, design optimization code SAMdesign; NASA Langley's design optimization code FUN3D and aeroelasticity code USM3D; and NASA Marshall's generalized mesh CHEM code and combustion code FDNS. Since our new mesh methods are also applicable to structural finite element analyses, the various multidisciplinary analysis and optimization efforts at NASA can benefit from our software. Given the ability to quickly modify and analyze trial geometry configurations, development of revolutionary design concepts will be facilitated.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The following are some of the many Non-NASA commercial applications for the generalized meshing software. (1) pollution dispersion from stacks of industrial processing plants, (2) design of viscous mixing processes for chemical manufacturing companies, (3) computation of exhaust flow from automobile and bus exhaust systems, (4) design of more efficient internal combustion engines, (5) commercial airplane design for improved fuel economy (6) analysis and design of waste disposal systems, (7) design of air conditioning systems for large buildings, (8) air quality modeling for large-city streets.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This effort undertook the creation of a Surface Operations Data Analysis and Adaptation (SODAA) tool to store data relevant to airport surface research and facilitate searching, visualizing, and analyzing that data, with the goal of improving understanding of airport surface operations. Data mining capabilities will, for example, support research of taxi routing and departure sequencing strategies used by air traffic controllers. The SODAA tool will reduce the time and cost required to build and maintain Surface Management System (SMS) adaptations. Finally, the SODAA tool will facilitate benefits and other studies by readily providing large sets of data without each researcher needing to separately collect appropriate data. In Phase 1, we designed and built a portion of the envisioned SODAA database as well as a limited visualization tool that, after Phase 2, will allow users to query the database and view the results in a variety of different formats. In addition, users will be able to add new analysis capabilities by creating plug-in modules. In addition, we conducted a variety of analyses of SMS data, providing insight into surface operations. Finally, we identified which SMS adaptation files could be developed using the SODAA tool.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The significant costs of aviation delays and the opportunity to reduce such delays through this effort result in a strong market for the SODAA technology. The application of this work at NASA can be grouped into two categories: supporting the development of airport adaptations for surface automation systems and supporting fundamental understanding of surface operations and traffic management. In addition, SODAA provides a repository for data that may be used in other NASA projects.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include use of SODAA by the FAA, air carriers and airport authorities, and other (e.g., university) researchers. The FAA will use the SODAA tool in the same ways as NASA, both to support developing and maintaining airport adaptations for automation systems that include an airport surface component and to gain fundamental insight into current operations. Air carriers will use SODAA or Mosaic ATM's services leveraging SODAA to improve efficiencies in their operations or planning decisions at hub airports. Finally, airport authorities have expressed interest in SODAA's data recording capabilities for improving the accuracy of their billing for landing/takeoff operations and noise abatement functions.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
KALSCOTT Enginering, Inc.
3226 S.W. Timberlake Ln.
Topeka,KS 66614-4515

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Tom Sherwood
tom.sherwood@kalscott.com
3266 S.W. Timberlake Ln.
Topeka,KS 66614-0000

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A method and device for situational awareness for unmanned air vehicles is presented. This enables integration of UAVs into the national airspace in a safe manner, equivalent to the level of safety of manned aircraft. Phase I results are presented and discussed. Phase II plans are discussed in detail. The Phase II will culminate in flight tests of the proposed gear. Alignment with national initiatives such as Access5 is discussed.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA, and several other agencies are evaluating UAVs for science, homeland security and military missions. The FAA requires that UAVs be allowed to fly in the National Airspace only if they have a level of security equivalent to manned aircraft. The proposed hardware addresses this issue. NASA has a strong civilian UAV effort currently to support Suborbital Earth Science missions. This device can be used on such NASA UAVs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The transponder can be used for airspace integration of UAVs. Such vehicles are now increasingly used for homeland security, science, civilian, and homeland security missions. Specific military end users have been identified.

PROPOSAL NUMBER:	04-II B1.01-8892
PHASE-I CONTRACT NUMBER:	NNC05CA35C
SUBTOPIC TITLE:	Exploiting Gravitational Effects for Combustion, Fluids, Synthesis, and Vibration Technology
PROPOSAL TITLE:	CMOS-MEMS Microgravity Accelerometer with High-Precision DC Response

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Evigia Systems, Inc.
2805 Windwood Dr., #10
Ann Arbor,MI 48105-1487

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Navid Yazdi
nyazdi@evigia.com
2805 Windwood Dr. #10
Ann Arbor,MI 48105-1487

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this Phase II SBIR project a high-sensitivity low-noise all-silicon CMOS-MEMS accelerometer for quasi-steady measurements of accelerations at sub 1 micro-g levels will be developed. The outcome of the project is a capacitive microaccelerometer with a resolution of 90ng/sqrt-Hz over +/-0.1g range for Type A sensor and 0.8ug/sqrt-Hz over +/-1g for Type B sensor with programmable bandwidth from DC to programmable 0.1Hz-100Hz. The accelerometer module includes integrated low-noise CMOS circuitry with active offset and low-frequency noise cancellation to enable high-precision DC measurements. The high-performance of the sensor is enabled by innovation in both MEMS accelerometer and readout circuit technologies: i) Single-crystalline silicon capacitive accelerometer structure. The device has high sensitivity and low thermo-mechanical noise; ii) Innovative high-yield fabrication process that enables formation of high-sensitivity devices on top of CMOS wafers; iii) New and improved low-noise capacitive sensor readout CMOS circuit. This novel microaccelerometer has several NASA applications including measurement of residual accelerations on spacecraft and ground-based low-gravity facilities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed CMOS-MEMS accelerometer will reduce the size, mass, power requirements and cost of the instruments for measuring the residual accelerations on spacecraft or in ground-based low-gravity facilities. By using innovative device and circuit technologies the proposed MEMS sensor can resolve sub micro-g quasi-static accelerations as solicited by GRC and MSFC under topic B1.01 (Exploiting Gravitational Effects for Combustion, Fluids, Synthesis, and Vibration Technology). Also this device can be employed for space drag measurements, space platform stabilization, and miniature self-contained or GPS-augmented navigation systems for micro-satellites, spacecrafts, aircrafts, and ground vehicles.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High precision accelerometers with micro-g sensitivity have several other applications including self-contained and GPS-augmented navigation and guidance systems, seismometry for oil-exploration and earthquake prediction, aerial mapping of gravitational forces for mining and natural resources exploration, tilt measurements and platform stabilization, and underwater acoustic measurements. The impact of low cost, small, high-performance micromachined accelerometers in these applications is not just limited to reducing overall size, cost and weight. It opens up new market opportunities such as personal miniature navigators.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Vision for Space Exploration demands increasing reliance on real-time trace gas monitors onboard spacecraft. Present grab samples and badges will be inadequate beyond low-Earth-orbit. New better monitors will be critical components for early detection of fire, release event monitoring, crew habitability, and air revitalization processes. The danger from fire and toxic releases aboard spacecraft is constant with only moments for detection and contravention. Spacecraft are unique high-value systems where failure is measured in lives, dollars, time, and public perception. Space crews have little chance of escaping vessels that cannot continue to support life. It is imperative to detect danger in these closed-cycle environments at the earliest possible moment. Present fire detectors onboard spacecraft are inadequate due to fatigue, sensitivity or time response. Smoke detectors are insufficient for detecting the earliest stages of combustion. Further, smoke detectors will become increasingly unreliable due to false alarms upon exposure to dust particulates from the Moon and Mars. Sensors are needed to directly detect the molecular products of combustion. Vista Photonics proposes to develop rugged, compact prototype optical fire detection and contaminant monitoring instrumentation capable of selectively measuring a critical suite of contaminants at parts-per-million (ppm) or better sensitivities in a few seconds.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immediate targeted application for NASA is fire detection and contaminant monitoring on spacecraft. Phase II prototypes will be capable of selectively detecting HCN-HCL-HF-CO-acetylene and methane. The emerging technology will be suitable as an event monitor for specific release events on the ISS, particularly ammonia and HF. ISS is the test-bed for developing CEV sensor technology. Other applications include fire detection on aircraft and high-value installations, trace atmospheric species detection on manned and unmanned aircraft, gas sensing in air revitalization and water recovery processes, and a macroscopic atmospheric composition monitor.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase III commercial applications abound for sensors whose performance and physical characteristics are suitable for spaceflight. Vista Photonics will focus initial commercialization efforts on two of these, moisture contamination in semiconductor process gases and acetylene contamination of chemical manufacturing feedstock gases. Both contaminants were detected at relevant low-ppb levels during the Phase I project. The fully-developed Phase II instruments shall offer a compelling and desirable blend of performance, affordability, compactness, simplicity and ease-of-use relative to present commercial product offerings in both industries. Other applications include environmental monitoring, occupational safety, biomedical breath diagnostics and homeland security monitoring of high-value buildings, rail, and mass-transit.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The technical objective of the Phase II project is to provide a more complete investigation of the long-term needs of the simulant community based on the updated NASA outline for exploration, including potential landing site designations, the types of technologies currently funded for research, and timelines for future development. Using this information, a number of prototype simulants will be created and analyzed for their ability to meet individual application requirements. If successful, each prototype simulant could then be produced on a larger scale through a Phase III contract or by a privately funded commercial effort. The current simulants to be addressed by the Phase II include a spherical glass inclusion JSC-1a derivative for improved physical lunar mare characteristics, a terrestrially produced lunar agglutinate inclusion JSC-1a derivative for true chemical and mechanical property simulation, a lunar highlands simulant for simulation of over 80% of the lunar surface, and improved JSC Mars-1a simulant to meet the immediate needs for Martian experimentation and testing. We anticipate that through these four prototypes, the majority of the needs of the scientific and engineering communities can be met with a high degree of fidelity, improving NASA's ability to successfully explore the Moon and Mars.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Significant research and testing is crucial for successful robotic and human long duration lunar or Martian missions. Over the next decade, NASA will develop techniques for in-space fabrication of critical path components, transportation and habitation equipment, health and reliability of advanced life support systems, and processes for in situ resource utilization. These projects, including currently funded programs, require lunar and Martian regolith simulants of the highest fidelity possible. To meet this immediate demand, NASA approved a Phase III contract for ORBITEC to produce the lunar simulant JSC-1a in late 2005. Unfortunately, NASA's future needs demand next generation simulants that better support key technical requirements. Well characterized simulants that match landing site requirements (such as highlands or Martian prototypes) or better match physical properties (such as agglutinate simulant or spherical glass inclusion simulant) will improve NASA's ability to successful explore the moon and Mars.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The commercial production and distribution of improved lunar and Martian simulants is a goal of both the scientific and NASA community. This approach provides improved access and tracking of simulant users, both scientific and educational. ORBITEC is currently funding the commercial production of fifteen tons of the lunar simulant JSC-1a, which we anticipate to quickly sell due to its tremendous appeal for schools and outreach programs. The simulant will be added to PLANET's (ORBITEC's sister company) line of plant growth kits, along with a new line of chemistry and geology experiments. Other educational supply companies have already placed orders for material as well, and several leading distribution companies have expressed interest in carrying simulant products as soon as they are available. In addition to education, programs such as Centennial Prize and commercial space ventures have energized interest in space exploration, space tourism, and marketing of space souvenirs and displays.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ZYVEX Corporation
1321 N. Plano Road
Richardson,TX 75081-2426

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Gobinath Balasubramaniyam
gbala@zyvex.com
1321 N. Plano Road
Richardson ,TX 75081-2426

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Zyvex in cooperation with Prairie View A&M (CARR) and Boeing will develop a space radiation shielding multi-functional material that will provide high energy radiation shielding required to protect astronauts on extended missions, strong enough to be used as an integral structural material and tough enough to survive micro-meteor impacts, provide EMI shielding, and enhanced thermal conductivity. The team will also develop an improved protocol for testing radiation shielding material. This effort will entail developing a composite material which uses proven radiation shielding material Polyethylene(PE), as its primary constituent in the form of very strong/tough Spectra fibers woven into a 3D fabric. In Phase 1 we demonstrated that, compared to bulk PE, this composite approach has significantly improved mechanical properties, excellent electrical conductivity, good Electro Magnetic Interference (EMI) shielding properties, and maintains excellent space radiation shielding properties of PE. We also demonstrated exposure to large doses of high energy actually improved the mechanical properties. In Phase II, the epoxy matrix used in Phase I will be considered along with Cyanate Esters, and Polyimides, As in Phase I, coating the PE fabric and reinforcing the matrix material will be ultra-high strength, highly conductive carbon nanotubes (CNTs). Zyvex's unique and commercially successful CNT processing technology will be adapted to maximize the transfer of the extraordinary mechanical, electrical, and thermal properties of CNTs to the composite structures. The work plan includes approaches to overcome CNT processing and delamination issues discovered in Phase I. CARR will carryout more extensive radiation testing with several ions at different energies. Boeing which has significant interest in developing long term space exploration will guide the development of the material to meet specifications for planned applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's needs for radiation shielding for extended space missions is unquestioned. Polyethylene is the best known material for shielding high energy particles but is parasitic weight if it does not serve any other function. A material with good radiation shielding capabilities that can also have the strength to be an integral structural component, have the toughness to deal with micro-meteor impacts, and provide additional EM shielding clearly has value to NASA. In addition to the Phase I SBIR we are just completing with Marshall, we also are working on a Phase II SBIR with NASA JSC to develop CNT composites with ultra-high specific strength for demanding space vehicle applications. We have had successful commercial spin-offs from this program listed below. This work has been so successful that we are entering into a Space Act Agreement with JSC to collaborate with them in the pursuit of this technology. The collaborative work on this Space Act Agreement is expected to include but go beyond structural applications; we also expect that other advanced material applications such as space suit fabrics and high surface area support for CO2 scrubbing will be explored.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The NASA funded work on CNT/Polymer composites have already produced two commercial successes. Epoxy concentrates with dispersed CNTs are being sold to Easton Sports who are using this CNT material to make bicycle parts (being used in the 2005 Tour de France), baseball bats (which were used in the College World Series), and hockey sticks. Aldela, the largest manufacturer of composite golf club shafts is also using this technology in their product. We have had eight different industrial research contracts, many of which are ongoing, to develop CNT composites for a variety of applications. Applications include structural materials, thermal interface materials, ballistic protection materials, and others. We are also working with a number of other companies either in a collaborative development mode, or selling them materials for testing and development. We also have a DARPA program in their Defense Sciences Office to develop ultra-high strength CNT fibers. This work has led to a follow on program where Zyvex will be a subcontractor to Hexcel in developing a new generation of high strength fibers. This program has been awarded and is currently being negotiated.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Novawave Technologies
230A Twin Dolphin Drive
Redwood City,CA 94065-1411

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joshua Paul
jbpaul@novawavetech.com
230A Twin Dolphin Drive
Redwood City,CA 94065-1411

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Small Business Innovative Research Phase II proposal seeks to develop a low cost, robust, highly precise and accurate CO2 monitoring system. This system will employ a novel mid-infrared laser source, which was successfully demonstrated during Phase I along with a bench-scale laboratory sensor. Quantitative analysis of the Phase I results showed that the goal of determining the mole fraction of CO2 in atmospherically relevant gas mixtures with a precision of 0.05% min-1 was achieved. The Phase II project will significantly refine approach and improve the long term stability such that an onboard gas calibration system needs to operate at most once-per-hour. The resulting compact, fully integrated Phase II prototype will enable completely automated CO2 concentration measurements to be routinely performed with unprecedented accuracy. Commercial systems based on the Phase II prototype will be refined and marketed during Phase III. Additionally, the core technology can be applied for the detection of other target species such as CO2 isotopes, methane, and CO.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA's Fundamental Biology Program seeks to improve our understanding of gravitational effects on plants and animals. The success of this proposal will directly impact this effort by providing compact fieldable CO2 analyzers with the requisite precision and accuracy to aid this effort. Additionally, NASA's Earth Science Enterprise has taken a lead role in understanding Earth's atmospheric dynamics. In particular, to better understand climate change and global warming, a more detailed knowledge of carbon exchange between terrestrial ecosystems and the atmosphere is required. The success of this effort will directly impact this area as well.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The worldwide market for low cost, high precision CO2 monitors is quite large due to the need to monitor greenhouse gas emissions and enforce world-wide emissions standards. Additionally, the core technology is promising for the detection of other target species such as CO2 isotopes, methane, and CO. Commercial arenas for the technology therefore include trace gas monitoring, pollution monitoring, and industrial process monitoring.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Quantum Logic Devices
7801 North Lamar, Suite B-161
Austin,TX 78752-1017

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Louis Brousseau
lou@quantumlogicdevices.com
7801 North Lamar, Suite B-161
Austin,TX 78752-1017

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase II program builds from the successful Phase I efforts to demonstrate that Quantum Logic Devices' nanoelectronic platform for biological detection could detect binding of Epo, TNF-alpha, IL-6, and IGF-1 in saline and serum without labels. The creation of an electronic "direct detection" platform for proteomics, enables rapid point of care monitoring of metabolic analytes in microgravity. This Phase II proposal will build working prototypes based on PDA-style electronic data capture with disposable assay cartridges for the analytes demonstrated in Phase I.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The product of this program is a handheld bioassay system that would be ideally suited for all biomedical research and diagnostic needs of current and future space missions. Real-time, quantitative monitoring of proteomic analytes will answer real questions about the metabolic and physiological changes induced by microgravity and space flight.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology will be a key part of the rapidly emerging paradigm of telemedicine, and provide point of care diagnostics capabilities, which are the most rapidly growing segment of the medical testing market.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nanotrope, Inc.
2033 Cambridge Ave
Cardiff,CA 92007-1707

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Donald Ackley
donackley@cox.net
2033 Cambridge Ave
Cardiff,CA 92007-1707

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
During this Phase II program we propose to build on the key aspects of the nanodroplet encapsulation technology to demonstrate optimized formulation and encapsulation of protein drugs. The ability of the nanodroplet generator to produce nanoscale drug "containers" with designer characteristics provides us with a distinct advantage in targeting protein containing vesicles to diseased cells and organs. We plan to target cancerous cells and tumors using our engineered drug vesicles, with specifically designed lipid outer layers as well as targeted surface functionalization to improve drug uptake by the cells, reduce toxicity, and otherwise improve safety and efficacy. The optimized vesicles will result in improved stability and enhanced control of pharmacokinetics in both cell lines and animal models.The nanodroplet platform will be scaled up to produce gram quantities of engineered vesicles with a monodisperse size distribution and a target size of 200nm.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The immiscible nanodroplet processor provides NASA with a platform that will impact space driven goals for biotechnology research as well as manned exploration activities. The nanodroplet technology lends itself to several important applications in drug formulation, diagnostics and sample preservation. For drug formulation applications, it is envisioned the astronauts on long-term missions may be provided the capability to program specific drug formulations for personalized space medicine care. Formulations may be tailored to meet the pharmacokinetics of drugs administered in space, for specific applications that include countermeasures for space borne afflictions such as bone loss due to microgravity and radiation exposure. Other applications may include the mixing and dosing of nutriceuticals to ensure astronaut health and peak performance and psychotherapeutics to treat long-term isolation experienced on extended missions. Finally, drugs for the treatment of diseases such as a cancer that may develop on a long-term mission to Mars may be of interest. The nanodroplet technology may also have applications in space medicine diagnostics and continuous water sampling and monitoring. For astronaut personal diagnostics, the nanodroplet approach may be utilized to analyze blood, urine or saliva by sampling, targeting and/or concentrating specific analytes. Similarly, the nanodroplet approach may be applied for monitoring the safety of drinking water used by the crew

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Nanotrope nanodroplet encapsulation technology tremendous potential for commercialization in such diverse areas as targeted drug therapy, personalized medicine, and point of care testing, especially for patients where samples are sub-optimal and the need for treatment may be frequently adjusted. Clearly, the ability to produce functionalized particles has tremendous potential for cancer therapy. With the nanodroplet technology, we can customize drug formulations for small, at-risk populations, or even for individuals on a rapid turn-around basis. The technology provides a compact device that is capable of titrating particle compositions on demand, which will allows care givers the new ability to adjust dosage levels to meet the need of the individual according to the patient's response to initial treatments. In addition, our technology is operated by inexpensive microfluidic devices that are readily adapted to conventional drug delivery instruments such as syringes or inhalers. Thus, we anticipate the facilitated integration of our on-demand, monodisperse drug formulation technology with a reduced time to market.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Cooling Technologies, Inc. (ACT), supported by Hamilton Sundstrand, proposes to develop a heat pipe heat exchanger that is low mass and provides two levels of isolation between fluid streams. It has potential applications in thermal control of manned spacecraft and a number of military and commercial equipment and processes. Phase I has successfully demonstrated the feasibility of the heat exchanger technology in effectively exchanging heat between two fluid streams while providing reliable separation of the fluids. Components and subscale heat exchangers were tested and the results compared with the heat exchanger design model. The model demonstrated an accuracy of within 8% in its predictions. The principal Phase II objective is to fully demonstrate the proposed technology by refining and further developing the prototype heat exchanger into a qualified full scale design. The project will demonstrate the heat exchanger's long-term compatibility through life test of heat exchanger components and qualification test of engineering units at representative thermal, acceleration, shock and vibration conditions. The Phase II results will elevate the technology to a TRL 6: Prototype demonstration in a relevant environment. The follow-on Phase III will conduct flight qualification test of the technology to address micro gravity operation issues.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications of the heat pipe heat exchanger technology include thermal control of manned spacecraft including the Shuttle, Space Station, and the planned CEV for Moon and Mars exploration missions.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Since manned spacecraft are not built in large quantities, Non NASA applications of the heat pipe heat exchanger technology include: ? Naval Turbine Bleed Air Coolers. ? Ammonia Refrigeration Plants. ? Food or Pharmaceutical Processing. ? Industrial Chemical Processing. ? Telecommunication outdoor cabinet cooling.

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

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Development of a microgravity and hypogravity compatible catalytic methane pyrolysis reactor is proposed to recover hydrogen which is lost as methane in the conversion of carbon dioxide to water via the Sabatier process. This will close the hydrogen loop which currently requires 50% resupply and also produce carbon nanotubes, a high value product which may be employed as an adsorbent or catalyst for removal of atmospheric trace contaminants, thus further lowering the resupply burden for manned spacecraft. Microgravity compatibility of Gradient Magnetically Assisted Fluidized Beds (GMAFB) has been demonstrated through a series of KC135 flight experiments. Metallic cobalt, which has been fluidized in microgravity using the GMAFB method, is an excellent catalyst for promotion of methane pyrolysis. Recently, fluidized bed catalytic methods have been shown to efficiently recover hydrogen, and produce single walled carbon nanotubes. Using the GMAFB method, this process can be rendered totally compatible with operation in the microgravity of spaceflight or the reduced gravity of planetary environments. By recovering all of the hydrogen which is lost as methane in the Sabatier reactor, the requirement for production or resupply of hydrogen is reduced to the absolute minimum.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The NASA application of this technology will be as Flight Hardware for deployment in support of future long duration exploration objectives such as a lunar mission, lunar base, Mars transit or Mars base. The primary application will be for the recovery of hydrogen lost in the Sabatier process for CO2 reduction to produce water in Advanced Life Support systems. Secondarily, this process may also be used in conjunction with a Sabatier reactor employed for propellant and fuel production from Martian atmospheric CO2.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A commercial application with extremely high economic potential is the production of carbon nanotubes (CNTs). CNTs are nanomaterials with unusually high strength, low density, excellent electrical conductivity, and other properties with numerous potential applications including: as nanometer sized semiconductor components and devices, field emission displays, hydrogen storage, sensors, energy storage and energy conversion devices, catalysts, conductive and high strength composites. Currently prices for CNT range from $30/gram to $2,000/gram, owing to the lack of methods for large-scale synthesis. The proposed technology will help to overcome this limitation.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Genexpress Informatics, Inc.
13091 Ponds Springs Road, Suite 150
Austin,TX 78729-6442

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Chin
rchin@genexpressinfo.com
13091 Ponds Springs Road, Suite 150
Austin,TX 78729-6442

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Returning men to the Moon and manned Mars missions will require advanced bioastronanutics research. One possible risk is Decompression Sickness (DCS) resulting from extravehicular activity (EVA), after exposure to habitat conditions that would be generated using available Moon or Martian resources. A key research tool to measure the onset of DCS is a Transcranial Doppler (TCD) instrument. The present research tool is bulky and does not allow for measurement of the TDC signal under astronaut stress conditions including exercise, EVA, pre-breathing prior to EVA, and work. GeneXpress Informatics, Ten X Technology and UTHSC-SA proposes to develop a fully functional TCD research device for hypobaric experiments for determining DCS risk assessment and management. GXI has develop a unique auto-focusing and steering TDC system which allows for the real time monitoring of DCS parameters during hypobaric stress activity experiments. In this Phase II program, the team proposes to (1) Define and Determine test bed requirements, (2) Identify and procure TCD components, (3) Design & Assemble the Piezoelectric Transducer, (3) Design & assemble Transducer attachment method, (4) Design, Assemble & Test Portable Instrument Electronics, (5) Develop Software for the Instrument and Development Platform, (5) Evaluate Laboratory Test Bed, and (6) Construct System Deliverable.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Advanced spaceflights will possess a number of risk. One risk area is Decompression Sickness (DCS) resulting from extravehicular activity (EVA) after exposure to habitat conditions. The proposed auto-focusing and steering ultrasonic TCD research tool will provide measurable DCS metrics and parameters to establish and model the level of risk due to these habitats & environments.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Total mortality rates in severe trauma occurrences show that 90 percent die within the first hour. This non-invasive auto-focusing and steering TCD technology developed in this program will provide an aid to paramedics in evaluating a trauma patient on site and in real-time.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Triple F, Inc.
10104 Douglas Avenue
Des Moines,IA 50322-3600

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
wilmot wijeratne
wilmot@insta-pro.com
10104 Douglas Avenue
Des Moines,IA 50322-3600

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This project is to develop versatile, low mass, energy efficient, and easily maintained multipurpose seed processing (MSP) equipment for food processing in space environments. Phase-1 of the project yielded a conceptual drawing for a MSP. Phase-II consists of six main tasks. The first model MSP will be manufactured, programmed and tested for ESM, function, and quality of processed product. The data will be used to refine the model and design multipurpose screws for the extrusion and press components of the MSP to simplify the equipment. Several models of MSP's will be fabricated and tested for versatility. The ESM crietia and functional parameters will be used to evaluate the optimum MSP for NASA applications and non-NASA applications. The final deliverables will be the test database, design drawings and the optimized MSP's for NASA and non-NASA applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The primary NASA aplication will be to perfrom a variety of food processing operations including size reduction, cooking, oil extraction, dehydration, stabilization, texturization, and expansion. This capability will lead to dry and shelf stable food products such as soy flour, textured soy protein, soy oil, breakfast cereals, expanded snacks, and pasta products. The proposed MSP will be unique in that the heat of processing will be generated internally by friction without dependence on an external heat source such as steam. The heat process will reduce microbial hazards in the space environment and also improve the stability of products by enzyme inactivation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The technology developed in this project will enable the design and fabrication of MSP's of capacities between the NASA MSP and the commercial extruders currently marketed by the contractor. Such small capacity equipment has application in two sectors: The research and development community will have the capability to process small quantities of seed material coming out of specialized varieties being developed. Also, high value raw materials available only in small quantities can be processed with the miniature MSP's. Secondly, the smallest commercial extruder/press combination marketed by the contractor has a rated capacity of 300 kg/hr. This is still too large for small agribusiness in many developing nations. This project will enable development of customized processing systems that enhance the business of the contractor in the developing nations.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
ZIN Technologies, Inc.
2001 Aerospace Parkway
Brook Park,OH 44142-1001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Alan Chmiel
alan.chmiel@zin-tech.com
3000 Aerospace Parkway
Brook Park,OH 44142-1001

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
BioWATCH is a modular ambulatory compact wireless biomedical data acquisition system. More specifically, it is a data acquisition unit for acquiring signals from biomedical sensors using modular acquisition modules attached to a common data and power bus. Several module slots allow the user to configure the unit by inserting sensor specific modules. The data is then sent real time from the unit over any commercially implemented wireless network including 802.11b/g, WCDMA, GSM, or EDGE. BioWATCH is of a distributed computing hierarchy and has a common data controller on each sensor module. This innovation allows for the modularity of the device along with the tailored ability to control the cards using a relatively small master processor. The distributed nature of this system affords the modularity, size, and power consumption that betters the current state-of-the-art in medical ambulatory data acquisition. The current state-of-the-art in biomedical data monitoring is limited in its modularity and relies on centralized computing models.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Numerous NASA applications exist in both human health monitoring and human life science experimentation. The most obvious application is support of health monitoring on human space flight and exploration missions. Additionally, numerous opportunities exist in support of ground based investigations that may or may not be directly related to human space flight. These include baseline monitoring of astronaut health, health monitoring during strenuous training procedures, on-ground evaluation of physical training techniques and muscle/bone loss countermeasures. Many experiments that have already flown on Shuttle and Station have required long duration monitoring and BioWATCH will be capable of extending the capability of such science activity.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This innovative design has obvious commercial applications for extending health monitoring outside clinical facilities and this has the potential to improve the patient's quality of life. It will provide health research institutions a flexible modular system that can be tailored to their experimentation. The modular nature of the system, use of standard communications protocols, and software will allow for economical growth of the system with the development of new technologies, e.g. greater memory storage. The proposed device and associated software could find many applications in ground based medicine and biomedical research. The tradition of long term monitoring was pioneered in the field of heart electrophysiology by Halter monitors and this has now expanded to a more generalized approach to ambula