TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposal program will develop and demonstrate an affordable
manufacruring approach to fabricate the latest generation of damage
tolerant composite fan case designs. These designs embed a grid of
stiffener ribs within the composite laminate to limit damage propagation
that is initiated during the fan blade containment event. This grid blunts
the crack growth and restricts damage within a "safe zone" that permits
structural viability of the case after the blade is contained. The
proposed work package will demonstrate that advanced braiding concepts can
be used to fabricate these composite-toughening elements in a cost-
effective manner. This economically viable fabrication method will allow
widespread application of the toughened design concept and enable weight
efficient, safe containment system designs for high bypass turbofan
engines.

POTENTIAL COMMERCIAL APPLICATIONS
Assuming that the technology is successfully demonstrated, this approach
can be applied to the design of all jet engine fan containment cases.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Mike Braley
A & P Technology
4595 East Tech Drive
Cincinnati , OH   45245 -

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
A&P Technology
4595 East Tech Drive
Cincinnati , OH   45245 -

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An airborne fire is one of the most dreaded emergencies, as all pilots will acknowledge. Isolated at high altitudes, a fire-induced loss of systems can disable the airplane beyond control. The space shuttles and the International Space Station face a worse predicament. While an aircraft can land on a short notice, spacecrafts are totally vulnerable. Existing fire sensors detect smoke or flame, indicating that the fire is in a relatively advanced stage. These systems produce false alarms 499 times out of 500. The proposed fire onset monitoring system (FOMS) will: (a) detect fire at a very early stage, without false alarm, by performing trend analysis on key chemical markers and temperature, and (b) provide a continuous status update for intelligent decision making by the crew. In Phase I, Intelligent Optical Systems (IOS) will establish the feasibility of FOMS by detecting 50 ppm of carbon monoxide with a signal-to-noise ratio of at least 5. The project team, with fifty person-years of hardware and software know-how, will develop and test a compact prototype in Phase II.

POTENTIAL COMMERCIAL APPLICATIONS
Terrestrial spin-off markets for the FOMS system abound. Worldwide, over 100,000 commercial aircraft are operating without reliable fire detectors. The FOMS device will be used in aircraft ranging from large commercial jet liners to small commuter aircraft, private airplanes, helicopters, military fighters, and transport aircraft. With 3,000 new jetliners on order (900 scheduled for delivery this year), 500 business jets scheduled for delivery per year and 500 fighters being sold annually, demand for FOMS will be very strong.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Kisholoy Goswami
Intelligent Optical Systems, Inc.
2520 W. 237th Street
Torrance , CA   90505 - 5217

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Intelligent Optical Systems, Inc.
2520 W. 237th Street
Torrance , CA   90505 - 5217

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The ultimate objective of the proposed project is to develop a practical onboard, inert-gas generation system for fuel tank inerting on small transport aircraft (e.g. Boeing 737). The system would operate autonomously and provide inert gas to the fuel tank ullage, maintaining an inert environment in the fuel tanks during all phases of aircraft operation, including descent and ground operation. The proposed system would be based upon a novel system comprising semi-permeable membrane air separation modules; a unique two-impeller, one-expander, electrically-assisted turbocompressor operating in foil bearings; and lightweight heat exchangers. The system will address the key issues associated with small transport aircraft fuel tank inerting: minimal or no electrical power available on the ground, minimal or no bleed air available in most phases of flight, and the critical need for effective inerting during ground operations. The Phase I effort will focus on developing specifications for the system, producing a preliminary system design, identifying key technology elements that require further development, and producing a preliminary palletized system design for a future flight test. In Phase II, we will demonstrate key technology components and further define the palletized system test to be conducted during Phase III.

POTENTIAL COMMERCIAL APPLICATIONS
A small transport aircraft fuel tank inerting system has significant business potential. It is anticipated that forthcoming rules from the FAA will potentially require that fuel tank ullage be inerted on commercial transport aircraft during a significant portion of the operational envelope. If this airworthiness directive is issued, it will create an immediate, large and ongoing market for this technology.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Patrick J. Magari
Creare Inc
Etna Rd., P.O. Box 71
Hanover , NH   03755 - 0071

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Creare Inc
Etna Rd., P.O. Box 71
Hanover , NH   03755 - 0071

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An innovative approach for passenger aircraft seat and restraint system design for improved occupant protection is proposed. The innovation consists of using metal/honeycomb composites for the seat legs and a tailored stiffness characteristic for the seat back tilt. Using advanced dynamic finite element modeling for the seat/occupant system under crash impulse loads, the seat design will be optimized and a preliminary design will be developed for improved safety. The finite element model will be validated using existing seat test data from the manufacturer. (P-01566)

POTENTIAL COMMERCIAL APPLICATIONS
The successful Phase I program will provide a solid foundation for a Phase II research and development effort. Prototype seat designs derived from this research will be manufactured with cooperation from subcontractors. Use of lightweight metal/composite materials, special seatback stiffness characteristics and inflatable lap belts to mitigate injuries during aircraft accidents will help the airline industry and seat manufacturers to promote better safety standards.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Kash Kasturi
Foster-Miller, Inc.
350 Second Ave.
Waltham , MA   02451 - 1196

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Foster-Miller, Inc.
350 Second Ave.
Waltham , MA   02451 - 1196

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this proposal, Epoch Engineering, Inc. (EEI) and its subcontractor, Intelligent Automation, Inc. (IAI), propose a Fire Prevention Monitoring Capability (FPMC) for assessing the availability of pre-fire and hidden fire Acoustic Emission (AE) information for fire prevention. The first element of the FMPC is a non-contact and portable Robust Laser Interferometer (RLI) designed by EEI. RLI has large dynamic range (up to 180 dB in acceleration) and provides very wideband measurements (0 to 262 kHz or higher). Moreover, it has excellent linearity across the frequency range and its performance is independent of environmental temperature at the measuring poiont. A large dynamic range means the sensor can pick up small emissions buried in large vibrations. In other words, the sensor is much more sensitive than conventional contact type sensors. Wideband measurement capability means the sensor is very versatile for various diverse applications. The second element of FPMC is an automatic fault detection and isolation tool developed by IAI that consists of Fast Fourier Transform, Principal Component Analysis (PCA), and a neural network classifier. We will use common aerospace materials to demonstrate the performance of FPMC. This proposal is relevant to this subtopic as it specifically asks for fire prevention.

POTENTIAL COMMERCIAL APPLICATIONS
Pre-fire detection in a flight vehicle is very important for flight safety. It also plays an important role in the overall maintenance approach. Since the sensor in our proposed FPMC system is very sensitive, we will be able to detect the acoustic emissions associated with "pre-fire" situations and hidden fire. Hence early diagnosis is possible now. At the end of Phase 2, we will have a tool that will be ready for real-time applications. We expect that the FPMC will be integrated into a more comprehensive total health monitoring capability that includes the demonstrated capability to also provide robust pro-active monitoring of rotating machinery, among other things.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Theodore C. Goodenow
Epoch Engineering, Inc.
814 West Diamond Avenue, Suite 325
Gaithersburg , MD   20878 - 1416

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Epoch Engineering, Inc.
814 West Diamond Avenue, Suite 325
Gaithersburg , MD   20878 - 1416

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
API proposes to develop a comprehensive toolkit for the construction of real-time diagnostics of aerospace systems. The toolkit includes modular ruggedized hardware components, based upon a COTS design, scalable from 400MFLOPS to 40 GFLOPS or more. Hermetically sealed, thermal managed processors in a small form factor will enable installation in hostile, confined spaces.

A software tool, based upon API?s system integration tool, will permit rapid specification of several aspects of diagnostics tasks, including signal extraction, analysis, statistical analysis, and diagnostics logic. Designs will be specified in a format compatible with diagnostics experts, requiring little knowledge of DSP or real-time systems. A library of software components will enable rapid assembly of diagnostics systems, with the tool synthesizing the required real-time code.

The concepts will be illustrated with several demonstration applications.

POTENTIAL COMMERCIAL APPLICATIONS
We have first-hand experience with the target users of this technology, and have received direct requests for these capabilities. We have provided similar capabilities in the laboratory, and have fielded instrumentation and health monitoring systems at Rolls-Royce/Allison engines, General Electric Aircraft Engines, NASA MSFC and Stennis Flight Center, and USAF/AEDC. These systems are laboratory only use, with the exception of some of our work with NASA/MSFC which is part of the Integrated Vehicle Health Monitoring program for SSME in-flight monitoring. A significant opportunity exists to make the systems flight-capable for testing of new systems. This is a niche market, with estimated potential sales of $2-3M over a period of 3 years.

A much greater potential exists for condition-based monitoring of aircraft engines. Significant unnecessary expenditures result from conservative maintenance schedules, handling worst case scenarios. Condition-based monitoring can continually compute the health and prognosis of an engine, provided that sufficient computational hardware is available. We estimate this market in excess of $40M per year. There is a compelling reason for the industry to invest in this technology, with individual airlines spending in excess of $2B per year for maintenance.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Jason Scott
Active Parallel Instrumentation, Inc
2506 W. Linden Ave
Nashville , TN   37212 - 5226

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Active Parallel Instrumentation, Inc
2506 W. Linden Ave
Nashville , TN   37212 - 5226

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key to producing reliable engine diagnostics and prognostics resides in the fusion of multisensor data. There are many different approaches to support the development of such systems. These can be generalized into three basic classes. First are physical models. Second are rule-of-thumb systems developed and refined by human engineering and maintenance experts. Third are statistical models that ?learn? from examination of real data that contain nominal and known fault conditions. Each of those techniques has unique strengths and weaknesses. Proposed here is the fusion of models from all three classes to produce a unique hybrid engine diagnostic and prognostic system. Fusion of sensors and techniques has been shown to improve detection and classification performance while simultaneously significantly reducing false alarms. The proposed development team is unique as well. IAC has proven statistical and hybrid system development expertise and has already developed a variety of statistical fusion techniques for engine diagnostics and prognostics. Pratt & Whitney, world leaders in the design and production of gas turbine engines, will be supplying expertise and C17/F117 engine data from on-going in-flight collections with NASA. Luppold & Associates has designed many of Pratt & Whitney?s advanced control systems and will supply physical model expertise.

POTENTIAL COMMERCIAL APPLICATIONS
The potential commercial applications for the technology, techniques, and systems to ultimately come out of this SBIR are significant. Pratt & Whitney, a partner on Phase I, is interested in applying the technology developed here to its engines. If Phase I is successful, Pratt & Whitney will also participate on Phase II and will be a potential Phase III transition / commercialization partner. The technology to be developed here can be applied to significantly improve automated monitoring and condition-based maintenance of all military and commercial aircraft gas turbine engines as well as all commercial / industrial gas turbine engines (such as those used in electrical generation plants).

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Tom Brotherton
Intelligent Automation Corporation
13029 Danielson Street, Suite 200
Poway , CA   92064 - 8811

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Intelligent Automation Corporation
13029 Danielson Street, Suite 200
Poway , CA   92064 - 8811

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
One of the most overlooked aspects of health management in aging aircraft is monitoring of the wiring and interconnection systems themselves. Brought to public attention by the crashes of TWA 800 and SwissAir 111, the problem of wiring faults and even fires on aircraft been the subject of investigation by numerous government and civilian agencies. Military needs are no less severe. Using a combined approach which can automatically diagnose problems on the ground as well as in flight, IPITEK's Smart Universal Sensor Interface (SUSI) can provide multi-faceted health monitoring as well as other value-added performance features such as piecewise upgrades, smart functions, reconfigurability, adaptability to a wide range of subsystems, network integration, and support for both copper and fiber interconnectivity.

POTENTIAL COMMERCIAL APPLICATIONS
SUSI is not only designed for advanced diagnostics and other added features but also to reduce weight, wiring, component, and subsystem overhead, which can lead to further operational cost savings. Both military and commercial aircraft could benefit from advanced smart sensor systems capable of providing real-time data on subsystem health.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
David Schaafsma
IPITEK
2330 Faraday Avenue
Carlsbad , CA   92008 - 7216

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
IPITEK
2330 Faraday Avenue
Carlsbad , CA   92008 - 7216

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The safety and efficiency of transportation will be enhanced by systems that provide on-line health monitoring and management of vehicle subsystems and overall system information. The health management systems will require the ability to combine information and data from many sources over local/wide area networks and make the data and processing of the data transparent to the many users who have a need to view and monitor the information.

The specific aim of this project is to develop a suite of object-oriented software tools that will support design, analysis, implementation, and use of on-line aircraft subsystem health monitoring systems. We will achieve this aim by building on Creare's previously developed, patented, award-winning middleware software which enables processing, communication, and administration of real-time and on-line data. We will augment this enabling technology with an easy-to-use graphical user interface (GUI) for configuring health monitoring systems including smart sensors and sophisticated signal processing routines.

During Phase I of this project, we will demonstrate the feasibility of our approach by developing a bench-top prototype. During Phase II, we will optimize, implement, and test a full-scale health management system for an aerospace vehicle.

POTENTIAL COMMERCIAL APPLICATIONS
This system could be used to enhance the safety and effectiveness of any electronic control or health management system. As such, it is relevant to military and commercial vehicles of all types, and also to a broad range of other equipment and facilities, particularly in the process and control industry.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Dr. Anthony J. Dietz
Creare Inc
Etna Rd., P.O. Box 71
Hanover , NH   03755 - 0071

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Creare Inc
Etna Rd., P.O. Box 71
Hanover , NH   03755 - 0071

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR will result in a system for Automated Noninvasive Health Monitoring and Failure Detection in Aircraft Electrical Wiring Systems. A Smart Insert Connector (SIC) will be designed for one-time insertion into all wiring end-connectors in existing aircraft. Each SIC will be based on VLSI/MEMS technology and will incorporate several systems on a microchip: a wiring testing and inspection system, an on-line wire failure analysis and diagnosis system, and a switching system for testing large bundles of multiple wires. A VLSI/MEMS hand-held Interrogator Unit (IU) will be designed to allow a roaming human Maintenance Technician to communicate with the distributed network of SICs for noninvasive harvesting of the wire health status resident in the memory of each SIC. Additional decision-making software will allow the integration of the SIC inputs into an analysis of the overall health status of the complete aircraft wiring system. This system will avoid the removal for testing of 5,000 wires per year and drastically reduce the probability of aircraft malfunctions, which cause crash disasters such as TWA 800 and SwissAir 111. WPI, Inc. has 40 years of experience with aircraft connectors and wiring, numerous patents, and a successful product line of military and commercial electrical connectors.

POTENTIAL COMMERCIAL APPLICATIONS
Phase III commercial applications of this wiring testing and health monitoring system are already being explored. The first is refitting existing aircraft with Smart Insert Connectors for wire monitoring, an application being explored in partnership with Delta Air Lines, and the second is equipping new aircraft with Smart Connectors as they are built, which is being explored in connection with Boeing. Rob Lyon, Manager of Electromechanical Systems Engineering for Delta Air Lines, will provide consulting advice for this Phase I SBIR to give guidance on the airline industry?s wire testing needs, regulation procedures and requirements, and commercialization procedures. WPI has the experience to handle product development and commercialization, having obtained 36 patents and taken them on to develop a full product line of over 100 electrical connector products and numerous other military/commercial products. Our initial analysis shows that applying this technology to the aerospace industry alone could be a niche market of $1-2 billion. We will also explore markets in a large class of other systems, such as wiring fault detection in automobiles, power transmission lines, home/office wiring infrastructures, and more.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Kartik Moorthy
Williams-Pyro, Inc. (WPI)
2721 White Settlement Road
Fort Worth , TX   76107 - 1331

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Williams-Pyro, Inc. (WPI)
2721 White Settlement Road
Fort Worth , TX   76107 - 1331

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aircraft icing severity depends on two key cloud parameters, liquid water content and droplet size. Proposed is a simple instrument using multiple hot wire elements to measure cloud droplet size (median volume diameter) and liquid water content.

The unit utilizes three hot wire sensor elements each of a different diameter, all exposed to the same airflow. By virtue of their different diameters, the elements have different collection efficiencies with respect to droplet diameter.

Liquid water content is determined by the total amount of water measured by all three elements. Droplet median volume diameter is determined by the response differences between the three elements. The range of droplet measurement includes super large droplets SLD).

The proposed instrument has no moving parts, no optics and emits no electromagnetic radiation. It is a first principles device capable of complete calibration. Its response time is under one second.

Total frontal area of the instrument is less than four square inches. Less than 500 watts of power are required for operation in continuous icing conditions. The operational airspeed range is compatible with operational jet and turboprop transport aircraft.

Applications include icing research and operational cockpit warning for icing and SLD conditions.

POTENTIAL COMMERCIAL APPLICATIONS
The primary commercial application would be in general and commercial aviation safety. Development of the unit would lead to a simple operational system that would provide cockpit indication not only of the presence of icing conditions, but an indication of the severity, based on cloud liquid water content and droplet size. Also immediate warning could be provided for super large droplet (SLD) conditions that can lead to very rapid loss of aircraft performance.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Lyle Lilie
Science Engineering Associates
114 C Mansfield Hollow Road, Box 605
Mansfield Center , CT   06250 - 0605

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Science Engineering Associates
114 C Mansfield Hollow Road, Box 605
Mansfield Center , CT   06250 - 0605

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is an efficient deicing system for aircraft leading
edges using polycrystalline piezo-electric-based active-fiber composites.
NASA and the entire aircraft industry need this technology to improve the
safety of aircraft operations under icing conditions while minimizing the
impact of ice removal on aircraft weight and fuel consumption. We propose
to use a composite structure consisting of a polymer matrix embedded with
piezoelectric fibers, driven by a highly efficient electronic controller.
Polycrystalline actuators can achieve substantial strain levels (that are
high enough) to break the ice, which are then carried away in the slip
stream. The controller actuates the composite to break ice films, then
recovers the unused actuation energy for very low net power consumption.
In Phase I, we will demonstrate the feasibility of using the actuator to
prevent ice buildup on aircraft leading edge surfaces by fabricating a
model deicing system, evaluating performance in a sophisticated icing
tunnel which simulates in-flight icing conditions, and designing a
prototype system for demonstration in Phase II.

POTENTIAL COMMERCIAL APPLICATIONS
This deicing system can be applied to a broad range of commercial and
military aircraft. It has the potential to drastically reduce power
requirements and can improve small aircraft deicing systems in particular,
since hot gases from turbines are not available. The system can easily be
retrofit to existing aircraft and can be applied to non-aircraft
applications, such as shipboard surfaces where ice buildup must also be
minimized.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Bruce R. Pilvelait
Creare Inc.
Etna Rd., P.O. Box 71
Hanover , NH   03755 - 0071

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Creare Inc.
Etna Rd., P.O. Box 71
Hanover , NH   03755 - 0071

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We will investigate the feasibility of thermographic inspection system that employs a small, handheld inspection head, which is swept over an area to be inspected, using IR transmitting fibers and a fiber coupled laser-heating system. The system, if successful, will allow more precise control of heating and data acquisition than current NDE systems allow, and as a result, provide NDE capabilities (in particular, for cracks oriented perpendicular to the sample surface) that significantly surpass the performance of current pulsed or scanned systems. The system will be suitable for either handheld, or robot-mounted operation. The system will utilize a novel signal processing scheme to allow signal to noise comparable to full scale system. The small size and absence of active heating or electronic components in the scanning head will allow inspection of limited access areas, such as radii or tanks, where access is available through a small port, or in environments where hazardous vapors pose an explosion risk.

POTENTIAL COMMERCIAL APPLICATIONS
This proposal was formulated based on input from current and prospective customers in Government and private aerospace manufacturing, service, and R&D, including NASA, commercial airline, and military NDE personnel. These customers indicated a high degree of interest in a small scanning system that would incorporate the advanced features of the pulsed systems that they were using on other applications, and also allow access to confined spaces and operation in hazardous vapor environments. Although the proposal has focused primarily on aerospace applications, significant market opportunities exist in the automotive and energy industries. The growing use of composites in automotive manufacturing is presenting new QA and NDE challenges to the industry. TWI has been a pioneer in applying Pulsed Thermographic solutions to automotive applications, and has worked with Ford, General Motors, Chrysler, Nissan and numerous Tier 1 suppliers. The automotive market is distinctly different than the aerospace market, primarily because of the high volume requirements and the importance of autonomous, on-line systems. TWI has recognized and responded to these needs, will build on our experience in the automotive industry in marketing the handheld scanning system.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Steven Shepard, Ph.D.
Thermal Wave Imaging, Inc.
845 Livernois Street
Ferndale , MI   48323 - 2308

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Thermal Wave Imaging, Inc.
845 Livernois Street
Ferndale , MI   48323 - 2308

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
New materials, manufacturing processes, structural designs, and damage mechanisms pose continual challenges to the state-of-the-art in nondestructive evaluation (NDE). Thick sections and complex multi-layered structures create difficult to inspect areas in which corrosion or other damage can propagate undetected. Although X-ray and ultrasonics are used for inspection of thick sections for buried flaws and hidden corrosion, they provide little information on absolute material properties. There is a need for higher speed, wide area scanning capabilities to image not only flaws, voids, porosity, corrosion, and geometric features in complex structures, but also metallurgical properties and stresses. This Phase I effort will demonstrate high-resolution sensor arrays that combine giant magnetoresistive sensing elements with shaped field, distributed drive windings. The goal of this Phase I is to lay a broad foundation on which numerous new applications can be addressed. Specifically, absolute conductivity and permeability mapping using magnetoresistive sensor arrays will be developed and demonstrated. Phase I will include demonstrations both of absolute property measurement and geometric feature or defect mapping. Phase II will demonstrate commercially viable solutions for selected applications for imaging of welds, subsurface features, heat treatment quality, residual and applied stresses (for ferrous alloys), or in-situ sensors for health monitoring.

POTENTIAL COMMERCIAL APPLICATIONS
JENTEK?s current customer base of Fortune 500 companies (including ALCOA, Siemens, 3M, Lockheed Martin, Boeing, Rolls Royce, etc.) and government agencies (including FAA, Air Force, Navy, Army, NASA, etc.) have all purchased commercial electromagnetic sensors and systems from JENTEK, and each have identified specific needs for deeper penetration imaging. These include (1) hidden corrosion mapping in aircraft, (2) in-situ health monitoring, extending the current capability of surface mountable JENTEK MWM eddy current sensors to support deep penetration damage monitoring, (3) imaging and defect mapping for cooling holes in turbine blades, (4) detection of buried inclusions in titanium castings, (5) dwell-time fatigue detection in engine disks to prevent uncontained disk failures, (6) residual and applied stress mapping in landing gear, train rail and wheels, pipelines, welds, and other alloy steel applications, (7) thick metallic coating porosity measurement, (8) 2nd and 3rd layer crack detection for aircraft lap joints, (9) thick composite characterization for impact damage, manufacturing quality, geometric features and porosity, (10) thick plate heat treat characterization, (11) burnishing assessment for ferrous and nonferrous alloys, extending the use of JENTEK sensors for the C-130/P-3 propeller population, and (12) applications in subsurface geometric feature mapping using both contact and noncontact sensors.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Neil Goldfine
JENTEK Sensors, Inc.
110-1 Clematis Avenue
Waltham , MA   02453 - 7013

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
JENTEK Sensors, Inc.
110-1 Clematis Avenue
Waltham , MA   02453 - 7013

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA has initiated several programs in recent years that will require distributed/embedded sensors to achieve vehicle safety and efficiency goals. The number of sensors needed implies use of optical fiber sensors for their small size and low mass. Only the technique offered has demonstrated the ability to obtain 1000's of high spatial resolution measurements on a single fiber. The Phase I effort, utilizing both testing and analysis of key technology, will produce a prototype design for a flight capable demodulation system. In Phase II, the prototype will be fabricated, tested, and the design modified to produce demodulation systems NASA can depend on to meet its program goals.

POTENTIAL COMMERCIAL APPLICATIONS
The commercial applications include health monitoring in civil, aviation, and marine structures. The push to smart materials and structures requires monitoring of all phases of the construction process and will create a large demand for grating arrays and dependable demodulation systems. The technology also competes with traditional foil strain gage and thermocouple technology which is well established in all areas of industry. As demodulation systems are introduced to solve measurement problems not addressed by traditional sensors, the technology will gain acceptance by the engineering community and encroach on the traditional sensors market share.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Brooks Childers
Luna Innovations Incorporated
2851 Commerce Street
Blacksburg , VA   24060 - 6657

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Luna Innovations Incorporated
2851 Commerce Street
Blacksburg , VA   24060 - 6657

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
DACCO SCI, INC., (DSI) proposes a Phase I SBIR program to use an electrochemical impedance spectroscopy (EIS)-based corrosion sensor to monitor the integrity of an adhesive bondline and correlate sensor measurements with mechanical properties. Using this sensor approach to detect moisture intrusion into a bondline will give advance warning of potential environmentally induced bondline deterioration. Corrective action can then be taken prior to permanent disruption of the bondline. Delaminations and kissing unbonds may also be detectable. This monitoring technology could eventually be used as a standard tool in the suite of nondestructive evaluation (NDE) methods for evaluating the integrity of adhesive bond. Because embedded sensors are not required, both existing and future structures could be inspected and monitored. Increased confidence and reliability of bonded structures would accrue.

POTENTIAL COMMERCIAL APPLICATIONS
Reliability of bonded structures will increase as a result of this health monitoring. Readiness and safety are also benefits to improved health monitoring. Extending the technology to composite materials is anticipated to be very feasible. Adhesively bonded repair patches (metal or compos-ite) on aging aircraft are one important application. Composite-reinforced infrastructure (e.g., bridge supports) is another application of interest. Other potential applications include storage tanks, pipelines, and weapon systems and components.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Guy Davis, Ph.D.
DACCO SCI, INC.
10260 Old Columbia Road
Columbia , MD   21046 - 1794

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
DACCO SCI, INC.
10260 Old Columbia Road
Columbia , MD   21046 - 1794

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Collaborative Decision Making (CDM) embodies a new philosophy for managing air traffic. The initial implementation of CDM has been aimed at Ground Delay Program (GDPs). It has become increasingly evident that very significant delays and throughput degradations have arisen from en-route airspace problems and limitations, particularly from convective weather activity and demand surges. Work is currently underway within the aviation community to apply CDM technology and concepts to the management of en-route traffic (Collaborative Routing). An essential component in the successful application of CDM to GDPs was the development of consensus around a fair allocation scheme for landing time slot assignment (ration by schedule, using the Official Airline Guide (OAG) schedule as a baseline). No such fixed baseline exists for the enroute airspace. Although there are several concepts for resource allocation before the CDM community, the feasible implementation of these concepts has yet to be demonstrated. We propose to construct a collaborative routing rationing algorithm (CRRA) to assign use of en route resources to individual flights. It will be shown that such an algorithm is both feasible and that it can be made consistent with traffic management goals and with the CDM paradigm.

POTENTIAL COMMERCIAL APPLICATIONS
A collaborative routing rationing algorithm (CRRA) has commercial application in several areas. Air Traffic Management (ATM) is confronted with demand-capacity imbalances in the en route environment on a daily basis. They require a systematic means for distributing scarce en route resources that is equitable across the air carriers. Conversely, the Airline Operations Centers (AOCs) require a means of inputting preferences to ATM when rationing is performed and a means of manipulating the resources they are allotted to maximize efficiency in their operations. CRRA would provide the receptacle for their preferences and refinements. Lastly, there are several en route management tools developed commercially or by R&D funds: the Post Operations Evaluation Tool (POET) and Collaborative En-Route Flow Management (C-Flow) developed by Metron, Inc. the Collaborative Routing Coordination Tool (CRCT) developed by MITRE, and the Future Automation Concepts Evaluation Tool (FACET) developed by NASA. Each of these would benefit from a core algorithm to perform rationing of scarce en route resources.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Robert Hoffman
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Metron, Inc.
11911 Freedom Drive, Suite 800
Reston , VA   20190 - 5602

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron, Inc. builds a data mining tool for fleet management that allows the user, in real time, to identify cost benefit opportunities within large quantities of operational data. Designed for Airlines Operations Control (AOC) personnel, we build a tool that manages large quantities of current time and archived air traffic, crew, passenger, hub, weather, and National Airspace System (NAS) data. Our tool exploits standard data mining techniques, electronically encoded playbooks for weather events, a predictor for reasoning about weather and how it affects the future of flights, and an easy-to-use Graphical User Interface (GUI). The user receives personalized reports that identify cost savings due to weather conflicts, hub priority changes, avoidance of traffic congestion, and other factors. Our data mining tool allows AOCs to make real-time decisions that anticipate future events and save the airlines money, reduce traffic congestion, and improve the overall NAS efficiency.

POTENTIAL COMMERCIAL APPLICATIONS
A data mining tool that focuses on National Airspace System (NAS) level data and Traffic Flow Management (TFM) constraints has commercial application for both the airlines and government Air Traffic Control (ATC) applications. For the airlines, the data mining tool is designed primarily for airline dispatchers. Metron works closely with airlines on several TFM projects including the Collaborative Decision Making (CDM) program and with the deployment of the Flight Schedule Monitor (FSM) and the Post Operations Evaluation Tool (POET). These systems, as well as the proposed data mining tool, provide cost benefits to the airlines by providing them access to valuable ATM system and NAS data. In a collaborative framework, these systems also provide benefit to Air Traffic Service Providers (ATSPs). The proposed data mining tool may be incorporated into the ATSP side of the CDM program or into specific TFM facilities, and can assist in strategic traffic flow management decision making.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Mark Klopfenstein
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA   20170 - 4835

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposals describes a new approach to implementing computer simulations of NAS using software autonomous agents. Each software agent is implemented as an independent entity with its own thread of control. This approach provides the ability to host the simulation on many computers, allows greater code reuse, is physically and logically scalable, and provides efficient and effective simulation of complex collaborative decision making. Another important benefit is that the agent paradigm for simulation allows the simulation to be gracefully enhanced, adding greater resolution to particular aspects of the simulation without affecting the remainder of the simulation. Future NAS simulations will need to be able to model a wide range of requests and decision processes which will be made by pilots, AOCs, and Air Traffic Controllers as NAS evolves toward the greater flexibility of Free Flight. Many important characteristics of the flow of aircraft will be emergent properties of the interaction of many flights, many companies, and many ATSPs. Attempting to simulate complex situations without this realistic diversity will lose much of the structure which is essential to understand. The work herein proposed will lead to NAS simulations which can meet this objective.

POTENTIAL COMMERCIAL APPLICATIONS
IAI has already achieved success in commercializing its work with software autonomous agents, and is nearing the release of its Diva product which will greatly simplify the use of this technology by others. Software agents are also key to enterprise integration, which is becoming a cornerstone of e-commerce.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Dr. Leonard Haynes
Intelligent Automation, Inc.
7519 Standish Place, Suite 200
Rockville , MD   20855 - 2785

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Intelligent Automation, Inc.
7519 Standish Place, Suite 200
Rockville , MD   20855 - 2785

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron proposes to develop a parallel-processing discrete event simulation of the entire National Air Space that can be used to assess courses of action in response to disturbances that impact Air Traffic Management. The innovative thrust is to use the NASA-patented SPEEDES parallel-processing engine. The ability of SPEEDES to efficiently distribute processing over large numbers of processors will allow the entire National Airspace (NAS) traffic (>50,000 flights) to be simulated quickly enough to support Air Traffic Management decisions in near-real-time. The resulting simulation would allow visualization/analysis of the propagation of delays across the air traffic system and rapid assessment of the probable downstream effects of decisions. Metron has already built a ?Pre-prototype? NAS simulation on SPEEDES, which has simplified models of schedules, flights, and airports and has been run with a small subset of a day?s flights between a handful of airports. Metron proposes that during Phase I, the Pre-prototype be demonstrated and benchmarked using a typical full day?s traffic, and that a full design for a Prototype with higher fidelity models and a link to live data be completed. The Phase II objective is to complete and demonstrate the Prototype.

POTENTIAL COMMERCIAL APPLICATIONS
Metron has a good track record of transitioning simulation products developed for the government to commercial application. Metron?s Flight Schedule Monitor (FSM) decision aid was developed for and is currently used by the Federal Aviation Agency (FAA) and is also in use at several airlines. The NASim will also be a valuable near-real-time ?what-if?? tool for commercial airlines. There is also a possibility that Air Traffic Control in the United States may be privatized, and major firms, such as GE-Honeywell and Boeing, have organized and are equipping to potentially take on that role. NASim would be a valuable asset to such companies.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Gary Blank
Metron, Inc.
514 Via de la Valle, Suite 310
Solana Beach , CA   92075 - 2718

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Metron, Inc.
514 Via de la Valle, Suite 310
Solana Beach , CA   92075 - 2718

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Extended operations and sleep loss can lead to fatigue, decrements in decision making, and other challenges to performance, productivity, and safety. The NASA Ames Research Center's Fatigue Countermeasures Group has conducted an extended program of research to develop and evaluate operationally useful countermeasures to mitigate the adverse effects of fatigue. This proposal describes an effort to conduct a meta-analytic integration of the evidence on the effectiveness of fatigue countermeasures such as naps, exercise, bright lights, and other interventions. The specific objectives of the Phase I research are to: (a) summarize and integrate existing research on naps as a fatigue countermeasure using a meta-analytic statistical technique, (b) identify the strength and significance of the effects of naps on performance, fatigue, and other relevant outcome measures, and (c) identify factors (such as length of the nap and the post nap interval) that may moderate the effects of naps as a fatigue countermeasure.

POTENTIAL COMMERCIAL APPLICATIONS
The integration of existing research and the identification of new and effective fatigue countermeasures should have a considerable impact on Federal as well as commercial users in aviation, transportation, medicine, equipment operation, manufacturing and other operational environments that involve 24-hour demands. This research will result in precise, empirically-based guidelines for implementing fatigue countermeasures in civilian and military operational environments. The integration and summarization of research results in this area will result in specific recommendations for research, policy and application.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
James Driskell
Florida Maxima Corporation
507 N. New York Avenue, R-1
Winter Park , FL   32789 - 3186

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Florida Maxima Corporation
507 N. New York Avenue, R-1
Winter Park , FL   32789 - 3186

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Rotary-wing vehicles proposed for improved system capacity must meet civil global aviation requirements for safety, efficiency, and affordability. To achieve the needed advances, greatly improved modeling is required. Many advances have been made in measuring dynamic characteristics of rotary-wing vehicles, for example by Tischler et al. However, innovative advances are needed in methods to capture the dynamic and cross-coupling effects that are still a challenge and impediment to rapid design cycles. A very recent advance in test techniques utilizes water as a test medium for dynamic testing. This method circumvents many of the problems presented by air as a medium, by allowing testing in slow motion, by separating model and test support frequencies, by greatly improving signal-to-noise ratios, and by allowing the traditional advantages of the familiar water tunnel or channel, with its unparalleled flow visualization.

POTENTIAL COMMERCIAL APPLICATIONS
The ability to predict maneuvering aerodynamics and stability parameters early in the development cycle will reduce the time, risk, and cost of new rotorcraft. The methods described herein also apply to high performance aircraft development.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Brooke Smith
AeroArts LLC
PO Box 2909
Palos Verdes Peninsula , CA   90274 - 2909

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
AeroArts LLC
PO Box 2909
Palos Verdes Peninsula , CA   90274 - 2909

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An integral element of meeting NASA's objective of tripling airport
throughput over the next decade is the utilization of helicopters and
tiltrotors to provide feeder service to major airports. Among the key
challenges in ensuring safe, high-volume terminal area rotorcraft
operations are identifying and mitigating potential hazards posed by
complex aeromechanical interactions ranging from wake vortex encounters to
powered flight in steep descent. To address these challenges, it is
imperative to develop fast yet high-fidelity rotorcraft vortex wake
modeling methods and simulation models in these flight regimes. To meet
this need, a physics-based analysis will be developed that captures key
aspects of rotorcraft wake aeromechanics in the complex terminal area
flight environment, including both interactions with wakes of nearby
aircraft and "self-interactions", such as vortex ring state. The enabling
technical innovation will be novel fast viscous/turbulent wake decay and
vorticity transport methodologies tailored to rotorcraft and coupled with
the state-of-the-art real time free wake simulation capabilities of the
CHARM rotorcraft model. The resulting product will be a hierarchy of
models enabling both detailed off-line assessment and on-line real-time flight simulation of potentially hazardous flight conditions including rotorcraft wake encounters and vortex ring state.

POTENTIAL COMMERCIAL APPLICATIONS
The proposed simulation could be used to determine safe operation
procedures for tiltrotors and rotorcraft used as shuttle service between
local airports and major airport hubs. Assessment results from this code
could be implemented within or used in support of NASA's AVOSS system for
reducing IFR spacing requirements between tiltrotors and aircraft.
Rotorcraft manufacturers could use this tool to enhance "design for safety"
of future rotorcraft. In addition, a capability for predicting rotorcraft
flight dynamics in terminal area operations would directly support flight
training activities by simulation manufacturers and rotorcraft operators,
as well as the military services.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Daniel A. Wachspress
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ   08618 - 2302

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ   08618 - 2302

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal puts forward a novel training methodology that takes advantage of automation?s potential as a high-speed decision aid and the strengths of human pattern recognition and conditioning. The methodology applies optimal control theory to solve for a vehicle?s trajectory and the required control inputs. A preview of the commanded input suite is displayed to the pilot, which will dynamically update as the vehicle state changes in time. Using this and other innovative training displays, the pilot should be able to execute numerous maneuvers previously considered outside the operational envelope, in addition to performing ?standard? emergencies with a high degree of control consistency and accuracy. The preview display?s function can be extended to serve as an on-board pilot cueing aid. This methodology can be incorporated in flight simulators to train pilots across a range of platforms. The initial target application will be for rotorcraft autorotation, a particularly challenging and accident-prone multi-axis maneuver. Phase I will focus on the development of the pertinent optimal algorithms and displays, as well as demonstration of the concept?s feasibility in the rotorcraft autorotation domain. Phase II will focus on practical application of the concept to rotorcraft autorotation training and expansion to other flight vehicles.

POTENTIAL COMMERCIAL APPLICATIONS
The pilot training software developed under this project can be used to train helicopter pilots to perform safe autorotation maneuvers. The core technology may also be adapted for use in training human operators of other vehicles (flight, ground, and underwater) where multi-axis control in time-critical situations is required.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Bimal Aponso
Systems Technology, Inc.
13766 S. Hawthorne Blvd.
Hawthorne , CA   90250 - 7083

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Systems Technology, Inc.
13766 S. Hawthorne Blvd.
Hawthorne , CA   90250 - 7083

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is divided into three parts. The first conducts basic measurements to assess the accuracy of the two-microphone scheme, developed by P. Dean, to measure the impedance of Helmholtz resonators in grazing flow. Dean?s method is the benchmark standard used to measure the effects of grazing flow and SPL on the impedance of cavity-backed liners. Implicit in its derivation is the assumption (1) that the incident sound pressure can be accurately measured with a single microphone located on the resonator face-plate and (2) that a single microphone located in the center of the cavity back wall can accurately describe the response of the cavity to the incident sound field. Unpublished in-house impedance measurements suggest that the use of a single microphone to measure cavity pressure may be subject to errors as large as 20%. The research program will determine the minimum number of microphones required to accurately measure Helmholtz resonator impedance. The second systematically investigates the effects of orifice spacing and orientation on resonator impedance as a function of SPL and grazing flow. The third develops accurate 1-DOF and 2-DOF models of the impedance of resonators as a function of SPL, grazing flow and boundary-layer thickness.

POTENTIAL COMMERCIAL APPLICATIONS
1. One of the primary commercial applications of the technology would be to license it to a commercial providers of duct propagation codes and/or to airframe and engine manufacturers. The control of engine noise in the community surrounding commercial airports is known to be a difficult problem to solve given the cost and weight constraints of the aircraft industry. It is envisioned that the duct propagation software could be licensed/sold capable of selecting resonator geometry that can be both economically constructed and achieve efficient sound absorption for a specified input noise signature.
2. A secondary application of the technology would to incorporate the impedance code into a as low frequency sound propagation and attenuation code to license/sell it to manufactures of electrical generating turbines and HVAC fans.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Alan Hersh
Hersh Acoustical Engineering, Inc.
780 lakefield Road, Unit G
Westlake Village , CA   91361 - 2657

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Hersh Acoustical Engineering, Inc.
780 lakefield Road, Unit G
Westlake Village , CA   91361 - 2657

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA?s current aircraft noise reduction research focuses on reducing the perceived noise levels of future aircraft by a factor of two. This Phase I effort will generate fast accurate finite difference algorithms for use in active noise design of inlet nacelles. This includes an analytical correlation of the geometrical parameters necessary to quickly maximize the attenuation of an active noise system. The secondary noise actuator size and number, position in relation to the primary noise source, angular orientation as well as other geometrical and acoustical properties will be evaluated in the optimization process to determine the maximum possible attenuation. Using this correlation as a starting point, the full numerical solution can be used to fine-tune the parameters for the particular complex engine geometry under consideration. The new algorithm will lead to more efficient use of active control and provide NASA and industry a revolutionary tool for planning and accessing future noise attenuation goals.

POTENTIAL COMMERCIAL APPLICATIONS
KJB Consultants? acoustic nacelle design code will be enhanced for aircraft engine manufactures to optimize aircraft nacelles to reduce noise emitted toward the ground and the aircraft fuselage. The code will have the capability to optimize both passive and active noise reduction. The code could also be used in the acoustic design of automobiles, mufflers and complex industrial systems. The codes will be constructed with enough geometric flexibility to model mufflers, automobile interiors, and other business applications besides an aircraft nacelle.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Kenneth Baumeister
KJB Consultants
7380 Baldwin Creek Drive
Middleburg Hts. , OH   44130 - 5544

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
KJB Consultants
7380 Baldwin Creek Drive
Middleburg Hts. , OH   44130 - 5544

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Innovative materials and processing capabilities are needed for the fabrication of ceramic matrix composite (CMC) components for efficient engine systems. NASA has identified CMCs as the only materials that will meet the combination of increased safety, reduced cost, and reduced weight as operational temperatures climb to higher levels (per AeroMat 2000 Annual Conference, June 2000). The current UEET (Ultra Efficient Engine Technology) initiative at NASA is looking at components such as combustor liners and vanes in particular. In light of these needs, this Phase I SBIR proposal addresses lightweight, high temperature, and low cost CMCs for engine and propulsion applications, particularly in the temperature range of 1200-1400?C. The work will specifically address the development of a hybrid PIP/MI SiC fiber-reinforced SiC-matrix composite (SiCf/SiC). Effort will focus on using SiC-yielding preceramic polymers and a combination of PIP and melt-infiltration processing routes that will reduce the cost and time for producing SiCf/SiC composites compared to traditional CVI/MI processing. The intent of this work is to carry out PIP/MI process development, generate a preliminary database of thermal and mechanical properties, and select a process to use for component development and demonstration in a Phase II effort.

POTENTIAL COMMERCIAL APPLICATIONS
The results of this program will be immediately applicable to the on-going work of a number of companies for programs such as Integrated High Payoff Rocket Propulsion Technology (IHPRPT) and other initiatives. For example, Boeing-Rocketdyne is interested in evaluating the use of CMCs for transpiration cooled injector faceplates or rocket engine thrust chamber liners for use on the IHPRPT initiative and other advanced engine programs requiring lightweight high temperature CMC materials. Understanding the thermal and mechanical performance of PIP processed CMC materials will improve the timeline and extent of insertion of CMC materials into a variety of lightweight, high temperature applications.

Rockwell Science Center has also expressed interest in C/SiC and SiC/SiC CMCs to use as the exhaust ramp material for the Aerospike Engine concept.

General Electric Power Systems and Solar Turbines, Inc., are investigating SiC/SiC CMC materials for turbine engine applications and are very interested in opportunities for reductions in cost and processing time.

NASA has identified CMCs as the only materials that will meet the combination of increased safety, reduced cost, and reduced weight as operational temperatures climb to higher levels (per AeroMat 2000 Annual Conference, June 2000). The need for high-temperature CMC materials is evident in applications such as turbomachinery, thrust chambers, seals, bladed-disks (blisks), and various structural panels that may have a requirement for integrated cooling channels. The NASA UEET program in particular has identified applications such as combustor liners and vanes that will require CMC components.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Dr. Timothy E. Easler
COI Ceramics, Inc.
9617 Distribution Ave
San Diego , CA   92121 - 2392

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
COI Ceramics, Inc.
9617 Distribution Ave
San Diego , CA   92121 - 2392

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Innovative Scientific Solutions, Inc. (ISSI) proposes the development of a high-framing rate quantitative flow imaging system, with potential application to a wide variety of optical diagnostic techniques for reacting and nonreacting flows. The system is based around a novel "burst-mode" laser, which has been recently developed by our Ohio State University (OSU) collaborators, a version of which is currently in place at NASA Glenn Research Center. The particular emphasis of the proposed Phase I program is to 1) demonstrate high-framing-rate velocity-field imaging using a 2D laser diagnostic technique known as Planar Doppler Velocimetry (PDV) in a reacting flow and to 2) extend the flexibility of the burst mode laser by building a prototype optical parametric oscillator (OPO) to be pumped by the burst-mode laser, enabling Planar Laser-Induced Fluorescence (PLIF) measurements of combustion intermediate species. The Phase II program would build upon this demonstration and design novel ways of attaining high-framing rate measurements of the 2D velocity field and minor species concentration (e.g., OH).

POTENTIAL COMMERCIAL APPLICATIONS
Products from this program may include new research tools for the laser diagnostics community, in particular, high-speed imaging and Planar Laser-Induced fluorescence (PLIF) tools. Although this market is relatively small (scientific market vs. broad commercial market), its impact on the understanding of high-speed combustion (and therefore on mobile and airborne power generation) could very large. Furthermore, advances in diagnostics tools such as that proposed would likewise spur the development of advanced computational tools such as Large-Eddy Simulation (LES).

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Campbell Carter
Innovative Scientific Solutions, Inc.
2766 Indian Ripple Road
Dayton , OH   45440 - 3638

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Innovative Scientific Solutions, Inc.
2766 Indian Ripple Road
Dayton , OH   45440 - 3638

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is the design of an active control system to reduce aircraft turbofan engine rotor-lock inlet noise generated when rotor tip speeds become transonic. The system design for this program would be tailored to the requirements of the NASA GRC 22-inch diameter Source Diagnostic Fan. The proposed Phase I research program consists of (1) a conceptual design of a prototype active control sound source and (2) a MatLab based design of an active control system. The concept is an innovation because it uses an active/passive segmented liner noise cancellation concept, developed at Hersh Acoustical Engineering, Inc. (HAE) to cancel rotor-lock noise. A successful Phase I research program will establish the feasibility of developing an active control system capable of efficiently suppressing rotor-lock noise.

POTENTIAL COMMERCIAL APPLICATIONS
1. One of the primary commercial applications of the technology would be to license it to airframe and engine manufacturers. The control of engine noise in the community surrounding commercial airports is known to be a difficult problem to solve given the cost and weight constraints of the aircraft industry. It is envisioned that the rotor-alone active noise control software/hardware elements could ultimately be an integral part of a hybrid active/passive liner that efficiently suppresses multiple BPF harmonic tones as well as broadband noise.
2. HAE intends to seek patent protection of its intellectual property and license the technology to manufacturers of modern large commercial jet aircraft such as Boeing, manufacturers of large aircraft engines such as General Electric Aircraft Engine Division, Pratt & Whitney and Allied Signal Corporation as well as manufacturers of engine nacelles such as Vought Aircraft Industries, Inc.
3. HAE intends to seek Phase III funding and partnership with Boeing, GEAE and/or P&W to further develop the technology and commercial potential of the active broadband noise control concept.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Bruce Walker
Hersh Acoustical Engineering, Inc.
780 lakefield Road, Unit G
Westlake Village , CA   91361 - 2657

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Hersh Acoustical Engineering, Inc.
780 Lakefield Road, Unit G
Westlake Village , CA   91361 - 2657

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
New and innovative ways to apply many of the newly developed, advanced materials are needed. The proposed technology addresses this need by enabling an innovative thermal spray process for use with newly emerging ultraviolet (UV) and/or visible light-curable polyimides. The technology combines a moderate amount UV/visible light radiation with other processing modes into a novel technology to spray polyimide powders without the use of solvents as neat polyimide films and coatings and as near-net-shape products.
The solventless spray, lay-up aspects of the proposed powder spray technology addresses the mandate that NASA has for producing Advanced Materials with Reduced Emissions. The advanced materials that can be processed with this technology, UV/visible light-curable polyimides, have application in gas turbines, rocket and turbine based combined cycle engines. The technology enables a process for economical and reliable application of these advanced materials to fabricate light-weight jet engine components.
The Phase II project will result in a prototype system for application of UV/visible light curable polyimides and other polymers.

POTENTIAL COMMERCIAL APPLICATIONS
The technology is suitable for use in applying a broad range of commercially available thermoplastic and thermoset polymer powder materials as neat materials and as ?designer?, composites, nanocomposites, including functionally graded coatings and composites. Commercial applications that include adhesives, scratch resistant coatings, protective coatings, high elongation coatings, self-extinguishing coatings, circuit board coatings, electrically conductive coatings and electrical component potting applications.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Lawrence Farrar
Montec Research
1901 South Franklin
Butte , MT   59701 - 4167

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Montec Research
1901 South Franklin
Butte , MT   59701 - 4167

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SATS is NASA's efficient personal air transportation vision. SATS airplanes must strive for higher levels of safety, speed, and comfort than small airplanes currently offer. BRS therefore proposes to develop an advanced parachute recovery system for high performance GA aircraft capable of 300-knot cruise speeds. BRS has already received FAA certification for its Cirrus Design SR-20 parachute recovery system which evolved from the BRS sport aviation products. However, heavier and faster GA aircraft will require the development of new and innovative technologies to enhance the performance, safety, reliability, and successful commercialization of an advanced parachute recovery system. First, these systems must be capable of reliable deployment in catastrophic emergencies from stall speeds to "loss of control" speeds approaching 350 knots. Secondly, the weight and volume of the systems and components is more critical to the performance and utility of GA aircraft than for recreational type aircraft and must be minimized. Finally, a steering capability for obstacle avoidance in hazardous landing areas will be investigated. These enhancements to aircraft recovery systems will be a significant step toward improving the safety of GA travel, and so have definite commercial potential.

POTENTIAL COMMERCIAL APPLICATIONS
BRS is continuing to work with Cirrus Design in Duluth, Minnesota to develop recovery systems for their aircraft. The BRS CAPS is already standard equipment on the Cirrus SR20 aircraft. and is being adapted to the SR22 aircraft, a upgraded version of the SR20. Future Cirrus aircraft include retractable landing gear versions of the SR22 and eventually larger, faster composite aircraft that will incorporate a variety of new technologies, including more efficient propulsion systems such as cost effective jet engines for GA aircraft. The Cirrus Design aircraft designs are a prime example of next generation of GA aircraft and are therefore, the ideal platform for the development of the advanced recovery system. A key component of BRS's strategic plan is to aggressively pursue relationships with as many of the currently existing and future aircraft manufacturers as possible to expand the recovery system product line for the general aviation and larger experimental aircraft markets. These markets can be a significant revenue source for BRS with the average recovery system price ranging from as low as $5,000 and up to $30,000.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Anthony D. Kasher
Ballistic Recovery Systems, Inc.
300 Airport Road
South St. Paul , MN   55075 - 3551

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Ballistic Recovery Systems, Inc.
300 Airport Road
South St. Paul , MN   55075 - 3551

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A critical barrier for GA to serve as viable and volume personal transportation is the lack of a cost-effective, yet open-growth, Lean DesignO and manufacturing methodology for installing emergent technologies in existing airplanes as well as for producing new small airplanes. Munro & Associate?s (Munro?s) vision is to create an innovative , Lean DesignO integration system to select, source, adapt and install 21st century automotive industry consumer comfort technologies - SATS-LDATT, this will serve as a vital enabler for turning NASA's SATS Lab Vision into reality. Munro will use its automotive industry technology transfer expertise to first create an automotive technology evaluation process in conjunction with its design team

POTENTIAL COMMERCIAL APPLICATIONS
Commercial applications include full cockpit and cabin installations in new as well as the 100,000 plus travel active existing small airplanes in the country. Spin offs include software applications for custom designs.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
DAVID Grieco
Munro and Associates
900 Wilshire Drive, Suite 301
Troy , MI   48084 - 1634

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Munro and Associates
900 Wilshire Drive, Suite 301
Troy , MI   48084 - 1600

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
DSI will develop an integrated backplane/server solution for the SATS cockpit. The GAAINS (General Aviation Aircraft Information Network Server) solution will provide the foundation for tomorrows SATS cockpit. DSI believes in the spirit of SATS, and through the integration of COTS technologies combined with current open architecture standards, a new enabling platform will be developed which increases cockpit functionality, while decreasing pilot workload at a fraction of the cost of today?s systems. DSI?s GAAINS architecture is based on current communication industry standards for redundancy and fail over scenarios. Ruggedized COTS hardware coupled with proven smart software suites will provide new heights of modularity, cost savings, and ease of access, operation and growth. This backplane/server platform will ultimately increase the chance of success for NASA?s SATS vision.

POTENTIAL COMMERCIAL APPLICATIONS
Commercial applications include the GAAINS installations in the existing 100,000 travel active airplanes, as well as new GA aircraft. This product will also be designed for integration with the ground and satellite based GA extranet (SATS-Net). Outside of this, there is almost no limit to expansion and opportunities in terms of providing information to the GA aircraft. The implications of this are vast. As the Internet has matured and brought forth a host of viable information services, the potential for radically improving the availability of information services to the GA aircraft is enormous. This also has strong potential for the commercial airline industry. As concepts were borrowed from the automotive industry, the likelihood that advances in the GA market could be applied back to the automotive industry are very high.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Gregg Schneider
Dynamic Systems Integration
529 Central Drive
Virginia Beach , VA   23454 - 5277

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Dynamic Systems Integration
529 Central Drive
Virginia Beach , VA   23454 - 5277

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aircraft turbine engines continue to evolve to meet demands for smaller, lighter power plants while improving fuel efficiency and increasing power output. As a result, turbine engines must endure ever increasing operating temperatures. Turbine blades in the hot-gas path are coated with a thermal barrier coating (TBC) that reduces thermal stress and extends their service life. Thermal and centrifugal stresses can initiate and propagate cracks that cannot be seen through the TBC. A method for in-plant inspection of new blades, blades removed from service, and refurbished blades is needed. IDI proposes an NDE technique employing a novel microwave resonant stripline probe that detects changes in the dielectric thickness of the TBC, any oxide formation, as well as surface defects in the Inconel substrate. The NDE system output is a two-dimensional color image detailing the overall health of the component. Phase I will design, build and test a prototype microwave probe. Phase II will further develop the NDE microwave system for demonstration in a production line environment.

POTENTIAL COMMERCIAL APPLICATIONS
The proposed microwave system can be used by blade and engine manufacturers and repair facilities to inspect coated blades for damage. The method will reduce inspection/rework costs and assure reliability of the blades. Other applications include inspection of aircraft parts such as landing gears that have complex geometries.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Jack Edmonds
Innovative Dynamics, Inc.
2560 North Triphammer Road
Ithaca , NY   14850 - 1252

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Innovative Dynamics, Inc.
2560 North Triphammer Road
Ithaca , NY   14850 - 1252

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The regenerated barrel cam engine addresses the needs of the GAA engine subtopic by providing very large reductions in life cycle cost (40-50% fuel use reduction, reduced aircraft and engine size and weight, less maintenance & overhaul), substantial performance improvements (smaller, lighter, aircraft and more powerful engines, greater range), increased safety and reliability (diesel-like engine features, safer fuel, ease of operation), improved environmental compatibility (reduced noise and emissions, use of alternative fuels). Regeneration has been under development at Caterpillar, ReJen, and elsewhere, under NASA, Navy, and Caterpillar funding. The objective of this program is to combine two engine technologies: in-cylinder regeneration and the axial cylinder, barrel-cam engine design. The successful merging of these two, highly synergistic, technologies will result in a new type of engine with outstanding applicability to GAA propulsion. The barrel cam engine circumvents several of the more severe problems confronting regenerated engine development, and the regenerated cycle reduces the peak cylinder pressure loads on the barrel cams. Basic feasibility of the regenerated barrel cam engine appears promising based upon completed analyses and component tests. In Phase I, detailed design of a Technology Demonstrator version of this engine will be completed. This engine will be built and tested in Phase 2. Caterpillar will match Phase 1 and 2 NASA funding.

POTENTIAL COMMERCIAL APPLICATIONS
In-Cylinder regeneration can have a huge impact throughout the power generation, earthmoving, and transportation industries. Ultimately, this new engine technology could find its way into nearly all reciprocating engines with dramatic effects on world-wide fuel usage, the national economy and employment, and US technological leadership. This is why Caterpillar has been so interested in regeneration technology and is supporting this project. It is most especially applicable to aircraft, where its compact size, exceptional fuel economy, and other features will result in a substantial reduction in aircraft life-cycle cost, increased performance, and improved reliability and safety. This new approach of a barrel-cam regenerated engine offers a means to bring this technology to market sooner and to further improve its performance and applicability to aircraft. It offers a means to most dramatically improve GAA propulsion technology.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Allan Ferrenberg
The ReJen Co.
255 Rimrock Dr., Swall Meadows
Bishop , CA   93514 - 7133

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
The ReJen Co.
255 Rimrock Dr., Swall Meadows
Bishop , CA   93514 - 7133

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
It is proposed to develop a hybrid piezoelectric/fiber optic (HyPFO) monitoring system for aerospace vehicles and structures for the purpose of quick non-destructive evaluation and long-term health monitoring. The development of the monitoring system will be based on Acellent Technologies' patented SMART Layer concept of integrating a network of miniature actuators and sensors in the form of a flexible layer onto structures. Currently, Acellent's SMART Layer product hosts only piezoelectric elements; however, there has been substantial interest in incorporating other types of sensors. Due to the popularity of fiber optic sensors for health monitoring in recent year, it is proposed to incorporate fiber optics sensors onto the current SMART Layer product to create a hybrid piezoelectric/fiber optic monitoring layer. The proposed hybrid piezoelectric/fiber optic system will use the piezoelectric actuators to input a controlled excitation to the structure and the fiber optic sensors to capture the corresponding structural response. The objective of the Phase I study will be to develop a hybrid piezoelectric/fiber optic monitoring layer prototype along with validation and proof testing. The end product will be a hybrid piezoelectric/fiber optic monitoring layer that can be easily integrated onto structures to perform various NDE and health monitoring tasks.

POTENTIAL COMMERCIAL APPLICATIONS
Upon completion of the HyPFO structural health monitoring system, the U.S. government and the aerospace industry would receive substantial benefits from the developed technology. The proposed development would bring to market a commercially viable product that will increase the reliability, improve the safety, and reduce the maintenance cost of aerospace vehicles and structures. Potential structural applications include real-time detection of structural defects (fatigue, cracks, corrosion, disbonds), long-term monitoring of vehicle health, characterization of load environment, and life prediction. Other uses include in-situ monitoring of material processing, identification of manufacturing defects (porosity, inclusions), and material property characterization. The technology developed here for critical space structures could be further distilled down to other commercial applications in industries such as aviation, automotive, naval/off-shore, and civil infrastructures.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Peter Qing
Acellent Technologies, Inc.
562 Weddell Drive, Suite 4
Sunnyvale , CA   94089 - 2108

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Acellent Technologies, Inc.
562 Weddell Drive, Suite 4
Sunnyvale , CA   94089 - 2108

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An innovative software tool is proposed to provide shared access to all pertinent information involved in the dynamic testing process. The dynamic testing process is collaborative and requires the sharing of many forms of data. By leveraging standard Internet technologies and customizing them for the dynamic testing application, all requirements, schedules, procedures, photographs, measurement data, and analysis data can be accessed in a hierarchical fashion using a standard web browser. The Project Site would serve as a ?virtual meeting room? where all test team members could share data and collaborate for the duration of the test program. The proposed research focuses primarily on determining the best architecture for implementing such an application. Application prototypes will be developed based on the candidate architectures. The best architecture will be determined from a comparison and evaluation of the application prototypes in the areas of robustness, performance, scalability, reliability, and security. In addition, open communication standards and open source frameworks will be investigated to ensure that the target application is state-of-the-art. By customizing and extending Internet technologies, a practical software tool can be developed which will shorten test cycles and improve the overall quality of the dynamic testing process.

POTENTIAL COMMERCIAL APPLICATIONS
ComFrame believes that there is a strong need within the environmental testing community for a software tool which will allow distributed data access and collaboration between project team members. Basing the tool upon leading industry standards will facilitate industry adoption of such a platform by allowing easy integration with existing test tools and processes. Once the application is proven, relationships and partnerships can be established with system vendors in the dynamic/vibration testing industry in order to broaden marketing opportunities. Finally, the basic software framework can be extended into other areas of environmental testing such as thermal, wind tunnel testing, and machinery monitoring. Given the cutting edge nature of the product and the broad market scope, ComFrame believes that the collaborative platform proposed herein has significant potential as a commercial offering.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Blaine Anderson
ComFrame Software Corporation
110 12th Street North, Suite A114
Birmingham , AL   35203 - 1537

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
ComFrame Software Corporation
110 12th Street North, Suite A114
Birmingham , AL   35203 - 1537

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced high performance cryogenic propulsion systems will be developed for second and third generation reusable launch vehicles. These systems will require higher thrust to weight ratios, demanding lighter pumps, higher operating speeds, and increased pressures. For reusable engines, cryogenic turbopump load support bearings have historically been life limiting components. New software is required to improve the design of rolling element and fluid film bearings to expand the operating envelope while improving life and reliability relative to today's hardware. An innovative bearing design tool is proposed that will facilitate improved design early in the initial pump development program. The tool will enable detailed thermomechanical design in the initial design phase. Traditionally this level of analysis has only been used to address problems that are discovered during hardware testing. The reason for this is that developing the required high fidelity models is currently complicated and expensive. A new software tool is proposed that will use a modern Graphical User Interface and model development tools to simplify the process. Thus more robust design will be accomplished in the initial design phase.

POTENTIAL COMMERCIAL APPLICATIONS
There are currently no modern Windows-based software analysis models available that support a multi-bearing system, rotating shaft load support bearing design, that has the level of sophistication required for cryogenic pump bearings. In fact, the most frequently used bearing design codes are DOS based and lack many of the routines required to address rocket engine component design. A modern Windows based bearing code will appeal to the users of the current generation codes, which includes the aerospace, automotive, and precision instrument industries.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
James D. Moore
SRS Technologies
500 Discovery Drive
Huntsville , AL   35806 - 9999

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
SRS Technologies
500 Discovery Drive
Huntsville , AL   35806 - 9999

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An innovative method for integrating experimental design with computational flowfield methodology for developing advanced liquid rocket combustors is proposed. Despite dramatic advancements in computational fluid dynamics (CFD) and diagnostic instrumentation, rocket engine designers still rely on antiquated experimental data bases. The gap between on-going experiments and real design issues is not yielding sufficient validation data. The proposed research will identify critical physical combustion problems, hypothesize experiments to elucidate the problem, simulate the experiment with CFD to locate necessary validation measurements, specify an appropriate instrumentation system, oversee the experiment, and synthesize the results. The utility of this new methodology will be demonstrated by critiquing existing experiments and planning new research projects.

POTENTIAL COMMERCIAL APPLICATIONS
The current practice of conducting liquid rocket engine research with large programs at numerous universities and at many different government laboratories demand that an experimental design methodology procedure be established to insure that these are productive in providing deeper insight into high pressure combustion. These investigators expect to benefit commercially and professionally by consulting on the coordination, planning, and integration of the multitude of on-going federally funded research activities.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Richard Farmer
SECA, Inc.
3313 Bob Wallace Ave., Suite 201
Huntsville , AL   35805 - 4063

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
SECA, Inc.
3313 Bob Wallace Ave., Suite 201
Huntsville , AL   35805 - 4063

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is the development of a compressible gas/liquid framework to simulate cavitation in cryogenic liquid rocket pumps. The generalized compressible framework will allow for the specification of variable thermodynamic properties and physical equations-of-state appropriate to cryogenic working fluids. Furthermore, the acoustics within a multi-phase gas/liquid mixture will be modeled rigorously, allowing for the simulation of interactions between pressure fluctuations and the cavitation process at different frequencies. The model will be implemented within an unstructured numerical framework that will effectively deal with complex geometries and resolve flowfield features using local grid adaption features. In particular, the proposed CFD tool is expected to improve modeling capabilities for inducers that operate at low pressures and high rotational speeds. These flow conditions make inducers susceptible to cavitation instabilities, which have the potential to generate large unsteady forces and reduce engine durability. Most current CFD tools for simulating cavitating flows have originated from incompressible formulations and have difficulty in modeling unsteady phenomena in multi-phase mixtures. With the inclusion of appropriate physical sub-models, the proposed innovation has the potential to be an important and useful tool in the analysis and design of liquid rocket turbopumps.

POTENTIAL COMMERCIAL APPLICATIONS
Empirical correlations and 1-D analyses currently used for turbomachine design are remarkably successful at design conditions but are less reliable at off-design conditions, when unsteady flow, coupled with cavitation, can generate potentially damaging pressure fluctuations and vibrations. Most current CFD tools for pump analyses have been derived from incompressible formulations and are inadequate for these complex flows. To address these deficiencies, the commercial CFD tool resulting from the proposed Phase I and subsequent Phase II efforts will have a generalized compressible formulation with temperature effects. The cavitation model will be implemented within our commercial code CRUNCH, which has an unstructured framework and is ideal for complex turbomachine geometries. This tool may be used with current design procedures to either refine preliminary designs or correct potentially anomalous behavior in existing designs. A broad market exists for this commercial product, including companies that are currently involved in designing space propulsion systems, as well as designers of high-energy industrial pump systems. Such pumps must perform at off-design conditions over extended periods, making it critical that cavitation effects be eliminated or mitigated.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Ashvin Hosangadi
Combustion Research and Flow Technology,
174 North Main Street, POB 1150
Dublin , PA   18917 - 2108

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Combustion Research and Flow Technology,
174 North Main Street, POB 1150
Dublin , PA   18917 - 2108

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A vehicle for access to space with the ability to successfully takeoff from and land on a land- based runway would have a great potential for reducing the cost and enhancing the safety of space access involving a reusable launch vehicle. A significant difficulty in attaining such an ability is the need to have acceptable low-speed handling and flight characteristics. In addition, a stable and robust control system for the low-velocity (as well as for the usual high-velocity) flight regimes is required. NASA is developing the X43A hypersonic vehicle with such a vision, and is currently exploring the vehicle's high-speed characteristics in another of its programs. This Phase I proposal is to explore the vehicle's low-speed flight envelope and handling characteristics, by performing flight tests on the X43A-LS, a low speed version of the X43A already developed by AAC. This work will lay groundwork for a Phase II effort to test adaptive controller designs for the X43A, to develop a supersonic version of the vehicle, to develop an integrated health monitoring system for the vehicle's small-scale turbine engine, and to explore application of AAC's high-compression video recording technology.

POTENTIAL COMMERCIAL APPLICATIONS
The vehicle design and telemetry system will be a key part of hypersonic as well as commercial aircraft in the future. Therefore, the technology from the X-43A-LS will have a commercial use. Accurate Automation designed and supplied the X-43A data collection subsystem. The IVHS would be used on all space vehicles and for commercial aircraft in FOOQA systems. Accurate Automation is working with Rolls Royce and is talking with American and United Airlines for non engine related areas.
The area of hypersonics will be a Billion Dollar industry within 20 years. The X43ALS is a key componen for the development of reusable hypersonic systems.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Christopher S. Gibson
Accurate Automation Corporation
7001 Shallowford Road
Chattanooga , TN   37421 - 1716

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Accurate Automation Corporation
7001 Shallowford Road
Chattanooga , TN   37421 - 1716

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Light alloy composites are required for components for reusable launch vehicle airframes due to their improved strength to weight ratios. This document proposes development of magnesium composites with advanced anodized coatings for improved corrosion and wear resistance. These coatings will be produced by electrochemical treatment of magnesium composite components for use in aerospace, military, automotive and recreational applications. Both the method of coating production and the properties obtained by the composites will be significant improvements over previous surface treatments for magnesium in terms of performance, economics, and environmental safety. Magnesium components exposed to the environment are prone to corrosion. This proposal concerns adaptation of a recently developed magnesium anodization process for composites which are exposed to corrosive environments. This process builds a thick, dense coating on magnesium that has both excellent corrosion resistance and wear resistance. Composites with the proposed coating system would be less expensive and demonstrate improved performance with a process has been proven environmentally sound. Testing of the coatings will include wear resistance and salt spray testing. Application of the anodization process will be tested on several magnesium alloys as well as representative magnesium composites of AZ91 and Mg12Li with carbon fiber and alumina non-metallic second phases.

POTENTIAL COMMERCIAL APPLICATIONS
Benefits of the new coating system will be improved wear and corrosion resistance for magnesium alloys and composites. Commercial applications include use of anodization on magnesium automotive components, recreational equipment, power tools, and industrial equipment exposed to harsh environments.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Thomas F. Barton
Eltron Research Inc.
4600 Nautilus Court South
Boulder , CO   80301 - 3241

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Eltron Research Inc.
4600 Nautilus Court South
Boulder , CO   80301 - 3241

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Triton Systems responds to the NASA need to produce new and unique lightweight high use temperature polymer materials with inherently high gas barrier, strength, and thermal stability. These multifunctional materials will enable the use of composite materials to replace metallic cryogenic fuel tanks for the Reusable Launch Vehicle (RLV). We will combine our extensive background in layered silicate nanocomposite technology with that of high use temperature polymers based on phenyl ethynyl imide (PEI) as well as Triton proprietary chemistries to achieve this goal. The incorporation of nanostructured silicate platelets into these polymer matrices will result in materials that will have superior gas barrier (i.e. hydrogen, oxygen). Further, the use of nanocomposites will achieve increased strength and decreased coefficient of thermal expansion (CTE), which will result in the elimination of microcracking observed during thermal cycling of conventional composite materials. The use of minute quantities of our patented nanosilicates will ensure that these polymers can be processed by standard molding techniques (RTM). During Phase I we will synthesize and evaluate the physical properties of several polyimide-based nanocomposite materials. For Phase II we will optimize these properties, and scale up the synthesis to fabricate a prototype composite prepared by RTM.

POTENTIAL COMMERCIAL APPLICATIONS
The polyimide nanotechnology developed by Triton Systems on this program will open the opportunity for applications in many areas where lightweight high temperature composites are required. For example, this enabling technology could be used for weight savings in high temperature environments such as those seen in the automotive, aerospace, and electronic industries.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Bryan Koene
Triton Systems, Inc.
200 Turnpike Road
Chelmsford , MA   01824 - 4053

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Triton Systems, Inc.
200 Turnpike Road
Chelmsford , MA   01824 - 4053

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Silicon carbide fiber-reinforced silicon carbide composites are being considered for reusable launch vehicle airframe components. There is a need for these composites to be joined to make complex and large shapes. TDA proposes to address this problem by using welding equipment to join SiC/SiC composites. In Phase I, we will determine the thermal processing parameters required to use welding equipment to prepare the joins. Microscopy and mechanical testing will be used to evaluate the quality of the joins.

POTENTIAL COMMERCIAL APPLICATIONS
Completion of the project will result in a method for joining and repairing SiC/SiC composites and monolithic silicon carbide in the manner of advanced metal alloys. This project will allow large and/or complex shapes to be joined for reusable launch vehicle airframe components as well as for advanced turbine engines, radiant tube heaters, heat exchangers, and erosion and corrosion components.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Mr. Jack D. Sibold
TDA Research, Inc.
12345 W. 52nd Ave.
Wheat Ridge , CO   80033 - 1917

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
TDA Research, Inc.
12345 W. 52nd Ave.
Wheat Ridge , CO   80033 - 1917

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Solidica is proposing a filament based rapid prototyping machine for the production of net shape metal and functional gradient components. Net shape fully dense metallic parts have been the holy grail of rapid prototyping since its inception. Solidica, Inc. has patented an innovative ultrasonic approach for rapid prototyping of net shape metallic parts using a ribbon feedstock. By combining the use of ultrasonics for layer-by-layer material build up of metallic ribbons with a simple machining head Solidica achieves net shape fully dense metallic components in a fraction of the time and at a lower cost than traditional machining or casting. Extending this proprietary technology to use filament based feedstock rather than ribbon, will enable a complexity of geometry that is currently only achievable for fully dense metal components through investment casting. This innovation has enormous cost saving advantages for production of both complex metallic and bimetallic functional gradient test hardware. There is currently no technology that is readily capable of forming functionally gradient structures for complex geometric shapes.

POTENTIAL COMMERCIAL APPLICATIONS
The market for rapid prototyping is an already proven market. Currently competitive machines in this area differentiate themselves through speed, accuracy, and cost. This technology is capable of leapfrogging all of the current technologies by providing the first truly functional metallic parts at a speed, accuracy and cost comparable with systems which by the nature of their material solidification or layer bonding processes are limited to plastics and powder processed materials.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Dawn White
Solidica
3941 Research Park Drive, Suite C
Ann Arbor , MI   48108 - 2219

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Solidica
3941 Research Park Drive, Suite C
Ann Arbor , MI   48108 - 2219

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
No timely and cost-effective methods now exist for the fabrication of thick-section (>=2"), continuous fiber-reinforced ceramic matrix composites (CMCs). Application of such CMCs can potentially enhance the efficiency and performance, reduce the weight, improve the durability, and lower the cost of aerospace propulsion systems, particularly those used in high temperature, high-stress environments. Achieving these benefits requires development of matrix infiltration techniques capable of efficiently producing thick parts. The quality of such parts will also depend on implementation of improved fiber/matrix interfaces and interface deposition techniques. For many projected applications, carbon fibers are of particular interest as CMC reinforcements because they are relatively inexpensive, have higher strength and stiffness and lower density than oxide or non-oxide ceramic fibers, and retain their mechanical properties at very high temperatures. The main drawback of carbon fibers, however, is their low oxidation resistance, which has prevented their extensive use in high temperature oxidizing environments. Oxide interfaces can potentially impart sufficient protection, as well as provide other essential interface functions. In previous work, Ultramet demonstrated a unique and innovative process for depositing oxide interfaces, specifically ultraviolet-enhanced chemical vapor deposition (UVCVD). Ultramet has also successfully achieved rapid infiltration of carbide matrices within thin-section (<0.125") fiber preforms using an innovative melt infiltration process. In this project, Ultramet will combine UVCVD of oxide interface coatings with a modified, innovative variation of the melt infiltration process to demonstrate the feasibility of rapidly and cost-effectively producing thick-section (>=2"), highly refractory carbon fiber-reinforced silicon carbide matrix composites suited for selected aerospace applications such as rocket engine turbomachinery components.

POTENTIAL COMMERCIAL APPLICATIONS
The composite materials to be developed in this project combine innovative interface materials, novel interface deposition, and rapid infiltration of refractory matrices into thick-section components. These components will have broad commercial applicability to a range of products, including rocket and aircraft engine turbomachinery components, recuperators, ducts, and other hot gas path components, process industry parts requiring high temperature capability and corrosive environment resistance (e.g. hot gas and liquid handling equipment) for extended periods, furnace structures, and high temperature filter elements.

NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name, Organization Name, Mail Address, City/State/Zip)
Jason R. Babcock, Ph.D.
Ultramet
12173 Montague Street
Pacoima , CA   91331 - 2210

NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address, City/State/Zip)
Ultramet
12173 Montague Street
Pacoima , CA   91331 - 2210

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Laser-Engineered-Net-Shaping (LENSTM) process uses a laser to create a molten pool on the surface of a substrate in which metal powder is then injected to increase the volume of the pool. The laser spot is selectively scanned to additively build up the required material in the desired shape. In a sequential fashion, each cross-sectional layer of the object is taken from a 3-D CAD file and deposited until an entire object is created. Many materials have been deposited using this technique, including steels and titanium alloys. Metal-matrix composites (MMCs) have been produced by the simple method of using coated particulate composite particles. The deposition of aluminum and its alloys is challenging because aluminum absorbs little incident laser energy. The ability to produce these materials may significantly impact NASA?s ability to fabricate or repair various components for advanced rocket engines. This proposal aims to develop the methodology to deposit high aluminum alloys during Phase I, and also show the feasibility of producing aluminum MM