NASA 2002 SBIR Phase 2 Solicitation

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Charles River Analytics Inc.
625 Mount Auburn Street
Cambridge , MA   02138 - 4555
(617 ) 491 - 3474

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Greg Zacharias
glz@cra.com
625 Mount Auburn Street
Cambridge , MA   02138 - 4555
(617 ) 491 - 3474

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The analysis of flight data presents us with the opportunity of sophisticated insights into the functioning of aircraft systems and into the effects of aircraft operations. However, the complexity and size of the data acquired through flight data logging represent a challenge to the most complex tools to date. The effort proposed herein sets forth a multi-phase approach for the efficient application of existing data processing, visualization and analysis techniques for the identification and characterization of safety-relevant flight conditions, and for the identification of their precursors. The approach starts by reducing the voluminous flight data into a feature-based encoding, where features used for each flight parameter type are selected to match its specific variation. The second processing phase allows domain experts to efficiently inspect the flight data starting from detected exceedances, and to formulate constraint-based hypotheses regarding co-occurring events, and possible precursors. The third phase uses the hypotheses developed during the second phase to apply constraint-based data mining techniques for the identification of patterns associated with exceedances, and to identify the precursor sets for safety-relevant flight conditions. The description of the proposed effort also includes preliminary implementation results for selected prototype components, and establishes the feasibility of the investigated approach.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
We expect the full-scope environment for Constraint-based Analysis of Aircraft Operations to have immediate and tangible benefit for the Aviation Performance Measurement System. The proposed capability provides an approach to analyzing the vast amount of data collected during routine flights, to detect and characterize behaviors that are transient, and may potentially remain undetected, and to identify their precursors. The proposed approach will offer domain experts immediate access to the important flight data analysis capabilities, and will be applicable to a variety of safety analysis problems and aircraft types. The proposed effort has also integration potential with components of the Aviation Safety Program at NASA?s Langley Research Center, and has application potential to the analysis of engine condition data for the Space Shuttle Main Engines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The non-NASA commercial applications of the technology for Constraint-based Analysis of Aircraft Operations will pursue the licensing of our constraint-based behavior verification technology to system integrators in the intelligent agent industry, and the application of the proposed approach to maintenance operations conducted by major airlines. Recent commercial scale experiments have demonstrated that the identification and recognition of safety-relevant flight and engine conditions can help airlines significantly optimize their maintenance schedule. The proposed approach would represent a new step in that direction, by helping maintenance personnel to accurately define the context in which certain engine conditions occur, and to take appropriate measures.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
WebCore Technologies Corp.
591 Congress Park Dr.
Dayton , OH   45459 - 0000
(937 ) 297 - 4200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Michael Sheppard
msheppard@webcoreonline.com
591 Congress Park Dr.
Dayton , OH   45459 - 0000
(937 ) 297 - 4200

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The goal of this program is to mature the FRF sandwich panel design for the engine fan case application. Toward this goal, the following technical objectives will be pursued. This program will demonstrate how critical structural details are incorporated with TYCOR technology, leading to unitized structures that require less post-processing than composite laminate approaches. The work will be focused on a commercial jet engine application using WebCore?s relationship with aircraft engine manufacturers to identify the best application. Structural and physical properties will be verified in each component structure as well as the final, integrated fan case.

The manufacturing processes used in the production of the engine case will be evaluated and refined. These include technologies to aid in the production of preforms, the methods for processing and molding the bodies of revolution. Of particular importance will be the molding of full-circumferential bodies and the production and molding of non-uniform cross-sections. Using the data collected during this program, a cost model will be generated to document the cost advantages of TYCOR/Resin Infusion Process technology vs. current baseline composite and metallic components. Finally, a full-scale demonstration article will be produced in which the components are integrated into the design. This fan case will show a full body of revolution with integral hard points and flange attachments.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This technology is pervasive and can be used for aerospace, marine, industrial, and transportation applications for ligtweight and durable composite structures.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This technology can be used for general aviation aircraft engines.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Advanced Projects Research, Inc.
1925 McKinley Avenue, Suite B
La Verne , CA   91750 - 5800
(909 ) 392 - 3151

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Sobota
thsobota@advancedprojects.com
1925 McKinley Avenue, Suite B
La Verne , CA   91750 - 5800
(909 ) 392 - 3155

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of the proposed Phase II effort is to transfer proven sensor technology from the laboratory breadboard to a functional flight-ready prototype for installation in an aircraft fuel tank. In the Phase I effort, a novel spectroscopic technique was shown to be an effective method for measuring oxygen concentration in harsh environments with sufficient accuracy for use in an OBIGGS system. This system utilizes rapidly scanned Vertical Cavity Surface Emitting Diode Lasers (VCSELs) to measure oxygen concentration by molecular absorption. This system can measure 1000 ppm to 100% oxygen in ambient temperatures from -60 to 150 F utilizing as the wavelength agile spectral-harmonic (WASH) technique. The wavelength agile aspect of the laser source/detection technique allows for temperature insensitive measurements of oxygen concentration over a wide range of pressures (0.3 atm to 2 atm) with high accuracy as well as with auto-calibration capabilities. The Phase II effort is focused on packaging this sensor technology in a form that is able to be inserted into an operational aircraft fuel tank and conform to a set of environmental and operational requirements as defined by both the OBIGGS needs as well as the fuel tank environment. Furthermore, achievement of the Phase II goal requires the miniaturization of the laser driver, data collection, and data processing functions into flight-scale electronic hardware.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are many commercial and military applications for an accurate and rugged fuel tank oxygen concentration sensor. The fuel tank oxygen sensor could be used in both new and retrofit commercial aircraft as a control sensor for fuel tank protection systems. The reliable and precise instrument can be used to control onboard inert gas generation systems (OBIGGS) for cargo compartment fire suppression, fuel tank inerting, and emergency breathing oxygen systems (OBOGS) for passengers and crew. The key to the commercial viability of this product is the accuracy of the sensor, its ability to handle harsh environments including highly variable temperatures and pressures, and its reliability and lifetime, which we have engineered into the system. The long operating lifetime and stability of this measurement system in challenging operating environments are superior to existing oxygen measurement strategies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This type of sensor can also be used to monitor the air/fuel ratio in terrestrial gas turbine and high pressure combustion systems where a rugged sensor with long operating life characteristics is needed. Also possible using this sensor is a real-time measurement of oxygen tension in respiratory gases and respiration monitoring. The absorption based technique has no biofouling effects and is nearly independent of scattering environments such as heavy droplet sprays or moisture making the sensor useful in biological measurements.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Williams-Pyro, Inc. (WPI)
2721 White Settlement Road
Fort Worth , TX   76107 - 1331
(817 ) 335 - 1147

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Matthew Scarpino
matt.scarpino@williams-pyro.com
200 Greenleaf
Fort Worth , TX   76107 - 1471
(817 ) 872 - 1500

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Within Phase 2, Williams-Pyro has designed, developed, and demonstrated a system for locating arc faults along aircraft cable. This fault localization is performed using signal reflectometry, in which an electrical waveform is transmitted through a length of wire. After the reflection is received, the characteristics of the reflected signal will be used to determine how far away the arc fault is located. After miniaturizing this system, it will be possible to integrate this functionality within a Texas Instruments' arc fault circuit breaker. In this manner, TI's AFCB's will be able to tell maintenance personnel where to look in order to perform repairs on the aircraft cable

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This system will be able to reduce the maintenance time and effort involved in repairing faulty electrical cable on NASA aircraft. After an arc fault has occurred, the Smart Wiring Infrastructure Fault Tester (SWIFT) will activate, using signal reflectometry to determine where the arc fault is located. Then, the SWIFT-enabled arc fault circuit breaker (AFCB) will be able to display the fault's location to the maintainer, saving hours of hunting for the damage within the wire. Texas Instruments has agreed that, given effective operation of the SWIFT functionality, they will be willing to consider integrating a SWIFT application specific integrated circuit (ASIC) within their Klixon family of aircraft circuit breakers

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This system will be able to reduce the maintenance time and effort involved in repairing faulty electrical cable on commercial aircraft. Following an arc fault, the Smart Wiring Infrastructure Fault Tester (SWIFT) will activate, using signal reflectometry to determine where the arc fault is located. Then, the SWIFT-enabled arc fault circuit breaker (AFCB) will be able to display the fault's location to the maintainer, saving hours of hunting for the damage within the wire. Texas Instruments has agreed that, given effective operation of the SWIFT functionality, they will be willing to consider integrating a SWIFT application specific integrated circuit (ASIC) within their Klixon family of aircraft circuit breakers

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Triton Systems, Inc.
200 Turnpike Road
Chelmsford , MA   01824 - 4000
(978 ) 250 - 4200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mr. Norman Rice
nrice@tritonsystems.com
200 Turnpike Road
Chelmsford , MA   01824 - 4053
(978 ) 250 - 4200

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a novel high temperature PMR-RTM polyimide resin with a low melt viscosity (<5 Poise at 288 ?C) that will address the NASA-GRC need for advanced materials for lightweight propulsion systems for reduced emissions. Triton?s proposed innovative research will focus on developing a novel PMR-RTM polyimide resin that has a very low melt viscosity (1-5 Poise), excellent thermal stability and mechanical performance comparable to PMR-15. This resin will allow out of autoclave manufacture of complex shaped parts, and the size of the part will not be limited by the size of the autoclave

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Development of new low melt flow viscosity (RTM/VARTM), environmentally friendly high temperature polyimide resins would allow ?out-of-autoclave? manufacturing of large structures such as large composite tanks for the next generation Reusable Launch Vehicles (RLVs). Currently the size of the autoclave predicts the size of the components that can be fabricated, which is a limitation for development of the next RLVs

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Triton has teamed with end users to evaluate the development of the new RTM/VARTM high temperature resins for compatibility with their current composite manufacturing. This teaming arrangement will assist Triton to develop the resin within the manufacturer production specifications. The potential commercial applications are aircraft jet engines, rocket and turbine engines, and auxiliary power in aircraft and space vehicles.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ceramatec, Inc.
2425 South 900 West
Salt Lake City , UT   84119 - 1517
(801 ) 978 - 2119

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Patricia Vaughn
patricia@ceramatec.com
2425 South 900 West
Salt Lake City , UT   84119 - 1517
(801 ) 978 - 2119

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is an integrated hybrid solid state electrochemical system providing co-generation of high purity hydrogen and electric power. The embodiment is a physical, chemical and thermal integration of three processes: (1) production high purity hydrogen, (2) electrochemical partial oxidation of hydrocarbon fuel, and (3) power generation by a solid oxide fuel cell. This highly integrated, multi-function system eliminates any need for the CO shift and cleanup process steps currently required to generate hydrogen for use in Proton Exchange Membrane fuel cell power plants being considered for aircraft electric propulsion and power needs. It also eliminates the efficiency penalty imposed by use of conventional partial oxidation reformers. Thermal integration of the endothermic hydrogen generation processes with the exothermic SOFC operation achieves several benefits, notably higher efficiency by chemical recuperation and much lower air pre-heater duty (size, weight and cost) by eliminating the need for excess cooling air. The process facilitates sequestration of fuel carbon content by segregation of product CO2 from non-condensable gases. This innovation closes a significant void in the technology required to implement efficient, quiet and clean electric aircraft propulsion and power systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed innovation would find application in meeting NASA needs related to:
? Fuel processing for electric aircraft propulsion and auxiliary power systems
? Ground based hydrogen production with CO2 sequestration

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The proposed innovation would be generally applicable to the following non-NASA commercial applications:
? Aircraft and automotive auxiliary power
? Highway truck hotel power
? Fuel processing for automotive fuel cell electric vehicles
? Point of use hydrogen generation
? Stationary electric power generating plants

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Titech International, Inc.
4000 West Valley Boulevard
Pomona , CA   91769 - 3060
(909 ) 595 - 7455

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Edward Chen
ti_castings@msn.com
4000 West Valley Boulevard
Pomona , CA   91769 - 3060
(909 ) 595 - 7455

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lattice block structures are innovative periodic cellular materials that derive their outstanding mechanical performance from a structure of highly ordered internal triangles, rather than the properties of the parent material. They are innovations that can provide tremendous opportunities for weight and cost reduction in future aerospace and non-aerospace systems. To date, lattice block structures have been successfully fabricated for a number of ferrous and non-ferrous metals, but not extremely difficult to cast reactive metals such as titanium-based alloys. As titanium is one of the most important metallic materials in existence today, with growing importance in aerospace systems due to its superior strength-to-density, high temperature strength, and corrosion resistance, titanium alloy lattice block structures offer significant benefits to NASA and the industry if they can be successfully produced. Consequently, the purpose of this SBIR Phase II effort is to demonstrate the feasibility of casting full scale lattice block structures from titanium alloys using a proprietary investment casting process. A successful Phase II project paves the way to manufacturing actual lattice block structural components in Phase III and beyond, providing the necessary foundation for a more widespread acceptance of this unique technology in the industry.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Titanium-based alloys, including gamma titanium aluminides, are high temperature materials that can meet the ever-increasing demands for more robust, higher temperature-tolerant, and lighter weight hypersonic vehicle airframe components for commercial and military systems. Titanium and gamma lattice block materials can be used as low weight structures within these applications. For example, gamma lattice block structures could be considered for sandwich structures for thermal protection system for the reusable launch vehicle.

Other potential NASA commercial applications include aircraft engine components such as fan blade and compressor casings, nozzle flaps, and engine tiles for next generation aircraft gas turbines.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Essentially, any application and/or industry that need superior strength-to-density within relative affordability while retaining the physical properties of titanium and gamma alloys could use lattice block structures. Furthermore, those that require potential replacements for Ni-based superalloys at lower temperatures and for titanium alloys at higher temperatures could consider gamma alloys. Potential commercial applications include aero engine components, automotive engine components, and aircraft and spacecraft structural applications. Other possible uses of lattice block materials include components for furniture, shipboard structures, building structures, automotive vehicle frames, and a potentially limitless number of other possibilities.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
AUSIM, Incorporated
241 Polaris Avenue
Mountain View , CA   94043 - 4514
(650 ) 322 - 8746

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Joel Storckman
jstorckman@ausim3d.com
241 Polaris Avenue
Mountain View , CA   94043 - 4514
(650 ) 322 - 8746

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Phase I showed that the Singular Value Decompostion (SVD) technique significantly reduces processing requirements for 3D binaural rendering using Head Related Transfer Function (HRTF) datasets. Equally important, the Equivalent Source Reduction (ESR) experiments completed show a dramatic simplification of the problem of acoustically modeling surfaces, with little to no perceivable difference in the auralization.

While AuSIM3D? real-time binaural rendering capacity has grown from a few point sound sources four years ago to a few dozen point sources presently, largely due to gains in commodity processor speed, the performance improvement capacity shown by SVD and the simplification of the acoustic surface modeling problem demonstrated possible with ESR has been much more dramatic. Our results show hundreds of point sources can now be realistically rendered in real-time, and that these sources can represent a relatively large surface with negligible loss of accuracy. When these techniques are integrated in the AuSIM3D client and server applications as proposed in Phase II, it will be possible for the first time to binaurally render the sound of an acoustic disturbance applied to a surface model of considerable area.

AuSIM is also eager to optimize the ESR and SVD implementations into commercial-quality software applications to create the next generation of AuSIM3D technology. With the newly added horsepower, AuSIM3D applications will be soon able to render directly the acoustic data generated by industry standard Finite Element Analysis (FEA) acoustics vendors such as MSC/Nastran, COMET Acoustics, and ABAQUS. These firms have already signed Letters of Intent to provide whatever technical support, collaboration, and marketing resources we need to become fully interoperable with their systems. Soon designers will be able to regularly hear the acoustic performance of the surfaces they've designed while the models are still on the electronic drawing board.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
AuSIM's end product will import acoustic data from major commercial FEA packages, allowing NASA to use computer models of aerospace surfaces for airplanes, rotorcraft, and space vehicles. NASA applications that have a need to perceive the acoustic characteristics of aerospace surfaces range from assisting the design phase and the design promotion phase to, in the worst-case-scenario, assisting in the accident analysis phase.

In the design and redesign of new and existing aerospace vehicles, it will be very useful to hear the effect of airflow on external surfaces. Although noise levels alone can be quantified fairly well with existing technology, the spectral coloration that gives each sound its distinct characteristics can also determine how pleasant or unpleasant the sound will be to listeners. The acoustic comfort level of the crew and passengers inside the craft is an important design factor, as it will affect the flight crew's level of fatigue, which will affect their ability to operate the craft safely.

Another factor of concern to NASA engineers is the sound generated by an aircraft or spacecraft that reaches the ears of people on the ground. Our end product will enable a design to be simulated under a range of normal operating conditions, and enable the completion of a perceptual study that will help determine which designs will have the minimum negative psychological impact on passengers, ground crew, and the general public.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The largest commercial applications of the technology would be in the aircraft and automobile industries, where millions of dollars are spent yearly to get new vehicles to operate with a more comfortable noise level. The real-time acoustic data rendering capabilities that would be enabled with the development of the SVD/ESR-enhanced 3D audio binaural simulation software could be applied widely throughout the automobile design world by licensing it to be integrated with existing and broadly used industrial acoustics analysis packages. Such a combined package would offer significantly more display versatility to engineers designing to optimize acoustic performance than any other package available today.

Existing FEA packages with acoustics analysis modules do well at quantifying the noise levels and spectral characteristics of vehicle surfaces in the presence of an acoustic disturbance, but determining which frequency distributions plotted on a view graph will produce a negative visceral human response, versus which ones will sound pleasant or unobtrusive, is still an inexact science at best. Therefore, vehicle designers are required to produce multiple prototypes and test them acoustically before bringing a product to market. Our Phase II product will give these designers, and even their decision-making managers, the ability to hear prototypes in service before they ever leave the electronic drawing board, saving significant costs in the product prototype mockup stage.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835
(703 ) 787 - 8700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Chris Brinton
brinton@metronaviation.com
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835
(703 ) 234 - 0782

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Small Aircraft Transportation System (SATS) concept envisions a dramatic change in demand on National Airspace System (NAS) resources: a significantly increased number of flights operating as needed on Point-to-Point (PTP) routes with smaller aircraft. In addition to the increased demand on the NAS, the dynamic, ?on-demand?, nature of the SATS concept will present even greater challenges to the country?s Traffic Flow Management (TFM) system. The NAS regulates the flow of aircraft through TFM initiatives. However, the current TFM system does not perform well under uncertain demand patterns. The innovation proposed herein creates a website marketplace for providers and consumers of SATS services. More importantly, our innovation links the information from this SATS website to the Nation?s TFM system. Critical information regarding projected demand can be provided to the TFM system to allow the necessary management of the NAS. Advanced portions of this concept include interactivity between the SATS website and the TFM system to notify consumers of small aircraft transportation services regarding projected delays due to congestion along their requested route of flight at their requested flight time. In phase II of this effort, a human-in-the-loop simulation will be conducted using a prototype system to evaluate the concept.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The SATS-VMP concept provides critical modeling and analysis elements to support further research into the SATS concept. The SATS concept will have a dramatic effect on the National Airspace System (NAS). In order to continue to refine and enhance the SATS concept itself, the interconnection with the NAS must be evaluated. As NASA continues to refine and develop the modeling and analysis efforts associated with both the SATS concept, and air transportation in general, components of the simulation and analysis conducted in this effort can be enhanced and provided for further NASA application.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
A significant need exists for the SATS-VMP technology. The TFM system requires improved operational predictability, which the SATS-VMP concept provides. Metron Aviation is competing on an FAA procurement to modernize the TFM system to which the SATS-VMP concept can be applied. Commercially, a website can be created for purchasing charter travel services. The SATS-VMP website can provide public awareness of charter operations and interaction with the TFM system. The operators of the SATS-VMP website can use multiple revenue models, including transaction fees for bookings and advertising. Licensing the SATS-VMP concept to another website operator is also under consideration

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Rannoch Corporation
1800 Diagonal Road, Suite 430
Alexandria , VA   22314 - 2840
(703 ) 838 - 9780

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Rick Cassell
rcassell@rannoch.com
1800 Diagonal Road, Suite 430
Alexandria , VA   22314 - 2840
(703 ) 838 - 9780

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This research involves the adaptation of an aircraft based runway incursion advisory and alerting system for general aviation applications. PathProx is a runway incursion advisory and alerting system developed by Rannoch Corporation for air carrier operations. The work under Phase I of this SBIR included the definition of the developmental needs for adapting the PathProx conflict detection and alerting collision avoidance algorithms to General Aviation (GA) operations. Systems currently being deployed by the FAA are based on a ground infrastructure where runway incursion conflict alerts generated by the system are provided to ATC. Under this operational scenario the pilot is not provided with conflict alert information in the cockpit, leaving the aircraft dependent on the ground ATC infrastructure and human response. A General Aviation runway incursion advisory and alerting system will provide the following safety benefits:

?Reduction in the likelihood of near collisions resulting from runway incursions.
?Improved pilot response in taking evasive actions following incursions.
?Provision of runway incursion alerting at airports not equipped with surface surveillance systems
?Provision of runway incursion alerting at uncontrolled (non-towered) airports

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are two current NASA programs where GA runway incursion alerting has application ? Aviation Safety and the Small Aircraft Transportation System (SATS). The Aviation Safety program includes the Runway Incursion Prevention System (RIPS), which has been addressing runway incursion prevention for air carrier operations. This program also includes General Aviation operations, however there has no work done to date on the GA application. The PathProx GA implementation would fulfill that role.

GA runway incursion alerting would be an augmentation to the SATS program. Although the SATS operational concept does not include runway incursion alerting, it does include conflict detection and alerting in the terminal area ? under the High Volume Operations (HVO) part of the SATS program. PathProx runway incursion alerting would extend the alerting to include the airport surface.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ultimate product that would result from this research has potential application to general aviation, because runway incursions are a significant problem at all classes of airports. A runway incursion alerting system is currently not available to any class of aircraft. It is envisaged that the PathProx alerting algorithms would be a supplement to several other technologies that are currently under development. These other technologies are GPS, ADS-B, and CDTI. As the infrastructure for these technologies is established, it will be easy to integrate aircraft based PathProx into the avionics.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835
(703 ) 787 - 8700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Terry Thomspon
thomspon@metronaviation.com
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835
(703 ) 234 - 0789

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA, through several technology and concept development projects, is developing simulation/evaluation tools to assess the capacity and efficiency of alternative airspace/operational concepts. Missing from the current tool suite, however, is the ability to evaluate concepts from the perspective of environmental impact ? a key missing piece required to move a promising concept from simulation to implementation. To fill this gap, Metron Aviation develops a NAS-wide environmental impact modeling (NASEIM) service and fully integrates access to this service within the Advanced Concept Evaluation System (ACES), a fast-time simulator being developed as a national resource for evaluating NAS concepts. NASEIM not only spares researchers from the computational burden and data requirements associated with environmental modeling, but provides innovative tools for interpreting modeling results. The design of NASEIM allows fast-time noise computation ? consistent with the needs of the simulation it is supporting. In addition to noise modeling, NASEIM integrates air quality impact assessment in the form of emissions inventories, providing a more complete environmental impact picture. Using NASEIM, researchers can, early in the development cycle, identify concept elements that are significant contributors to specific impacts. Further, NASEIM allows comparison across multiple concepts. Phase II concludes with an integrated demonstration of NASEIM with ACES.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed NASEIM service is initially targeted for application to the Advanced Concept Evaluation System (ACES) simulation environment being developed under the Virtual Airspace Modeling and Simulation (VAMS) project. By generalizing the interfaces and services designed in Phase II and leveraging existing web-based protocols, we open up access to NASEIM to other simulation environments. Another particularly viable NASA application is the Future ATM Concepts Evaluation Tool (FACET). Other potential ?clients? include CTAS tools such as FAST and EDP ? where NASEIM could assess impacts of a given window of traffic or, alternatively, provide real-time support for the CTAS decision logic.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
In direct response to the globalization of air travel and increasing environment concerns, potential commercial applications of NASEIM include:
? State and local governmental bodies that need low-cost access to environmental modeling that across many airports and large regions;
? Transport providers that need the ability to see what impacts their evolving business strategies may have on the environment, and where their strategies may potentially conflict with environmental concerns;
? Aerospace firms and other contractors interested in airspace concepts that need a nationwide modeling capability to reduce the need for duplication of data, model elements, and analytical effort.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835
(703 ) 787 - 8700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dan Rosman
rosman@metronaviation.com
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835
(703 ) 234 - 0731

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron Aviation, Inc. builds the Pre-Operations Hypothesis Evaluation Tool (PROPHET), a tool for Traffic Flow Management (TFM) that integrates existing and emerging technologies in the areas of modeling and operations analysis to enable the evaluation of proposed TFM initiatives. The key innovation of this effort is the integration of the Post Operations Evaluation Tool (POET) and the Future ATM Concepts Evaluation Tool (FACET) to accomplish ew tasks that neither of these tools can do alone. This development leverages the following key features: FACET?s trajectory prediction and modeling capabilities, and POET?s mature database management system and operations analysis tools. By integrating the tools we provide a system allowing Traffic Flow Managers to investigate future TFM initiatives in real-time. These users then exploit the tool?s analysis capabilities to observe and compare the benefits and impacts of several proposed initiatives prior to operational implementation ? an assessment carried out based on explicit reasoning regarding uncertainty. In Phase I, we provided a proof-of-concept, demonstrating technical feasibility. In Phase II, we develop a plug-and-play module for FACET enabling interaction with POET?s databases and data mining capabilities and providing users access to PROPHET functionality. Phase II culminates in a demonstration of this plug-and-play functionality.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed PROPHET tool is initially targeted towards researchers at NASA Ames developing and enhancing the Future ATM Concepts Evaluation Tool (FACET). Additional NASA applications include real-time VAST-RT tools and the fast-time Advanced Concept Evaluation System (ACES) being developed under NASA?s Virtual Airspace Modeling and Simulation (VAMS) project. Real-time application would allow concept developers to ?test drive? different concept-specific strategies with Traffic Flow Managers ?in-the-loop?, and directly compare their performance against other baseline strategies used today. Integration of PROPHET?s functionality into ACES? various strategic TFM agents will allow fast-time evaluation of the potential for automating robust TFM decision-making under uncertainty.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential commercial applications of PROPHET include:
? Near Real-Time Decision-Support Tool (DST) for specialists at the ATCSCC
? Near Real-Time DST for Traffic Flow Managers at FAA field facilities including ARTCCs, TRACONs, and ATC Towers
? Supporting various industry working groups (such as CDM) in prototyping and evaluating novel TFM concepts
? Supporting airlines in filing flight plans and managing their operations network
? Supporting aviation industry/university researchers
? Applicability to TFM concerns of EuroControl and other international ATM organizations
Through these applications, PROPHET allows users to actively participate in developing robust TFM solutions consistent with local and system-wide concerns.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Seagull Technology, Inc.
1700 Dell Avenue
Campbell , CA   95008 - 6902
(408 ) 364 - 8200

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Mr. David B. Signor
dsignor@seagull.com
1700 Dell Avenue
Campbell , CA   95008 - 6902
(408 ) 364 - 8219

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is the use of advanced GUI and underlying functionality to reduce the time and effort required for real-time air traffic simulation scenario development. Our product directly addresses efficient generation of scenarios for real-time HITL simulations which analyze NAS operational performance and economic impact. Thus, we are responsive to: next generation simulation and modeling capability; NAS operational performance, economic impact; and real-time simulations: components with different levels of fidelity, human in-the-loop - in the A3.02 subtopic. The project objectives are to field a working prototype during Phase-II that demonstrates efficient scenario generation and incorporate feedback into a range of profitable commercial scenario generation products. The Phase-II effort includes; (1) refine application requirements; (2) refine application architecture;, (3) implement and evaluate the Phase-II prototype; and (4) prepare Phase-III business plans. We anticipate the Phase-II prototype to demonstrate significant efficiency gains regarding scenario generation - initially for the ATM domain and subsequently for other domains. Our application supports NASA human factors research regarding; current and future airspace systems, human performance, human-computer interfaces, distributed human decision-making, and design/evaluation of decision support tools. Benefits include: (1) increased scenario generation efficiency by reducing both time and resource requirements; (2) usable scenario output across multiple simulation facilities; (3) compatibility with distributed simulations; and (4) reduced need of expensive target simulation facilities for scenario development and evaluation. The period of benefit will begin during Phase-II and continue as long as there is a need for efficient scenario generation ? we expect tangible benefits for the next 10 years.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The initial NASA application will enable scenarios used in real-time HITL simulations to be generated and changed much more efficiently than they are today. The Phase-II prototype will be the first demonstration of the collection of innovative features and is intended to provide tangible near-term benefits to NASA real-time simulation efforts such as the VAMS project. Our application will support more complex and extensive research into a variety of human factors issues regarding current and future airspace systems including:, human performance, human-computer interfaces, distributed human decision-making, and design and evaluation of decision support tools. The proposed application would enable not only increased efficiency in generating the initial scenario but would allow the scenario to be changed while preserving the salient features of the desired experiment. With some modifications to the initial application it will support additional NASA applications including: (1) scenario generation for fast-time air traffic simulators such as NASA?s Airspace Concept Evaluation System (ACES); (2) the study of integration of new vehicle concepts such as SATS aircraft, reusable launch vehicles, and uninhabited aerial vehicles (UAVs) into the National Airspace System; and (3) the static and dynamic visualization of air traffic research results.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The FAA, commercial airlines and fleet operators perform airspace analysis regularly. An improved scenario generation application would support; technology investment decision making, new procedure design, new operational concept robustness analysis, operations analysis, airport and airspace design and capacity studies, noise and emissions analysis, fleet response planning, and training. The FAA may use our product in connection with real-time simulations to provide quick-turnaround, human factors analysis of future operational concepts. Within commercial air traffic market, there is a growing demand for airspace operation simulation research to support: a) communication, navigation, and surveillance, and weather sensing equipment loading and placement analysis; b) UAV and commercial space launch scheduling and design; c) planning and procedure development; d) mission training and rehearsal; e) mission debrief; f) pilot training; g) safety training; h) aviation security threat analysis; i) situation re-enactment and post-mortem analysis; and j) accident/incident investigation. Our application can be used by scientific researchers as a graphical display and analysis tool for illustrating: conflict detection and resolution study result;, airport design or redesign; en route planning; and re-planning or weather avoidance research results. Adacel is interested in our application regarding generation of scenarios for non-ATM applications.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Concepts ETI, Inc.
217 Billings Farm Road
White River Jct , VT   05001 - 9486
(802 ) 296 - 2321

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Karl D. Wygant
kdw@conceptsnrec.com
217 Billings Farm Road
White River Jct , VT   05001 - 9486
(802 ) 296 - 2321

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Phase I effort demonstrated the feasibility of measuring cavitating inducer dynamic transfer functions using an upgraded Concepts NREC pump test facility. As there are no analytical tools or experimental facilities in the world today that can quantify a cavitating inducer?s dynamic transfer function, developing this capability is crucial for the safety, reliability and competitiveness of the American Space Industry. An innovative experimental technique that uses mappings of inlet and exit flow and pressure fluctuations to quantify a cavitating inducer?s dynamic transfer function is proposed. A cavitating inducer can be a source of instability in a rocket vehicle. Due to cavitation dynamics, inlet flow perturbations maybe amplified by the inducer resulting in very large flow and pressure fluctuations in the fuel system. The resulting dynamic couplings can lead to vehicle instability (POGO) as well as generate intense dynamic loadings on the turbopump. The feasibility of implementing the proposed measurement technique on an upgraded Concepts NREC water flow test loop was demonstrated in the Phase I effort. Implementation of the test loop upgrades and demonstration of the transfer function measurement technique on a scaled inducer with a historical pedigree will occur in the proposed Phase II effort.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
As mission requirements lead to higher power density turbopumps with lower specific weights and higher suction specific speed requirements the potential for flow-induced dynamic instabilities, both at the turbopump level and at the system level, increase. Rocket vehicle dynamic models require an accurate dynamic characterization for the inducer. The proposed experimentally measured dynamic transfer functions will provide accurate and reliable pump dynamic attributes which are necessary to assess the probability of destructive flow instabilities, such as cavitation surge and rotating cavitation, and their effect on engine component reliability and life expectancy and integrated vehicle system instability.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High energy density turbomachines such as gas re-injection pumps and compressors and high-energy density industrial pumps are a source of instability. Accurate dynamic characterizations of these machines are required to ensure safe and reliable operation of the systems into which they are installed. In addition to understanding the dynamic attributes of these machines under cavitation or stalled conditions, the dynamic transfer function under normal operating conditions is also required. The methodology proposed to measure the dynamic transfer function of a cavitating inducer is transferable. The proposer is well positioned to commercialize the technology to both aerospace and industrial customers.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Southwest Nanotechnologies, Inc.
710 Asp Avenue, Suite 303
Norman , OK   73069 - 4324
(405 ) 217 - 8388

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Leandro Balzano
lbalzano@swnano.com
710 Asp Avenue, Suite 303
Norman , OK   73069 - 4324
(405 ) 217 - 8388

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall goal of SouthWest Nanotechnologies (SWeNT) is the development of superior technology for the large-scale manufacturing and marketing of nanotubes of unique quality for near-term specialty applications. The Phase I of this SBIR focused in demonstrating that SWeNT's process can be scaled-up to a continuous-mode operation. In the commercialization aspects, the company focused on developing strong partnerships with companies such as Dupont, ChevronPhillips, General Electric, Applied Nanotechnologies Inc., and Nomadics, who will use nanotubes for their end-products.

The low operating costs and scalability of the SWeNT's process, coupled with its versatility for producing nanotubes with tailored structure are attractive characteristics that may make this technology the preferred mode of nanotube production. The expertise developed at SWeNT may position the company in a leading role in the field of nanotube-based materials.

To consolidate the technology and boost the commercialization of SWeNT's products, phase 2 includes the expansion of the nanotube production capabilities and the development of applications to take advantage of the uniqueness of the SWeNT's process for tailoring nanotubes for each specific application. The targeted applications are directly relevant to NASA's stated goals and include structural and conducting composites, fuel cells, microelectronic parts, and field emission devices.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
A4.02 Space Structures, Materials, and Mfg
A8.01 Revolutionary Aerospace Vehicle Sys. Concepts
E2.01 Structures and Materials

SWeNT is working with ChevronPhillips Chemical and Lockheed Martin, to help advance this project by "market pull," rather than by "technology push." SWeNT's success in Phase 1 is reflected in the commitment of these two organizations in Phase 2.

Additionally, with the support of the University of Oklahoma, GBTech, and ConocoPhillips, the Company expects to deliver NASA-spec material at the end of this phase 2 project.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Company will focus on near-term specialty applications for carbon nanotubes. These include structural and conducting composites, fuel cells, microelectronic devices, and flat-panel displays. The aforementioned products will drive demand, resulting in demonstrable near-term revenue.

SWeNT is currently working with ~10 Fortune 500 companies on various application development programs. In July 2003, after only six months in operation, the Company began making commercial sales. This was partially a result of NASA's phase 1 funding to SWeNT, and provides validation that NASA dollars were spent wisely. At the start of Phase 1, the Company is pleased to announce that it received an investment and partnership from ConocoPhillips.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Foster-Miller, Inc.
350 Second Ave.
Waltham , MA   02451 - 1196
(781 ) 684 - 4000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Player
jplayer@foster-miller.com
350 Second Ave.
Waltham , MA   02451 - 1196
(781 ) 622 - 5502

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent designs for large aerospace structures especially cryotank structures for the second and third Generation Reusable Launch Vehicle (RLV) are driving the aerospace community to develop out-of-autoclave composite manufacturing processes to save an estimated $30 million in autoclave capital equipment costs. In the Phase I effort, this process was demonstrated to produce excellent quality laminates typical for most of the thin regions of cryotank structure. In this proposed Phase II effort, Foster-Miller will further refine its Ultrasonic Tape Lamination (UTL?) technology coupled with its novel out-of-autoclave processing approach, controlled state curing, and demonstrate that reinforced regions cryotank structure can be fabricated with this novel methodology. The proposed Phase II program will also advance the state of art for the UTL? equipment by developing key articulation control mechanisms for complex contour fabrication. Foster-Miller will fabricate and deliver the resulting advanced UTL? head to NASA at the conclusion of the Phase II program. Foster-Miller will also fabricate a cylindrical demonstrator using both the advanced UTL? equipment and the refined controlled state curing technique. Northrop Grumman and Alliant TechSystems (ATK) supported the Phase I program, and both have agreed to cost share in the proposed Phase II program. (P-030587)

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Foster-Miller?s UTL ? technology, coupled with its novel out-of-autoclave processing approach, controlled state curing can be utilized during the manufacture of many of NASA?s large aerospace structures. The most prominent are the cryogenic fuel tanks for the next generations of reusable launch vehicle. Although the cryotanks provide the largest immediate cost savings primarily due to the elimination of autoclave capital investment, the opportunity to save manufacturing costs with this novel out-of-autoclave processing approach exists for other large space vehicle structures such as RLV wing skins, payload bay and landing gear doors. Other launch vehicles such as Delta IV rocket and its composite payload fairings also provide an excellent cost saving opportunity for the UTL?/controlled state bag-less technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Foster-Miller?s UTL?/controlled state bag-less cure has the potential to dramatically change the cost structure for fabricating a wide range of commercial aircraft composite components. Many of the large nacelle and flight control structures on Boeing and Airbus aircraft require multiple autoclave cycles for their manufacture, incurring substantial costs in cycle time and associated labor. Foster-Miller?s UTL?/controlled state bag-less cure would eliminate the need for the autoclave and perhaps more importantly, would eliminate the labor costs associated with vacuum bagging, usually performed several times during a component?s fabrication. UTL?/controlled state bag-less curing can also be applied to the manufacture of a wide range of other large composite structures that need high quality at low cost such as thick tubulars for offshore oil drilling, military fighter structures (JSF, F-18E/F, and V22) and military space plane structures (Air Force SOV cryotanks).

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Plasma Processes, Inc.
4914 Moores Mill Road
Huntsville , AL   35811 - 1558
(256 ) 851 - 7653

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Hickman
robert@plasmapros.com
4914 Moores Mill Road
Huntsville , AL   35811 - 1558
(256 ) 851 - 7653

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Non-conventional technologies are needed to revolutionize space propulsion. Development of materials with improved properties is essential to increase performance and reduce cost. Advancements are needed for components in solid and hybrid rocket, high powered electrical, beamed energy, and nuclear propulsion systems. Innovative processes for fabricating net shape, tungsten-rhenium-hafnium carbide alloy components are proposed. Tungsten is being used for its high melting temperature (6170?F) and chemical stability. However, conventional tungsten materials have to be forged to get adequate properties. Forging tungsten into complex shapes is difficult and has limited its application. Small additions of rhenium improve the ductility of tungsten without significantly decreasing the melting point. Also, dispersion hardening by additions of HfC increases the high temperature strength and creep resistance by pinning grain boundaries. In Phase I, W-Re-HfC materials and processing parameters were developed, and W-Re-HfC samples were fabricated for characterization and hoop tensile testing. In hoop tensile tests, Phase I W-Re-HfC was stronger than baseline W-Re or W. Solid rocket nozzle inserts were fabricated and are being hot fire tested at ATK-Thiokol to demonstrate non-eroding nozzles. Development of these materials will allow the production of components with unique properties and reduce the size, weight, and cost of propulsion systems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The results of the Phase I effort clearly demonstrate the ability to fabricate improved tungsten alloy components. Development of these advanced materials will produce robust components with unique properties and reduce the size, weight, and cost. Potential clients for these components are NASA, DOD, ATK-Thiokol, and Aerojet. PPI will develop and transfer the SBIR technology to other applications such as: rocket nozzles, Ballistic and tactical missiles, gun barrel liners, Arc-jet thrusters, Heat exchangers, welding electrodes, plasma facing components for nuclear reactors, gas turbines, automobile engines, incinerators, thermal control coatings, oxidation protective coatings, coatings for composite parts and structures, thermal barrier coatings, structural jackets on tubular combustors and nozzles, crucibles, tubes, valves, and storage vessels.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Commerical applications are solid and hybrid rocket nozzles, high powered electrical contacts, crucibles, heat pipes, fuel cells, components for solar thermal propulsion, valves, liquid rocket motors, nuclear power containment, furnace parts, armor penetrators, heat shields, electronics, incinerators, protective coatings and other high temperature applications.
Over $300,000.00 of commercial investment has been obtained for Phase III development.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Ultramet
12173 Montague Street
Pacoima , CA   91331 - 2210
(818 ) 899 - 0236

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jason R. Babcock, Ph.D.
jason.babcock@ultramet.com
12173 Montague Street
Pacoima , CA   91331 - 2210
(818 ) 899 - 0236

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Application of fiber-reinforced ceramic matrix composites (CMC) can enhance the efficiency and performance, reduce the weight, improve the durability, and lower the cost of rocket engine combustion devices and turbomachinery components used in high temperature, high-stress environments. Meeting these objectives requires improvements in fiber-reinforced CMC materials and fabrication processes, particularly improved fiber/matrix interfaces, interface deposition processes, and oxidation protection. In previous work, Ultramet developed an ultraviolet-enhanced chemical vapor deposition (UVCVD) process that allows deposition of dense, strain-tolerant ceramics at room temperature, thus avoiding heat-induced material degradation and providing excellent material performance, including enhanced oxidation protection. Although these coatings have improved performance, identifying a single phase that best performs the two key functions of the interface coating, oxidation protection and interface slip, has proven elusive. Phase I focused on development of both conventional CVD and UVCVD deposition techniques that resulted in several novel multilayer interface coating systems utilizing oxide and carbide phases. Fiber tows coated with multilayer systems exhibited dramatic improvement in tensile strength compared to both uncoated tows and fiber coated with a single oxide layer. One multilayer system was employed in the fabrication of a carbon fiber-reinforced silicon carbide (C/SiC) CMC that demonstrated the highest mechanical strength yet achieved for C/SiC using Ultramet's melt infiltration densification process, verifying the beneficial effect of the multilayer system via a 33% strength increase. The Phase II project will build on this encouraging preliminary room temperature data via further optimization of multilayer interface deposition at Ultramet and extensive evaluation of both coated tows and CMCs utilizing the coatings at the elevated temperatures expected in actual use.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Ceramic matrix composite materials are projected to significantly increase safety and reduce costs simultaneously, while decreasing weight for space transportation propulsion. Innovative material and process technology advancements are required to enable long life, reliable, and environmentally durable materials. Specific areas of technology development that are of interest include low-cost, rapid, scalable, repeatable CMC fabrication process development for multiple space transportation propulsion applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The composite materials to be developed in this project using innovative interfaces and novel UVCVD processing will have broad commercial applicability to a range of products, including fuel-rich turbomachinery components, aircraft engine components, recuperators, ducts, and other hot gas path components, process industry components requiring high temperature capability and corrosive environment resistance (e.g. hot gas and liquid handling equipment), furnace structures, and high temperature filter elements.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Starfire Systems, Inc.
10 Hermes Road
Malta , NY   12020 - 1903
(518 ) 899 - 9336

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Lynn Tarnowski
tarnowskil@starfiresystems.com
10 Hermes Road
Malta , NY   12020 - 1903
(518 ) 899 - 9336

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The need for low density, high temperature materials in space has driven evaluation and implementation of carbon-carbon, ceramics and ceramic matrix composites (CMC) for structural applications. The thermal, mechanical, and chemical properties of ceramic matrix composites make them attractive both for next generation and retrofit applications. CMC?s require a fiber matrix interface coating to impart toughness, but the high cost of current interface coatings ? from 30 to 70% of the cost of a CMC part - has severely limited overall adoption of CMC?s. Low cost oxidation resistant coatings are the third leg of the CMC material triad (fiber-interface-matrix) needed to realize full commercial potential. Starfire polymer based coatings can reduce interface coating costs by 95%.
In Phase I, these coatings exhibited desirable interface properties (thin, uniform, debonding). The phase II effort will optimize these interface coatings such that they will protect the fiber from oxidation and support an oxygen sealing feature against both matrix micro-cracking and impact damage. The interface coatings will be validated for hypersonic, rocket, and turbine engine applications.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Key NASA applications are expected to include virtually all CMC applications such as thermal protection systems, turbo-pumps, cryotanks, nozzles, thrusters, and even space structures that would take advantage of the light weight and low thermal expansion properties of CMC?s. Specific programs may include: Integrated High Performance Turbine Technology (combustors, turbine rotors, exhaust nozzles); Integrated High Payoff Rocket Propulsion Technology (turbomachinery, nozzles, thrust chambers); Reusable and Expendable Launch Vehicles (thermal protection, thrust chambers, nozzles, brakes); In-Space Propulsion (maneuvering thrusters).

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Low cost, oxidation resistant fiber interface coatings will enable ceramic composites to be utilized in a wide range of applications where they are currently considered too costly. Specific applications that have been identified as potential markets include: brakes for commercial and military aircraft; brakes for automobiles, trucks, heavy equipment and trains; hot gas filters for pressurized fluidized bed combustion and integrated gasification combined cycle systems; furnace hardware such as pipe hangers for petroleum refining; reverberatory screens in porous radiant surface burners used for drying, curing and process heating, components for melting and handling metals; non-rotating components in ground-based gas turbines, especially combustion liners and shrouds; heat exchangers for externally-fired combine cycle (EFCC) power systems, thermophotovoltaic power systems for household appliances and quiet generators, reforming tubes for the chemical processing industry; and exhaust manifolds and high temperature engine components for diesel and gasoline powered auto engines.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Applied Thin Films, Inc.
1801 Maple Ave., Suite 5316
Evanston , IL   60201 - 3135
(847 ) 467 - 5235

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Kimberly Steiner
ksteiner@atfinet.com
1801 Maple Ave., Suite 5316
Evanston , IL   60201 - 3135
(847 ) 491 - 3373

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Space transportation and other vehicles entering the earth?s atmosphere at hypersonic speeds undergo aerodynamic heating which necessitates thermal protection systems (TPS) on exterior surfaces. Future reusable launch vehicles (RLVs) will require TPS durable over several missions with rapid turnaround between each flight. Advanced metallic TPS are under development that utilize a honeycomb structure with thin face sheets (typically 7-10 mils) that are coated to provide high emissivity, oxidation protection, and low catalytic efficiency. Currently-available TPS coatings are not adequate and do not have the durability required for use with RLVs. Thus, a new coating system with suitable and environmentally-friendly formulations are required that meet the basic property requirements and also have the ability to withstand the harsh acoustic and aerodynamic thermal environments during reentry over several missions. Phase I results demonstrated technical feasibility of an innovative approach utilizing a nanocomposite material (Cerablak) that contain carbon as nanosized inclusions to provide emissivity. The coatings are deposited using low-cost, simple, easy-to-apply, and stable formulations. High emissivity properties after heat treatment and excellent protection against oxidation protection were demonstrated. Phase II effort will include further optimization of precursor formulations and coating properties with the primary objective to meet the durability requirements.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Direct use of the proposed technology will be with metallic TPS which are being developed by several companies for both NASA and DoD. ATFI intends to commercialize the technology through strategic partnerships with these companies. Black pigmented high emissivity paints are currently used on various parts of NASA?s space shuttle fleet. The proposed coating product offers many advantages including low-cost, durable high emissivity, ease of applicability, relatively thin, and oxidation protection. The proposed formulations contain no VOCs, have extended shelf stability (years), and require short curing times. The coating can be applied using brush/spray/flow/dip coating methods. With these attributes and relative low-cost, the proposed technology has excellent potential for insertion. Excellent oxidation protection has been demonstrated with thin hermetic glassy films (200-500nm) with excellent adhesion properties on alloys that will be useful for turbomachinery components, seals, and other components exposed to high temperatures during service.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
High emissivity coatings are being widely used to limit heat transfer in furnaces, boilers, ducts, and other components and to improve thermal efficiency and performance of IR radiant burners used in the energy industry. The proposed product will help improve performance and will be durable that will result in lower maintenance costs and downtimes for production. In addition, oxidation protection will also be beneficial in both protecting the components as well as to prevent cracking and spallation of the high emissivity coating. Due to the large volumes of formulations used, environmental concerns are more relevant for these commercial applications. Hence the zero VOC and environmentally-friendly formulation offered by the proposed technology will serve as a distinct advantage over currently-used products. The ease and flexibility of application of the coating and short curing times will be especially beneficial as minimal training or skills will be required to perform the function.

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Jennifer Scherr
jennifer@zonatech.com
7430 E. Stetson Drive, Suite 205
Scottsdale , AZ   85251 - 3540
(480 ) 945 - 9988

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Among the critical components of the next generation launch technology (NGLT) is the design of panels and ?integrated panel systems? (panel + support + thermal protection system). Such an effort can be built upon ELSTEP/FAT, an existing ZONA software providing accurate predictions of the response and fatigue life of panels subjected to severe acoustic loads and thermal effects. The work carried out successfully during the Phase I led to the formulation and proof-of-concept validation of an estimation strategy of the sensitivities of a panel to changes in its geometric and/or material properties. Accordingly, the first focus of the proposed Phase II effort will be on the generalization of the approach to account for changes in all aspects of the 2 or 3-dimensional panel geometry and on the various material properties involved (Young?s modulus, ply angles and thickness, ...). Panels are not independent structures but are part of more complex systems, e.g. panel + support + TPS, and an accurate estimate of the response/life of the panels must include the interaction with these other components. Accordingly, the predictive and sensitivity capabilities of ELSTEP/FAT must be extended and validated for such integrated systems. Computational aspects will also be re-visited to maintain the efficiency of ELSTEP/FAT.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed design-oriented software (ELSTEP/FAT) will become the only available tool for the prediction of the response, fatigue life, and their design sensitivities of panels subjected to thermo-acoustic loads. Additionally, it will include the capability to model the integrated panel system (panel + support thermal protection system) and thus will help in the transition from component design to system design. With its strong focus on fatigue, ELSTEP/FAT will cover two separate markets (panels and fatigue) thereby increasing its distribution potential. ZONA can market ELSTEP/FAT through agreement with MSC Software (seamlessly integrated) or as a standalone package loosely integrated with several nonlinear finite element packages. It can be adopted by structural engineers for a wide class of aerospace vehicles ranging from JSF, UAV/UCAV, supersonic transports, reusable launch vehicles, RLV/TAV and other new hypersonic aerospace vehicles. It will be an ideal design tool for the current NASA projects under its space initiative and, with its sensitivity analysis, will also naturally support the NASA multidisciplinary optimization efforts. Other than NASA, potential customers include R&D and design arms of DoD Government and private industry such as ZONA?s ZAERO software users in the structures community. With ZONA?s user/customer network, the marketing of ELSTEP/FAT is relatively straightforward with or without MSC Software.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The ELSTEP/FAT software will occupy a unique niche as there is currently no software to predict the response/fatigue life of panels subjected to thermo-acoustic loads nor to evaluate the response/life design sensitivities. It will play an important role in the design of many flight vehicles including supersonic transports, reusable launch vehicles, RLV/TAV and other projects of NASA?s space initiative that experience severe thermal, acoustic, or both types of excitations. The inclusion of the TPS modeling and of its interaction with the panel will provide a common platform for the development of these components and will help to transition from component design to system design. Further, the reduced-order modeling of ELSTEP/FAT will lead to expedient sensitivity computations. Thus, ELSTEP/FAT will also naturally support NASA?s multidisciplinary optimization efforts.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Tethers Unlimited
19011 36th Ave W. Suite F
Lynnwood , WA   98036 - 5752
(425 ) 744 - 0400

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Hoyt
hoyt@tethers.com
19011 36th Ave W. Suite F
Lynnwood , WA   98036 - 5752
(425 ) 744 - 0400

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The MXER Tether Boost Facility will serve as a fully-reusable in-space ?upper-stage? that will provide propellantless propulsion for orbital transfer and Earth-to-Orbit launch assist. By elimi-nating the need to launch an upper stage along with each payload, the MXER Tether can reduce the size of the launch vehicle needed to deploy the payloads, achieving dramatic reductions in total launch costs. In the Phase I effort, we successfully developed an architecture that will en-able MXER tethers to be constructed using small modular components that can be designed, tested, and mass-produced at low cost. We demonstrated methods for fabricating high-strength tether structures, for protecting the high-strength materials in the tethers from the atomic oxygen environment, and for providing the high voltages and high powers needed to enable the MXER system to restore its orbit using propellantless electro-dynamic propulsion. In the Phase II effort, we will develop tools for performing design trade studies of MXER Tether Systems. We will then use these tools to design a flight demonstration mission that will bring the components needed to build an operational MXER tether up to a TRL of 8. We will develop and test new methods and algorithms for controlling the dynamics of MXER tethers. Finally, we will design, build, and test a prototype tether deployer module suitable for use in both the flight demonstration and the opera-tional MXER tether.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The MXER Tether Boost Facility will particularly benefit NASA?s deep space missions, such as the Europa Lander, Titan Explorer, and Neptune Orbiter, by enabling them to use a much smaller launch vehicle, saving over $30M per mission. The MXER Tether can also achieve fivefold launch cost savings for NASA scientific missions to GEO, the Moon, and Mars. The high-power tether technologies developed in this SBIR can also provide propellantless propulsion for orbital transfer, asset repositioning, and deorbit of LEO spacecraft. Potential for Phase III success is demonstrated by the fact that during the Phase I SBIR effort, TUI was selected for award of two contracts from NASA?s In-Space Propulsion Program for development of tether technologies and simulation tools for MXER Tether systems, with total non-SBIR funding of up to $2.1M over the course of the proposed Phase II project.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The MXER Tether Boost Facility can also provide significant launch cost savings for DoD and commercial space organizations. It can combine with DARPA?s RASCAL launch system to pro-vide a rapid, low-cost means of delivering 200 kg microsatellites to GEO for space control and spacecraft servicing applications. The high-voltage power systems and space-survivable tether technologies developed by this SBIR also have applicability to an innovative new concept for remediation of natural and HAND-induced radiation belts. During the Phase I, TUI received $205K in DARPA funding for development of high-voltage and electrodynamic tether technologies that are directly relevant to the MXER Tether System. TUI has also been selected for award of a $350K DARPA seedling effort for the development of innovative technologies for capturing space objects. The high-strength tether technologies also have strong potential for solving some of the critical problems facing the oceanographic community in the area of deep-sea research cables.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
SRS Technologies
1800 Quail Street, Suite 101
Newport Beach , CA   92660 - 0000
(256 ) 971 - 7000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Nobie H. Stone
nstone@stg.srs.com
500 Discovery Drive
Huntsville , AL   35806 - 9999
(256 ) 971 - 7029

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Grid-Sphere is a passive electrode contactor that relies on a very large area to allow the collection of large currents from the ionosphere. Dynamic drag is minimized by using a grid construction. This Grid-Sphere can provide electrodynamic tethers with the ability to passively collect arbitrarily large currents at the positive pole?requiring only low bias voltages. This makes current collection independent of tether length and eliminates hazardous high-voltage operations. The Phase-1 results include the development of grid-film materials with the required characteristics and the derivation of a linearized model of the current collection process?and clearly show the Grid-Sphere to be feasible and to collect current with virtually the same efficiency as a solid-surface spherical electrode of the same radius.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Grid-Sphere electrode will be an attractive addition to space tether technology because it will allow the collection of arbitrarily large currents with arbitrarily short tether systems while maintaining very low dynamic drag. These characteristics will be enabling to applications such as the Tether Reboost System that has been proposed as a alternative means of reboosting and maintaining the orbit of the International Space Station?where the micro-gravity environment must be maintained, thereby prohibiting long tethers. It will also be a valuable asset for the MXER Tether Launch System concept being proposed as a low-cost alternative to second-stage boosters for missions requiring launch into deep space. In this case, high-power electrodynamic reboost of the MXER system will be essential to achieve efficiencies competitive with alternative launch technologies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The Grid-Sphere Electrode relies on deploying a very large-scale spherical body of 10 to 20 meters or more in radius. Dynamic drag is minimizing by using a grid construction so that orbital lifetime may be very long?even in LEO. The Grid-Sphere can, therefore, be used as a very large RF antenna that could remain in LEO for long periods of time. Grids can be upwards of 90-percent transparent, in order to minimize drag, and still allow grid spacings ranging from sub-millimeter to several centimeters to be used. Grid spacing can, therefore, be selected to match the frequency range of the RF band used. Placing such an antenna in LEO would minimize the distance to mobile ground-based transmitters, thereby reducing transmitter power requirements and improving receiver sensitivity.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Invocon Inc.
19221 IH 45 South - Suite 530
Conroe , TX   77385 - 8703
(281 ) 292 - 9903

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Eric Krug
ekrug@invocon.com
19221 I-45 South, Suite 530
Conroe , TX   77385 - 8746
(281 ) 292 - 9903

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The feasibility of extremely low-power wireless RF sensors has been demonstrated by Invocon, Inc. and others, but the application of the technology to broader applications, particularly ground test systems, has been limited. Ground test facilities must be capable of providing reliable, laboratory grade instrumentation capabilities as part of a reconfigurable architecture in sometimes extreme environments, while simultaneously considering purchase costs, maintenance and operations costs, and upgrade costs. The proposed system shall enable the use of existing Ethernet hardware and Web-based IT resources for the configuration, acquisition, transmission and display of sensor data from extremely low-power RF sensors. Standard facility and experiment monitoring functions such as set points, alarms, data logging, and status displays will be provided, as well as the capability to integrate wireless sensor data into existing third party data acquisition and analysis tools available at the NASA ground test facilities. Configuration of individual sensors will be via a Web browser, and sensor output will be available anywhere with Internet access. By providing widespread access to miniature RF sensors, this system will enable the creation of a highly flexible, scalable, robust, wireless instrumentation backbone, which can be integrated with the existing resources of NASA rocket engine ground test facilities.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
This system could benefit many NASA ground test facilities, including wind tunnels, environmental chambers, and biological chambers. Monitoring of launchpads and other Orbiter processing facility resources could be enhanced and further automated with the proposed system, eliminating labor-intensive data logging activities currently employed. The International Space Station, which is already outfitted with wired and wireless LAN, could potentially benefit from this development through the utilization of environmental and vehicle sensors, crew health monitoring sensors, and payload monitoring and control. Finally, significant benefits to the 2nd Generation RLV Integrated Vehicle Health Monitoring system or payload systems could be realized.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Potential Non-NASA applications include industrial facility monitoring, building monitoring and automation, and industrial process control systems. Recent efforts to capitalize on the low cost and trained workforce associated with Ethernet-based networks for factory monitoring and automation have been successful, and would benefit from the ability to utilize low-power RF sensors within that framework. The successful development of a standard Ethernet-based access point with the associated network software could be the enabling technology that leads to the widespread application of RF sensors within the industrial market.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NVE Corporation
11409 Valley View Road
Eden Prairie , MN   55344 - 3617
(952 ) 996 - 1602

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Russ Beech
beech@nve.com
11409 Valley View Road
Eden Prairie , MN   55344 - 3617
(952 ) 996 - 1613

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed development will integrate data acquisition electronics with a relatively high performance processing capability and a large amount of memory, all in a miniature package, yielding a miniature, intelligent, sensor electronics module. This combination allows embedding of intelligent functions on sensors, providing the capability to implement data pre-processing and health monitoring of the system. The data acquisition electronics will provide programmable, analog I/O and digital I/O, including programmable gain, filtering, and voltage or current source, and auto-calibration. With the included processing power and memory, this system could operate autonomously, reporting to a higher level system only when queried or when specific conditions occur. With an included Ethernet interface, the system can use a standard network to communicate with a higher level system or other intelligent sensor modules. This system will simplify the task of data acquisition from remote locations or within a large, distributed data acquisition system. Implementation of health monitoring within the intelligent sensor module increases confidence or trust in the data that comes from the module. Maintenance is also simplified when the sensor node is able to report on its own health status, indicating when there is a fault or other need for maintenance.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The intelligent sensor module is being developed for use in ground testing of rocket engines, including monitoring of related support systems. The programmable sensor interface will allow the system to be used with a wide variety of different sensors. The Ethernet network interface and health monitoring capability allow the system to be conveniently deployed in remote and/or hard-to-reach locations. Because of the systems versatile interface and programmable processing capability, the system could be applied to other test and monitoring applications.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Other potential commercial applications for the intelligent sensor module include automotive and industrial testing and monitoring, which are similar to the target NASA application. Again, the flexible sensor interface, standard network interface, and processing capability, including the ability to monitor system health, allow the module to be applied in a broad range of situations. With the ability to include complex data processing at the sensor level, the module could be used to distribute the processing load in an industrial process control system. Similarly, the module would prove useful in automation and control applications that are not well served by traditional Programmable Logic Controllers, due to inadequate processing power or sensor input flexibility.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Combustion Research and Flow Technology,
6210 Keller's Church Road
Pipersville , PA   18947 - 1020
(215 ) 766 - 1520

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Vineet Ahuja
vineet@craft-tech.com
6210 Keller
Pipersville , PA   18947 - 1020
(215 ) 766 - 1520

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The development of simulation technology is proposed for carrying out high-fidelity transient analyses of systems that support experimental rocket testing such as control valves, feed system elements, pressure regulators and other flow control elements. The simulation technology comprises of a generalized multi-element unstructured framework (CRUNCH CFD) with integrated sub-models for grid adaption, grid movement and multi-phase flow dynamics including cryogenic cavitation. As part of our Phase I effort, simulations were performed for a series of systems that included the 10-inch LOX service valve, split-body valve, pressure regulator valve and the cavitating LOX venturi valve, all at constant valve settings. Results indicated excellent agreement with experimental flow coefficient curves. In Phase II, we will extend the framework to provide coupled valve motion - flow transient analyses with the development of an automated grid movement procedure to track valve motion. Valve timing analysis for a number of high pressure valve systems will be performed and the resultant dynamic events such as cavitation and valve chatter that lead to pressure fluctuations will be simulated. The framework will be used as an analysis support tool to generate performance metrics, evaluate design modifications and identify dominant frequencies associated with hydrodynamic instabilities and valve motion.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The software product resulting from our Phase II effort directly addresses core needs of the propulsion testing and design community at NASA as outlined in the Next Generation Launch Technology Program (NGLT). One of the requirements of the NGLT program is to operate the system over a wide range of off-design conditions where dynamic effects and cavitation become important. The simulation technology proposed here will be directly applicable to performance evaluation and transient analyses of components of the main propulsion system such as propulsion-related ducts, valves, lines and actuators delivering fuel from main propulsion tanks to the main engine. Analyses of hydrodynamic instabilities related to cryogenic tanks can also be carried out with the proposed technology.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The testing and design of launch systems places increased reliance on high pressure valve systems. Our simulation software could be used as an analysis support tool in enhancing on-site capabilities at test stand facilities. Besides the launch systems industry, the developed software product can be used in development of valves for cavitation control, design of cryogenic control valves, and fluid-transient simulations for feedback in control loops. Such applications would encompass a broader commercial market including (a)distribution networks associated with water, waste (b) valve industry (in petrochemical, refining, chemical processing and food processing). The proposed Phase II effort can also directly address problems in the area of biomedical devices such as the functioning of prosthetic heart valves that are sensitive to valve timing and susceptible to cavitation.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nanoptek
250 Old Marlboro Rd.
Concord , MA   01742 - 4128
(978 ) 371 - 7339

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Guerra
jguerra@nanoptek.com
250 Old Marlboro Rd.
Concord , MA   01742 - 4128
(978 ) 371 - 7339

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Phase II will continue developing the efficient production of hydrogen from water using sunlight and nanostructured titania thin-film semiconductor electrodes achieved in Phase I, delivering a solar hydrogen generator. Titania?s (TiO2) absorption cutoff is moved from UV (414 nm) to visible (529 nm) by shifting the energy bandgap to ~2.0 eV , through stress induced by the nanostructured template. The disorder/strain distribution forms amorphous/strained titania with a high density of states localized within the energy band gap. Absorption of 29% of the solar spectrum is achieved, more than 5X improvement over single-crystal TiO2. The nanostructures enhance total absorption through multiple total internal reflections, eliminating the need to track the sun. A prototype three-electrode electrochemical cell evolves hydrogen at 2 mL/(s?W?m2) ? a solar-efficiency of 8% after light source correction; electrochemistry data shows 20% efficiency is attainable. Efficient conversion of water to hydrogen fuel with sunlight is ideal for closed environments like the International Space Station, with continuous recycling of hydrogen from contaminated water back to clean water when combined with a fuel-cell electrical generator. With possible water on the moon, Mars, and other bodies in the solar system, this technology will greatly reduce the mass of space ships for future missions.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Phase III production of bandgap-shifted titania photoelectrolysis would provide NASA with the hardware to efficiently use solar energy to convert water to hydrogen fuel. This technology is ideal for closed environments like the International Space Station, with continuous recycling of hydrogen, using photo-electrolysis, from contaminated water back to clean water while also producing electrical power in a fuel cell. If water is confirmed on the moon, Mars, and other bodies in the solar system, efficient conversion of water to hydrogen fuel using sunlight will greatly reduce the mass of space ships for future missions to and from these bodies.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Phase III commercial product applications include supplying clean hydrogen fuel for small-scale power generation for hospitals and businesses or home refueling of fuel cell automobiles, as well as large-scale hydrogen supply for local utilities and ?super? fueling stations located along major interstates. With this point-of-use technology, problems with hydrogen transport, leakage, and storage are reduced or eliminated. Hydrogen flow rates and efficiencies determined in Phase 1 project a payback in 2 years for residential and commercial installations, and a reduction of the price of hydrogen by a factor of 4 assuming a realizable projected photo-electrolytic cell lifetime of 8 years.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Microwave Power Technology
1280 Theresa Avenue
Campbell , CA   95008 - 6833
(408 ) 379 - 5335

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Espinosa
micpwrt@aol.com
1280 Theresa Avenue
Campbell , CA   95008 - 6833
(408 ) 379 - 5335

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The primary goal of Phase II is to produce an X-ray tube with a small focal spot suitable for an X-ray Diffraction instrument that can be used for in situ analysis of materials in industrial and planetary exploration environments. A base model, based on a previously developed miniature, carbon nanotube X-ray tube, was designed and fabricated during Phase I. Four tubes will be delivered at intervals during Phase II. Each tube will incorporate improvements converging on the objective specifications, 40 kV operating voltage, 100 microamps of current and a focal spot of 40 microns. Design improvements will be achieved with electron optics simulation computer code that was modified to model emission from CNT cathodes and the electron beam analyzer that was design and constructed during Phase I. Improvement in the emission stability and uniformity will be sought using the cathode test and evaluation station that was constructed and operated during Phase I. The cathode evaluation system has already been used to select cathodes and develop CNT cathode processing regimens that resulted in improving the acceptance rate, from 50% to 90%,of CNT cathode X-ray tubes being produced at Oxford X-ray Technologies for hand held XRF Spectrometers.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
Cold cathode x-ray tube provide the source for very small x-ray fluorescence and diffraction instruments that are suitable for hand held and portable applications on earth as well as space. These tubes are well suited to withstand the rigors of space travel and mounting on small rovers. The improvements in CNT cathode technology and electron optics design tools that we are developing to meet the space based requirements, are key to utilizing CNT emitters in vacuum electron devices for microwave amplifiers and electron beam sources for air purification, environmental remediation, sterilization, and space base manufacturing.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Development of the focused beam x-ray tube will immediately extend the utilization of CNT cathodes to x-ray diffraction instruments and imaging that require small focal spots and higher intensity. Improvements in emission stability and uniformity resulting from this project will be exploited for electron beam generators for use in drying inks on high speed presses, for non-burning destruction of toxic and odoriferous hydrocarbons in the environment, for sterilization of surfaces and powdered materials in industry and pharmaceuticals and for brachytherapy in medicine. Integrated arrays of microwave amplifiers based on cold cathode vacuum electronics technology are currently being investigated.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Atlas Scientific
1367 Camino Robles Way
San Jose , CA   95120 - 4925
(408 ) 507 - 0906

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Ali Kashani
akashani@atlasscientific.com
1367 Camino Robles Way
San Jose , CA   95120 - 4925
(408 ) 507 - 0906

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future NASA programs will utilize solid-state devices (e.g., detectors, processors) that require cooling. Thermal management is of critical importance for a variety of solid-state devices. As the size of solid-state devices continues to shrink, device performance and reliability is limited by the ability to remove the increasing density of heat generated within these components. Furthermore, other devices such as solid-state lasers and infrared cameras require cooling and active temperature control. We propose two complimentary approaches to address these issues. The first approach is to develop thermoelectric (TE) coolers using nanotechnology. Thermoelectric materials require high electrical conductivity, but low thermal conductivity. Using nanotchnology it should be possible to significantly suppress the thermal conductivity without a corresponding reduction in electron transport. The second approach we propose is to enhance the thermal contact conductance at interfaces by taking advantage of nanotechnology.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
There are several NASA applications for both proposed approaches to thermal management in solid-state devices. The thermoelectric devices could be used for refrigeration and cooling from cryogenic to room temperature for a variety of devices such as microprocessors or detectors. The same thermoelectric materials could also be used for power generation in the presence of an external heat source. A variety of heat sources could be utilized including waste heat from engine exhaust or heat from a radioactive isotope. The technique for enhancing thermal conductance at interfaces could be used for the thermal management of space-borne microelectronic and nanoelectronic packages and systems. The concept could be integrated with current device technology and packaging and it would allow for an efficient method to manage excess heat generation without requiring any additional power.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
There are several potential commercial applications for both proposed approaches to thermal management in solid-state devices. The thermoelectric devices could be used for refrigeration and cooling from cryogenic to room temperature for a variety of devices such as high-performance electronics and IR/visible CCD/CMOS imaging cameras. The same thermoelectric materials could also be used for power generation in the presence of an external heat source. A variety of heat sources could be utilized including waste heat from engine exhaust or heat from a radioactive isotope. The technique for enhancing thermal conductance at interfaces could be used for the thermal management of microelectronic and nanoelectronic packages and systems. The concept could be integrated with current device technology and packaging and it would allow for an efficient method to manage excess heat generation without requiring any additional power.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Nielsen Engineering & Research, Inc.
605 Ellis St. Suite 200
Mountain View , CA   94043 - 2241
(650 ) 968 - 9457

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Robert Childs
childs@nearinc.com
605 Ellis Street
Mountain View , CA   94043 - 2241
(650 ) 968 - 9457

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Computational fluid dynamics (CFD) is the primary tool of aerodynamic design, and the ability to reduce and quantify uncertainties in CFD results is essential. Efforts throughout the CFD community are aimed at improving the accuracy of CFD methods. The proposed work will develop computational algorithms and software that yield comprehensive estimates of uncertainty in CFD results. The methods involve error modeling, in which specific sources of error, such as truncation error, and error in the transition and turbulence modeling, are related to the errors and uncertainty in the solution via solutions of an error equation. These methods will be relatively comprehensive, accounting for the dominant sources of uncertainty in typical CFD analyses, and yielding the uncertainties in all data predicted by the CFD solution. For example, the uncertainty in distributed aerodynamic heating can be computed. The techniques to be used in the work have been demonstrated in predictions of uncertainty due to truncation error in structured-grid CFD data. The proposed work will extend these methods to unstructured-grid CFD and to transition and turbulence modeling errors.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The proposed technology will have benefit wherever CFD is used to assess aerodynamic performance in critical applications. This includes the design and analysis of all commercial, NASA, and military aerospace vehicles. The technology developed will be represented as a set of software modules that can be used with existing and new CFD solvers.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The benefits to non-NASA applications is similar to NASA applications.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
JMSI, Inc. dba Intelligent Light
1290 Wall Steet West Third Floor
Lyndhurst , NJ   07071 - 3603
(201 ) 460 - 4700

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Edwards
dee@ilight.com
1290 Wall Steet West Third Floor
Lyndhurst , NJ   07071 - 3594
(201 ) 460 - 4700

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Large-scale, 3D simulations of complex configurations using Computational Fluid Dynamics (CFD) have become increasingly critical in the design of aircraft, aerospace vehicles and propulsion systems. The CFD analysis process consists of three phases: pre-processing, solver and post-processing. Multi-disciplinary techniques, which analyze phenomena such as fluid-structure interaction, introduce additional computational complexity and require non-trivial coupling between CFD and structures codes. In designing software for each of the three analytical phases, software developers tend to look at what is optimal and necessary for their particular operation. Considerations such as data sharing, archiving and interoperability are given less attention than efficiency and accuracy of physical models. As the pace of simulation increases, the sheer volume of numerical data requires that a stable and easy to operate methodology be made available to developers and users of pre-processing, post-processing and solver tools. The offeror proposes to create a software toolkit that provides an intelligent storage and retrieval mechanism for large-scale CFD simulation data, combining software libraries, database/compression methodologies and web browser-style control and query tools. This toolkit will assist those developing and maintaining solver codes as well as the analyst/designer community and greatly accelerate aerospace vehicle synthesis by enabling data sharing, storage efficiency and interoperability.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA programs such as ASCoT, AVST and 3rd Generation RLV all have components that hope to develop new, fast tools for rapid assessment of new vehicle configurations. FAAST is one such element. The technologies proposed herein can be used by authors of these solvers and pre/post-processing tools to accelerate their development of tools. Designers and analysts can then take advantage of the benefits of the technologies in their work as well. Current NASA CFD tools that are known to the offeror are CFL3D, OVERFLOW, TLNS3D, VULCAN and USM3D.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Integration of the proposed technologies into CFD analysis codes will increase productivity and interoperability between industrial users of CFD in the Aerospace, Automotive, Propulsion and Chemical Process industries. The technologies are applicable to commercial CFD codes, those developed by the government and in-house codes as well. The technology can be extended to other forms of analysis, such as structural analysis, heat transfer and computational electromagnetics (CE). Furthermore, it can be used to assist in coupling such codes for multi-disciplinary analysis.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
MATRA
P.O. Box 1264
Carmel , CA   93921 - 1264
(831 ) 917 - 0943

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Dr. Shun Lung
kolar@redshift.com
P.O. Box 1264
Carmel , CA   93921 - 1264
(831 ) 917 - 0943

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Fracture mechanics capabilities based on finite element multidisciplinary analysis will be designed and developed. Incorporating finite element based fracture mechanics analysis will enhance the power and strength of the MDFEM software. An in depth literature survey will be conducted to assess the appropriate finite element methodology for modeling crack tip stress regions and associated material constitutive relations. In order to characterize fracture behavior, crack tip finite elements, crack tip opening displacement and J-integral methods will be implemented. Software to perform these fracture related parameters will be developed and tested with benchmark problems.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The development of fracture mechanics capabilities enhances the strength and applicability of existing finite element multidisciplinary engineering analysis software such as STARS software. Such capabilities enable application to monitor and perform risk assessment of flight vehicle structural integrity in NASA?s shuttle programs, Flight Testing of Research flight vehicles, extending flight envelope of test flight vehicles. The structural integrity and safety monitoring of NASA's shuttle programs, Flight Test Research vehicles, lauch vehicle structural integrity risk assessment will be potential beneficiaries.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
The development of fracture mechanics capabilities enhances the strength and applicability to monitor and perform risk assessment of structural integrity in such areas as commercial airplane structures, nuclear power plants, and other fracture and damage critical structural components in rail-roads, off-shore structures, and automobiles. Other applications include home land security related issues with nuclear power plants, and other fracture and damage critical structural components of national security interests.

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

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Christina Arnold
carnold@metrolaserinc.com
2572 White Road
Irvine , CA   92614 - 6236
(949 ) 553 - 0688

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Investigation into fatigue damage precursors over the last decade has demonstrated that surface-