NASA 2004 STTR Phase 1 and 2 Solicitation

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Ann T Tai
tai@ia-tech.com
10501 Kinnard Avenue
Los Angeles, CA 90024-6017
(310)474-3568

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Software is an integral part of many complex embedded systems, such as avionics, scientific exploration, and on-board systems. However, poor software reliability is a major impediment to the success of these mission-critical systems. Testing, formal verification, and code synthesis techniques have been proposed to achieve more reliable software, with automated code synthesis being the most promising method. But synthesizing a complex system from scratch is costly. A more practical approach is to synthesize systems from existing components, i.e., component-based system synthesis (CBSS). Existing research in CBSS focuses on synthesizing systems bottom-up, which has severe limitations. We propose to achieve CBSS by combining the top-down and bottom-up approaches. Specifically, we develop techniques to achieve automated system decomposition and semi-automated system architecture synthesis. The IDEAL decomposition technique decomposes a system into ``IDEAL'' units that are mathematically composable and can be developed and evolved independently. Consequently, the technique assures system reliability and enables on-the-fly feature/technology upgrades. The QoS-based architecture synthesis technique seeks to assure system QoS properties by synthesizing an architecture that optimizes QoS objectives. It also facilitates on-board system adaptation due to resource and power constraints. Combined with bottom-up techniques, such as Amphion and pattern-based code synthesis, a dramatic leap in automated CBSS capability can be achieved. The proposed research will lead to sophisticated automation for synthesizing highly reliable, multi-mission capable avionics and exploration systems.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
As software for space applications are often developed by domain experts (e.g., robotics scientists) rather than professional programmers, the resulting synthesis environment will effectively reduce development/maintenance costs and increase productivity, especially for the NASA missions that need to be equipted by large and complex software. Moreover, since future deep-space missions will require long-life, reconfigurable, upgradable high-assurance avionics systems, the resulting component-based QoS-driven software synthesis environment can be applied to enable rapid and safe onboard reconfiguration and upgrades (e.g., adding or substituting one or more components using an onboard repository or through uplinking new components to a spaceborne system).

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
As it will lead to significant improvement of productivity and appreciable reduction of development and maintenance costs, the resulting component-based QoS-driven software synthesis technology will be appealing to the commercial sector. Specifically, the component-based QoS-driven synthesis environment will greatly benefit the industry in which software are typically developed by domain experts rather than professional programmers. Such examples include bio-medical industry and robotic system manufacturers. In addition, since our component-based approach to software synthesis facilitates system reconfiguration and upgrades, a potential commercial market is the fast growing wireless communication industry which frequently requires capacity upgrade and the corresponding software adaptation.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
John I Rodriguez
NEMOmetrics@aol.com
28 Constitution Road
Boston, MA 02129-3108
(617)242-0050

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This Phase I STTR project will demonstrate the Aerospace System Monitor (ASM). This technology transforms the power distribution network in a spacecraft or aircraft into a multiple-use service, providing not only power distribution but also a diagnostic monitoring capability based on observations of the way in which loads draw power from the distribution service. Careful measurements are made power transients and this data is used to assess system functioning and identify potential faults and failures. In Phase I, ASM measurements will be made on spacecraft components like attitude thruster control valves and a power switching array. An integrated circuit will be constructed with several components running on a single power supply to demonstrate analysis of several components simultaneously. In Phase II, ASM measurements will be made on actual spacecraft.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The Aerospace System Monitor is a new, inexpensive, lightweight and non-space consuming method to measure system operation and system health. It will be a new method to obtain this information on satellite systems and provide a new source and type of data. It also represents another "string" of data for manned and high value unmanned systems which require multiple sources of sensor data.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This technology can monitor system health and identify potential problems and failures in ground venicles and in ships. It also can improve monitor energy consuming equipment in buildings and improve energy efficiency, equipment usage and user comfort.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
William Morrison
bill@teamqsi.com
100 Great Meadow Road, Suite 501
Wethersfield, CT 06109-2524
(860)257-8014

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In order to meet the challenges of space exploration, knowledge of the current and future health of mission critical systems is essential. Qualtech Systems, Inc. in cooperation with Montana Tech of the University of Montana proposes to develop an intelligent self evolving prognostic fusion solution. The proposed solution intelligently combines multiple subsystem health assessments to form an overall system health assessment. Additionally, the solution performs optimal system configuration based upon the health assessment.

Design of the individual prognostic solutions for subsystem health assessment also utilizes fusion methods. The approach combines both model based and data driven techniques to provide optimal health assessment. The prognostic solution self evolves over time to cover the life of the subsystem.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed solution offers intelligent prognostic health assessment capabilities for mission critical systems. The solution works to support the NASA "system of systems" approach. Important systems such as spacecraft, space stations, lunar and planetary bases, etc? will benefit from the proposed technology with increased reliability and safety.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed technology will have wide applications beyond NASA. Such complex systems as commercial and military aircraft, ground transportation, communications systems, power generation systems, computer systems, etc... could all benefit tremendously from the proposed technology.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Freeman Rufus
frufus@globaltechinc.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The complexity of modern systems and the stringent performance requirements for operation and uptime suggest that optimum and robust means must be deployed to make effective use of multiple sensor suites for assessing risk, identifying system degradation, understanding how system degradation progresses to failure, etc. Global Technology Connection and Georgia Tech proposes the development of data fusion architecture based on a hybrid analytical / intelligent methodology that exploits the concept of "focus of attention" via active perception in order to optimize degradation/fault classification accuracy while reducing substantially the computational burden. The fusion scheme incorporates several levels of abstraction: fusion at the data level, the feature level and the sensor level. The overall architecture employs technologies from soft computing, Dempster-Shafer theory and game theory to provide a robust and reliable platform for critical aerospace systems. Phase I effort will develop a data fusion algorithms for system degradation/fault identification.

Phase II will address design and construction of prototype field hardware for implementing the data fusion concept for components.

Several aerospace end users like Lockheed Martin and Boeing have already expressed interest in the commercial applications (Phase III) of this approach for health monitoring and life determination of Aerospace vehicles/systems.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The results of this project will assist NASA initially and other government or industry sectors eventually to fully deploy robust and reliable identification of system degradation/fault from multiple sources of raw data. When integrated into an intelligent engine environment, such practices will reduce substantially the risk of false ID of faults while achieving fault detection in the shortest possible time, increase the availability of aircraft systems and improve their reliability in the execution of critical missions. The aerospace, air traffic control, transportation, biomedical and other industries will also benefit from the introduction of these "smart" technologies into their operations.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Detecting and identifying fault and damage in aerospace systems for DoD and other government / private industries: air traffic control, pump manufacturers, HVACs, transportation, biomedical, etc.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Prith Banerjee
prith@uic.edu


(847)757-8708

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this research we will develop a system level tool to translate binary code of a general-purpose processor into Register Transfer Level VHDL code to be mapped onto FPGA-based reconfigurable hardware. We further plan to study techniques for performing hardware/software co-design on integrated systems-on-a-chip platforms consisting of embedded processors, memories and FPGAs. Finally we will develop techniques to perform area, delay and power tradeoffs in the hardware that is synthesized by our compiler on the FPGAs. We will demonstrate our concepts using a prototype compiler that will translate binary code of a Texas Instrument TMS320 C6000 processor into a hardware/software implementation on a Xilinx Virtex II Pro Platform FPGA. This work will be performed jointly between BINACHIP, a small business company, and University of Illinois at Chicago, a partner research institution

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
NASA is pursuing its missions through high visibility projects such as: (1) the Space Shuttle and the International Space Station that will help humans explore the Moon, the Mars, and beyond (2) the Earth Observing System such as the EOS Aura that will study the ozone layer and its impact on the environment (3) the Spirit and Opportunity Rovers that will explore Mars and prepare for a manned mission to Mars (4) Deep Space Missions such as the Hubble, Chandra and Spitzer Orbiting Observatories that will help us understand the Milky Way and other galaxies. All these projects have one thing in common; they require a lot of sophisticated image processing operations on images captured by various cameras that require high performance implementations. Interest in targeting FPGAs for high performance hardware-based implementations is growing. The major roadblock to obtaining this performance is the lack of sophisticated tools. The BINACHIP compiler will be useful in developing these FPGA based hardware applications by taking software implementations of sophisticated image processing applications and migrating them to hardware implementations. Possible customers for the BINACHIP compiler within NASA include the Ames Research Center, Langley Research Center, the Jet Propulsion Laboratory, Goddard Space Flight Center, Dresden Flight Center, and others.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The software that will be developed by BINACHIP will have two general application areas (1) embedded systems software (2) electronic design automation. Increasing demands for cell-phones, PDAs, and network devices have provided opportunities for the growth of embedded software, operating systems and development tools vendors. The embedded systems software market is expected to become $21 billion in 2005. As newer processor architectures are announced, there is a need to reuse and migrate the software from older generation processors to newer processors. The BINACHIP compiler will be useful to these companies to assist in the task of software migration. The second commercial area for BINACHIP is electronic design automation (EDA) that is expected to become a $6 billion market in 2005. One of these segments is that of system level EDA, which is expected to grow to at least $300 million by 2005. The BINACHIP compiler will enable translation of software from a general-purpose processor onto a system-on-chip consisting of processors, memories and FPGAs.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
David J. Strobel
dstrobel@spacemicro.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Space Micro and Clemson University have teamed for a miniature, ultra low power, space radiation dosimeter. We project this unit, "MicroRad", to be 50X smaller than the existing solution. Our ability to capitalize on COTS semiconductor devices and processes enable extremely accurate measurements at low cost. Space Micro Inc. adds their space rad hard computing to provide data logging and reporting of radiation levels. Our innovation is to utilize a normally negative response of modern microelectronics to space radiation to enable measurement of impinging particles. It is our understanding of the radiation effects physics, combined with space electronics computing and hardware which will make this R&D successful.
In Phase we demonstrate technical feasibility with a lab breadboard dosimeter and device level radiation test results. We also evaluate advanced microelectronics packaging techniques (3-D stacking) to even further miniaturize in Phase II.
At the end of Phase II we have developed and tested flight model dosimeter including ground-based radiation qualification. Use of space radiation dosimeters has been severely limited due to the size, power, cost of limited custom products; it is our mission to provide a commercially viable standard dosimeter for widespread application to new NASA long duration exploration and science missions.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Many NASA space programs will benefit from some level of on-board radiation doimetry. Our innovative dosimeter allows leveraging commercial IC processes and will enable increased performance at dramatically smaller size and lower costs. Applications range from space shuttle, space station, earth sensing missions e.g. (EOS), and deep space missions. NASA programs or missions which will benefit include Mars surveyor missions, solar system exploration e.g.(Titan, Europa, comet nucleus return, JIMO, New Discovery and Living with a Star (LWS). Products evolving from this SBIR will enable improved performance/weight on future programs such as Dawn, Aquarius, Kepler, Ocean Vector Winds, and space interferometry.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A miniature, accurate space radiation dosimeter is a key component for any commercial system in a radiation environment. These applications include commercial space platforms, both LEO and GEO. Telecommunication satellites, such as Intelsat and earth sensing applications e.g. (NOAA) may use a dosimeter for both platform and payloads. Terrestial commercial applications include nuclear power plants (near core) and research accelerators e.g. (Fermi Labs). Military applications for rad hard lower cost miniature computing include strategic satellites (MILSATCOM and GPS upgrades), strategic missiles (Trident and AF upgrades), as well as many tactical weapon programs such as MDA THAAD and MKV with nuclear survival levels.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Marek Turowski
jls@cfdrc.com
215 Wynn Dr.
Huntsville, AL 35805-1926
(256)726-4858

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Future NASA space exploration missions will use nanometer-scale electronic technologies which call for a shift in how radiation effects in such devices and materials are viewed. The energy deposition by ionizing particles (so called single event effects) can no longer be treated as an average deposition (linear energy transfer, LET). Nano-scale electronic device responses are strongly related to the microstructure of the radiation event. This requires a much more detailed physics-based modeling approach. It is also important to convert such results into engineering models used in device and circuit designs. Hence, the proposed innovation: detailed high-energy-physics-based simulations of radiation events efficiently coupled with advanced device response computations. The innovative Technology Transfer: interface specification and implementation to allow smooth, automated integration between Vanderbilt University high-energy particle advanced computations and CFDRC Device Simulator, and to enable statistically meaningful runs on a massively parallel supercomputing cluster. Significance for NASA: the impact of such radiation events has implications for nano-scale devices operating in space exploration environments. The new approach to understanding the single-event response of semiconductor materials, devices, and circuits is necessary for reliable engineering models used for early design assessment, radiation hardening, and to reduce the amount of radiation testing cost and time.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed advanced single-event models, which better reflect the true deep-space environment of exploration missions, will lead to development of new tools that will help NASA to:
(a) better understand and predict response of nano-devices and novel materials to space radiation environment, particularly high atomic number and energy particles (HZE particles) and energetic protons;
(b) assess technologies, devices, and materials of new electronic systems;
(c) better evaluate the radiation response at early design stage;
(d) develop and assess radiation hardening techniques for exploration electronics;
(e) set requirements for hardening and testing; reduce the amount of testing cost and time.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The new, more accurate radiation-effects models, integrated with automated simulation tools, will enable better understanding and analysis of radiation-response of novel nano-materials and nano-devices for advanced aerospace electronic circuits and systems. The modeling and design tools will provide reduction in cost and time-to-market through significantly reduced experimental R&D, design cycle, and laboratory testing time and cost. The new models will impact the Radiation Hardening of airborne and terrestrial electronics for defense applications (Air Force, Navy, Missile Defense Agency) and commercial applications (satellites, aircrafts).

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Chandra Parekh
engsys@aol.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed effort is concerned with the development of a novel optimization scheme and computer software for the effective design of advanced aerospace vehicles. Since such vehicles are characterized by unprecedented levels of areo-structural-controls-propulsion interactions, a multidisciplinary simulation is essential for their effective design. This can be accomplished by employing the common finite element method for the structures and also fluids and propulsion simulations. A typical multidisciplinary optimization scheme will involve structural design for minimum weight with aerodynamic data such as drag and wing platform as design variable subject to constraints like flutter and structural strength. Emphasis will be placed on the choice and calculation of suitable gradient of objective function as well as the constraints to guarantee global optimal solution. Novel numerical schemes will also be developed for efficient, cost effective solution of large complex practical problems such as current and future flight vehicles. In Phase I, the basic numerical schemes for the optimum design will be establish along with a pilot code to verify these techniques. Also developed will be a general turbulence package for any typical FE CFD software. In Phase II, a complete software will be developed and checked out for the simulation of complex practical problems.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The development of multidisciplinary optimization capabilities enhances the strength and applicability of the existing CAE software such as STARS and its application for the optimum design of advanced aerospace vehicles.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Other potential applications include machineries, automobiles and nuclear power plant. The commercialization of the product will be done on Peter Drucker's philosophy based on innovation and marketing.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Ping-Chih Chen
pc@zonatech.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Time simulation of a nonlinear aerodynamics model (NA) developed at Virginia Tech coupled with a nonlinear structure model (NS) is proposed as a design/analysis methodology for highly flexible HALE/morphing aircraft. With this nonlinear aero-structure (NAS) approach, large structure deformations and static/dynamic aeroelastic responses of such flexible aircraft can be properly accounted for including all dominant linear/nonlinear effects. The vortex dynamics coupling and spline procedure in NAS render it an ideal tool for expedient time simulations. The proof-of-concept example demonstrates the validity of the NA model and its aeroelastic applicability to a HALE flying wing in an open and closed loop control environment. Pathfinder/Helios flying wing will be selected as the candidate NAS feasibility study case. Further, ZONA Technology will integrate this methodology into an user-friendly, open-architecture software with a highly modular format using the ZONA Database Management (ZDM) system. Phase I effort will focus on the NAS for wing-only configurations. Phase II will enlarge our scope to include modules in time-domain gust, NAS-aeroservoelasticity, and interfacing with commercialized nonlinear structural FEM, and to increase the geometric complexity for wing-body and realistic aircraft configurations. The ZONA team intends to work closely with NASA and AeroVironment throughout these phases.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A truly nonlinear time-domain aeroelastic/aeroservoelastic tool for highly-flexible/morphing vehicles is still non-existent at NASA/Dryden. The proposed ZAERO-NAS software can perform expedient time simulation to account for large structure deformations and aeroelastic responses of actual HALE type aircraft. It is also an ideal diagnostic/analysis tool for the current NASA projects in Helios. ZAERO-NAS will support flight-tests to dramatically reduce the risk during flight of unexpected instabilities induced by dominant linear/nonlinear aeroelastic effects. The proposed software will be especially valuable during flight tests to the next-generation of HALE aircraft, future RevCon designs and to assist the health monitoring of flexible structures.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed nonlinear aero-structure (NAS) will be integrated with ZAERO to enhance its technical capability and commercialization standing. This unique ZAERO-NAS software can be used for design/analysis of wide classes of aerospace vehicles ranging from HALE aircraft, Joint-wing aircraft, SensorCraft, UAV/Predator, Airship/CargoLifter (all with flexible structures large-scale design) to morphing aircraft. Potential customers include the R&D/Research arms of DoD, Government and private aerospace industry, as well as the ZONA software/ZAERO users. With ZONA's user/customer network, marketing ZAERO-NAS should be relatively easy. ZAERO-NAS also has its market place in civil and auto industries for the designs of bridges/ buildings and cars.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Alex Sang
vogtw@lunainnovations.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Fiber optic sensors are rapidly emerging to replace conventional electrical-based sensor instrumentation in specific applications where small size, low mass, multiplexing capability, and high temperature resistance is a requirement. The advantages offered by state-of-the-art fiber optic sensors are particularly important for flight testing applications where the extremely low-profile geometry of a hair-thin Fiber optic sensor permits precise measurements of pressure, temperature and skin friction with minimal intrusion into the flow field. Luna innovations propose the design of a miniaturized, co-located temperature, pressure and skin friction sensor for point distributed transonic flow measurements during aircraft testing. Luna will also work on demodulation hardware and algorithms to improve output accuracy and reliability in a flight environment. During Phase I, Luna proposes to leverage previous experience in the development of combined pressure, temperature and skin friction sensors previously developed and investigate the feasibility of miniaturizing and ruggedizing these transducer assemblies to make an integrated sensor package that is simple to install, cost effective and is compatible with the harsh aircraft environment.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The sensor package will enable NASA engineers to accurately measure multiple, co-located environmental and aerodynamic parameters during flight test applications. A spatial distribution of the sensor package over the test area will enable surface mapping of the measurands which, when correlated to flight events, will facilitate determination and correction of undesirable performance characteristics. The high accuracy data obtained will enable improvement of computational fluid dynamics (CFD) flow simulation codes leading to further reduce test times and overall cost savings.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
In addition to NASA's need for a high-performance integrated sensor for flight test applications, there is a large commercial market for such devices for wind tunnel test applications, sub-sea flowline design and analysis, transportation system design, development and operation. The technology can also be used in commercial jet engines, automobile engines and in power generation and monitoring systems for nuclear and full-cell technologies. Government agencies such as the Air Force, DARPA, Navy and the DOE are potential end users of the miniaturized, integrated sensor.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Chiman Kwan
ckwan@i-a-i.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Intelligent Automation, Incorporated (IAI) and its subcontractor, Penn State U., propose a novel system to detect damage in aircraft structures. The system combines novel TFT based thin film actuators and sensors for signal acquisition and a robust software for fault prognosis and diagnosis. The actuator/sensor is known as PVDF-IDT (Polyvinylidine Fluoride Interdigital Transducer) that is integrated into a TFT switching circuit. It is low cost, compact, flexible, and has great potential for wireless interrogation. PVDF-IDT sensor has been proven to be useful for sensing cracks in rivet holes as well as other structural defects such as corrosion, delamination, and fatigue cracking. The second element of the system is an automatic fault prognosis tool, which consists of Principal Component Analysis (PCA), Learning Vector Quantization (LVQ), and Hidden Markov Model (HMM). PCA is a popular neural network tool for extracting useful features. LVQ is used to generate the code sequence. HMM has been proven to be extremely useful in several applications, however, HMM is used here to perform both fault prognosis and diagnosis. Our proposed system can perform continuous monitoring of aircraft structures in both ground and in-flight situations, and the sensors can be easily embedded into the structure.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed approach will be useful for in-situ monitoring of many NASA aircraft and spacecraft. The ability to predict the onset of structural failures is critical for reducing cost and improving safety in aircraft. At the end of Phase 2, we will have a system with both hardware and software for structural failure prognosis and diagnosis. The system will perform continuous monitoring of aircraft structures in both ground and in-flight situations.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed system can be useful for commercial aircraft as well as military aircraft in the Navy, the Army, and the Air Force.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Thomas W Carpenter
tcarpent@calpoly.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent success of an annular aerospike flight test by NASA Dryden has prompted keen interest in providing thrust vector capability to the annular aerospike nozzle (AAN). The AAN with a moveable spike could provide a solid-fueled rocket with thrust vectoring and unique throttling capability.

Cal Poly, which has a thrust vector research facility, has teamed with Rolling Hills Research Corporation, with CFD capability, to experimentally and analytically determine the optimal approach to thrust vectoring and throttling the AAN.

In Phase I a scale model AAN will be fabricated to include a movable spike that can be displaced and/or gimballed. One set of studies with this model will examine thrust changes as a function of spike position. Other studies will examine the thrust vectoring effectiveness of vanes at two positions: side of the spike and outer edge of the annular throat. Nozzle exhaust flows will be photographed using color Schlieren techniques in order to validate CFD analysis.

The most promising of the nozzle configurations for thrust vectoring and throttling will be selected from Phase I results. In Phase II, the selected configuration will undergo extensive laboratory testing and computational analysis for optimization. The objective of Phase III will be flight test.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
In the near term, aerospike nozzles with optimal thrust vector control would provide added safety and improved capability to the NASA Dryden Aerospike Rocket Test project, as well as economic benefit through the reuse of nozzles. Thrust vectoring and throttling capabilities would provide control of flight regimes (speed, angle of incidence, transients, and other flight conditions). In addition, flights with thrust vector control would have less dispersion and therefore could be confined to a smaller test area, which would improve range safety.

An aerospike nozzle with thrust vector control would be appropriate for future NASA single-stage-to-orbit programs.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Now, in the early 21st century, we stand at the threshold of commercial access to space. In the future, single-stage-to-orbit (SSTO) reusable launch vehicles (RLV) will provide relatively inexpensive and widespread commercial access to space. Due to their inherent altitude compensation, aerospike rocket nozzles are ideal for SSTO vehicles. A self-contained aerospike nozzle with thrust vectoring and throttling capability would provide a practical, cost-effective means of controlling the rocket flight path for such vehicles.

Commercial applications for relatively inexpensive SSTO RLVs are virtually unlimited, but certainly include the economically significant small satellite launch business.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Tom Sherwood
tom.sherwood@kalscott.com
3226 SW Timberlake Ln.
Topeka, KS 66614-4515
(785)979-1113

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The need for aerodynamics-based efficiency enhancements for air vehicles is presented. Concepts are presented for morphing aircraft, to enable the aircraft to optimize its configuration for various flight regimes. Using simulations, wind tunnel testing, and benchtop hardware development, the feasibility of the concepts will be established in Phase I. In Phase II, flight testing will be performed to refine and finalize the designs. The concepts involve tailoring of the wing using adaptive surfaces to acheive drag reduction. This translates to benefits in range, endurance, manueuvering and speed characteristics of the air vehicle.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
These innovations can be applied to several NASA subsonic aircraft, including manned and unmanned platforms. Some of the work here can be extended to gust alleviation for high altitude UAVs as well. This STTR effort complements other work underway at NASA in the areas of adaptive aircraft, morphing aircraft configurations, robust controls, and intelligent aircraft.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Efficiency enhancements for commercial and private subsonic aircraft, tactial and long endurance UAVs (for military, homeland security and science applications), morphing aircraft technologies.

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This STTR Phase I effort proposes to develop an innovative, affordable processing route for larger-sized shape memory alloy (SMA) components. Despite significant advances over the last decade, innovative, cost-effective shape processing techniques yielding controlled microstructure-properties are still needed for SMA's. An advanced reactive metal casting technology is applied in this project to manufacture SMA's. Casting offers a relatively low-cost approach for fabricating near net-shape components, and would allow for widespread acceptance and application due to its cost-effectiveness.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Potential NASA commercial applications include aeroengine and airframe structural components, particularly those requiring impact resistance. SMA's are also being considered for flexible wings for aircraft.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Potential non-NASA commercial applications include building structural components, armor applications, automotive and land vehicle components and structures, shipboard structures, sporting goods, and biomedical implants. Essentially, a practically limitless list of potential applications could be made if large-sized SMA components can be manufactured affordably.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Said Jahanmir
sjahanmir@mitiheart.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Fuel cell air handling systems require clean and contaminant-free inlet air, which dictates that oil-free, motorized, compressor/expander systems should be used. Although there is no sliding contact in the steady state operation of the foil bearing, occasional contact between the foil and journal surfaces at startup and shutdown and during overload situations, could limit the bearing life. Therefore, to ensure that the compressor system is highly efficient and reliable the foil air bearings need wear resistant, low friction coatings.

The objective of the proposed STTR investigation is to identify new coatings for use in fuel cell propulsion compressor bearings that would allow the foil bearing to be functional from low temperature start-up conditions to the maximum temperatures encountered during operation. The proposed program will build on a novel hydrogenated diamond like carbon (DLC) coating developed at the Argonne National Laboratory (ANL). The goal of this joint MiTi^REG and ANL STTR Phase I program is to demonstrate the feasibility of ANL hydrogenated DLC and MiTi^REG KorolonTM coating technology for fuel cell propulsion compressor bearings. This will be accomplished through coating adhesion and tribological testing of the coatings against various potential shaft coatings such as the NASA developed PS304 and/or Korolon 1350B.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A direct application for the proposed foil bearing coating system is NASA's Propulsion and Power Project that focuses on ensuring the long-term environmental compatibility and efficiency of aircraft propulsion and power systems. This NASA Program seeks to demonstrate key component technologies to enable electric and hybrid propulsion and power systems. An oil-free compressor system is an enabling technology for the fuel cell system. Potential NASA applications include foil bearings for the Aerovironment/NASA solar powered Helios and other oil-free foil bearings for other high altitude UAVs or auxiliary power unites used for long duration observation.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
There are significant opportunities in the automotive transportation sector and industrial compressor and blower markets for oil-free compressors. For example, Samsung is now buying foil bearings from MiTi^REG for their TurboMaster Micro Compressors in lot sizes from 50 to 150 sets. Growth to over 300 sets per year are anticipated. We have also recently been approached by a blower and compressor manufacturer requesting a proposal to support their development of a family of oil free compressors and blowers in the 10-15 HP range. Projected volumes for these applications are in the tens of thousands per year. In addition, a substantial number of proposals are outstanding for development of commercial products using MiTi^REG foil bearings. Included in this list is a proposal to develop the air handling system for aerospace fuel cells, a proposal to supply foil bearings for automotive fuel cell compressors for both domestic and international fuel cell manufacturers.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Paul W. Rehrig
paul@trstechnologies.com
2820 East College Ave Suite J
State College, PA 16801-7548
(814)238-7485

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
TRS Technologies, Inc. in collaboration with The Pennsylvania State University propose to develop new families of high temperature piezoelectric materials for adaptive engine control. The identification, synthesis and characterization of these new materials will enable the design of new high temperature piezoelectric active flow control actuators that may enable dramatic increases in the efficiency of revolutionary alternative propulsion system concepts or the concept designs themselves. Specifically, the objective of the program is to identify materials for high authority (d33 ? 400 pC/N) piezoelectric actuators for fuel flow control in gas turbine engines. The high strain, high force actuators will be operational in the range of 600?1200^oF with 1 to 10 kHz capabilities. This will be achieved by synthesizing new piezoelectric in both textured ceramic and single crystal form. The focus will be to use cost effectives methods to produce either textured microstructures or single crystal materials that lend themselves to domain engineering for enhanced piezoelectric performance at elevated temperatures.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The identification, synthesis and characterization of these new materials will enable the design of new high temperature piezoelectric active flow control actuators that may enable dramatic increases in the efficiency of revolutionary alternative propulsion system concepts or the concept designs themselves. Specifically, the objective of the program is to identify materials for high authority piezoelectric actuators for fuel flow control in gas turbine engines. Other NASA applications of interest include high temperature accelerometers, sensors, and vibration sensors.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
There is a broad range of applications that can be greatly improved through use of the textured ceramic and converted ceramic technology discussed in this proposal. Accelerometers and vibration sensors require a high degree of property stability with temperature and there are many industrial and aerospace applications that require increased operating temperature. Also, there are a broad variety of actuator and sensor applications, particularly in the area of smart structures (vibration control, structure morphing) for aircraft, watercraft, and automotive applications that could benefit from increased operational temperature and/or improved temperature stability.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
James Canniff
canniff@rmss.us
P.O. Box 1092
Barnstable, MA 02630-0001
(508)362-9400

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The technical objectives for the proposed Phase I study are:
1.Develop a compact, dual-wavelength antenna system capable of electronically scanning or producing multi-beams at different incidence angles, conical scanning and generating matched beams at both wavelengths.
2.Determine the optimal frequencies for the dual-wavelength operation that balances resolution, sensitivity, atmospheric attenuation, sea clutter contamination, size and weight. This will include conducting a brief literature review to select a model or develop a model for simulating the radar response to precipitation as a function of frequency and for a range of precipitation rates. Simulation will likely be based on Mie/Rayleigh scattering and attenuation models using a Gamma drop-size distribution shape.
3.Develop a compact, power efficient dual-frequency transceiver design that is based on surface mount RF components and low-noise monolithic microwave integrated circuits (MMICs) receivers. While custom MMICSs are available from several vendors, RSS and UMass will develop the low frequency RF and digital circuit board designs.
4.Investigate and develop compact, low-voltage power amplifier designs to produce high average power linear transmit signals. Design will need to operate unpressurized at the high altitudes typical of the Global Hawk UAV and similar aircraft.
5.Develop advance remote sensing algorithms to interpret the unique sampled data from the proposed instrument and retrieve high resolution maps the ABL winds, precipitation and ocean surface winds within tropical cyclones.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The innovations and designs of the proposed phase I effort will enable the construction of a full prototype, a Wind and Precipitation Scanning Radar for UAV deployment, in a phase II. The designs for, and data collected on, the antenna, transceiver, amplifier and procesosr will be essential to reduce the risk and ensure the success of this phase II effort. This novel sensor network can then be used in NASA research programs aimed to support the NASA TRMM and GPM missions and other precipitation focused programs such as the NASA CAMEX efforts.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
None

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Hao Chen
wulinghui@yahoo.com
2817 Cascade Falls Dr
Austin, TX 78738-5347
(512)263-8659

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The STTR Phase I proposal aims to develop innovative device concepts and fabrication techniques that enable the construction of high-performance uncooled long-wave infrared (LWIR, 8-12?Ym) photodetectors. LWIR photodetectors are of great importance in real-time acquisition of radiation characteristics of the Earth and its environments for understanding and predicting the Earth's climate and potential hazards. Quantum dot infrared photodetector (QDIP) technology offers an excellent choice for LWIR sensing due to its superior performance, including high temporal resolution (<1 ?Ys) and low noise equivalent temperature difference (NETD <10mK). However, existing QDIP technology requires cryogenic cooling to reduce dark current, which substantially increases size, weight and power consumption. Because of this, the proposed research aims to develop innovative device concepts and fabrication techniques that can substantially reduce dark current, thus allow the construction of uncooled QDIPs. The uncooled QDIP technology enables high-performance LWIR detecting on a chip with significantly reduced payload. It is highly desired in many Earth science applications. The Phase I work will perform feasibility investigation of the proposed device concept, optimize quantum dots growth and annealing techniques and produce a preliminary design for a prototype system that can be built and demonstrated in Phase II with a NASA supplied platform.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed QDIP is especially useful for a number of potential NASA applications, including:
(1) Real-time high-throughput, high definition acquisition of radiation characteristics of the Earth and its environments: The thermal-emission data provide critical information for understanding and predicting the earth's climate and potential hazards. The avoiding of large mass of cryogenic systems significantly reduces payload and power consumptions.
(2) 3-D Robot Vision: 3d imaging and motion sensing for docking and robot-assisted assembly; Robot vision for micro-spacecraft, surface lander and rovers for planetary exploration.
(3) Lidar remote sensing: topographical profiling and monitoring of atmospheric variables such as temperature, winds, and trace constituents providing landing site characteristics

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The ultra-sensitive, room temperature and spectral tuning capabilities make the proposed technology particularly useful in many Non-NASA applications requiring ultra-sensitive and standalone, including:
(1) Night Vision
(2) Ultra-sensitive missile early launch detection and high-speed trajectory tracking with non-false alarming
(3) Continuous and standalone chemical and biological hazard detection
(4) High definition three-dimensional medical imaging and reconstruction

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Xiuhong Sun
xhsun1@aol.com
One Parker Street
Lawrence, MA 01843-1548
(978)327-6599

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A Web-based Airborne Remote Sensing Telemetry Server (WARSTS) is proposed to integrate UAV telemetry and web-technology into an innovative communication, command, control, and computer-network (C4) system for operational UAV remote sensing. WARSTS integrates two innovative subsystems: the Tracking Antenna Radio Link (TARL) and the Web-based Application Support System (WASS). TARL serves as the sensor gateway to WASS. It links a remotely deployed airborne sensor platform and ground control equipment by a high-speed peer-to-peer Wi-Fi link. TARL monitors airborne instruments and UAV operation status continuously while performing selective imaging data transmission. WASS processes the structured UAV platform position/attitude and imaging data and makes them visualizable through an integrated web-enabled application package in realtime. WARSTS features the following capabilities: (1) a realtime sensor fusion algorithm that combines inertial, GPS, magnetometer, and other sensor input to deliver precision airborne platform state vectors at a rate greater than 50 Hz; (2) a set of visualization tools that automatically generate the mapping area mosaic of the remote sensing UAV along with its 3D flight through animation; (3) human-UAV instrument interactive control; (4) hotspot realtime hyperspectral/multispectral data download; and finally (5) a fully featured web-based connectivity solution that speeds up information delivery.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The final WARSTS product deliverable to NASA is a suite of innovative web-enabled telemetric instrument control, data acquisition, and application support tools with a portable tracking antenna system for UAV Remote Sensing. WARSTS will be initially implemented to support NASA GSFC's Airborne VNIR and SWIR Imaging Spectrometer (AVSIS) and/or other UAV hyperspectral/multispectral instruments. The C4 enabled WARSTS will not only support sophisticated operations required for deployment of these instruments but also speed up data processing and information delivery. These are valuable to NASA UAV remote sensing commercial applications including satellite calibration and new application development.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The commercial product combines a suite of innovative communication, command, control, and computer-network (C4) capabilities in an integrated system for operational manned and unmanned aerial vehicle, blimp, and balloon remote sensing. With real-time interactive remote sensing platform monitor and control, data downlink, and data processing, distribution, and visualization through the web-enabled information-processing pipeline, rapid and lower-cost delivery of remote-sensing/GIS solutions becomes feasible. The potential commercial market of WARSTS includes homeland security, forestry and park services, precision agriculture, crop growing status monitoring, disaster response and management, surface pollution detection, land-use surveys, and environmental monitoring, design, and management for urban planning.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
J Ari Tuchman
ari@technoventures.com
17 Saddlerock Court
Silver Spring, MD 20902-1611
(301)593-8002

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of the proposed work is to develop a multi-color imaging array capable of simultaneously detecting radiation in either the UVa (400-320nm) and UVb (320-290nm), or UVa (400-320nm) and UVc (290-100nm) wavelength bands. This will be the first such device ever fabricated. Imagers of this type can identify and track rocket trajectories even in bright sunlight. Many types of camouflage material are transparent in the UV, allowing for ordinance detection beneath camouflage. Earth resource management (crop data acquisition and weather prediction) will also benefit from this activity. Our research team has fabricated a single-color GaN imaging array. We found that bright solar radiation does create a significant background signal that makes missile plume identification difficult. The solar spectrum provides well-defined intensity ratios of UVa, UVb and UVc radiation. Sensing simultaneously in two of the three bands allows for rejection of signals with the solar ratio signature. This significantly reduces the possibility of registering false positive alarms.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
There are two important commercial applications deriving from the proposed work: solar weather prediction and earth resources management. UV studies of the sun are of critical importance in determining sunspot activity and its impact on terrestial communications. UV images of the earth are routinely used in crop surveys as well as in geological data base generation.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Rocket plume detection and camoflauge penetration.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Xiucheng Wu
xiucheng.wu@atoptics.com
18007 Cortney Court
Industry, CA 91748-1203
(626)581-3755

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this STTR project we will address the radiation hardness issues using radiation hard (RH) materials. We will based on the RH material to develop our photon counting APD device structure and grow and fabricate high-quality devices that can achieve high sensitivity, high uniformity, low dark counts, and fast and small after-pulse dark current. We will further utilize our high quality guard-ring and backside lens techniques to develop reliable, high uniformity, 2-D, APD arrays with near 90% fill-in factor for the detection area coverage.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
High performance avalanche photodiodes (APDs) and arrays in the 1064 and 1300-1550 nm wavelength ranges are very important components for lidar remote sensing applications and satellite-to-satellite or satellite-to-ground optical communications. 1064 nm Nd:YAG lasers are the most important and dominated laser sources for remote sensing. For the longer wavelength APD applications, eye-safe factors are 70 (1300nm) to 100 (1550 nm) times better than their counter parts working at the 850 nm wavelength regions.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
For the military and commercial applications, APD can be used for range finder systems (military and commercial), free-space optical communication systems, high-speed fiber optic receivers, ?etc. An APD receiver can have higher receiving sensitivity, which can increase the margin of system power budget and allow a better performance with lower cost. For example, it allows a longer distance in a range finder or a higher number of signal (fiber) splitting, in a fiber distribution system.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Hailiang Zhang
zhang@sci-sol.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A tunable dye laser for Lidar detection will be fabricated based on the innovative dye-doped Holographic Polymer Dispersed Liquid Crystals (HPDLC) technology. The demonstration of the tunable lasing of dye-doped holographic polymer dispersed liquid crystal is the main focus during the Phase-I research, while the commercial tunable-laser product will be realized in Phase-II.

By carefully choosing the materials including liquid crystal, UV-polymerizable monomer, emitter dye and optimizing the holographic-writing process, dye-doped HPDLC is formed as an one-dimensional photonic bandgap material, Mirrorless Lasing in the dye-doped HPDLC occurs at the reflection band edges. Applied voltage tunes the reflection peak of the HPDLC as well as the center wavelength of emitting laser. The whole laser device is solid state and highly resistant to shock and vibration as it has no moving parts. Since the innovative laser device is based on the thin film technology, there is no bulky laser cavity and the cost of the HPDLC thin films are low due to easy-to-achieve large scale manufacturing. The unit price of the HPDLC thin film can be so low that it is economical to throw away and replace a HPDLC thin film device once the dye reaches the end of its life.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This innovative tunable laser has applications in LIDAR, atmospheric sensing and planetary exploration when wavelength agility is required. The proposed tunable laser is especially useful for on-orbit LIDAR systems, either as a seed laser for a more powerful laser or as a primary laser when replicated in a stack, for example mapping planetary surfaces because of its great advantage of small size, low weight and shock/vibration resistance. Such a small laser could be used on surface rovers enabling surface Raman spectroscopy and LADAR mapping.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed tunable laser also has application in hyper-spectral medical imaging and bio-imaging where different color signals the biochemical makeup of different regions of tissue, nuclei, cytoplasm, etc. Additionally this laser can be used to create inexpensive and perhaps disposable Raman sensors and imagers for use in the biological, medical and chemical sensing markets. In addition, this innovative tunable laser will bring a great improvement in high quality laser display with merits of high color purity and high light intensity. Its role as a tunable signal source in optical communication such as Wavelength Division Multiplexing (WDM) is another commercial application.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Stephen D Vining
viningsd@crgrp.net
2792 Indian Ripple Rd.
Dayton, OH 45440-3325
(937)320-1877

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Astronomers strive to see farther and farther into the cosmos. These increased observation distances will gain access to a wealth of information that will enable a better understanding of the universe, and the origins of Earth. To gain these distances larger aperture telescopes are required. Current materials and fabrication processes for space-based mirrors have serious drawbacks that severely limit the size and therefore the performance of optical systems for imagery. These drawbacks fall primarily into the areas of mass properties, structural properties, thermal properties, and fabrication costs.
Cornerstone Research Group, Inc. (CRG), proposes to develop a composite material system that will address the drawbacks of conventional materials and fabrication processes for space-based mirrors. This novel composite system will integrate syntactic materials (see background Section 2.4) with electroformed nickel foils to achieve a balance of mass, structural, thermal, and optical properties that dramatically advances the state-of-the-art for space-based mirrors. The composite material will also enable fabrication techniques that are faster and cheaper than current practices.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Supporting NASA's Goddard Space Flight Center, this project's technologies directly address requirements for lightweight materials for larger space-based imaging systems, especially UV mirrors and LIDAR telescopes. This project's technologies offer dramatically reduced areal density, while maintaining high optical surface quality and dimensional stability.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Government systems (especially MDA and other DoD) that would derive the same benefits would include but not be limited to space-based imaging systems (for surveillance and other remote sensing); space-based, missile, and airborne weapon systems (in optics for target detection, designation, or illumination); and optical communication systems.
This technology's attributes for telescope mirrors should yield a high potential for private sector commercialization for high-end research observatories and consumer-level telescopes or systems space imaging spacecraft by LANDSAT and SPOT.

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Biofilms are ubiquitous in the environment. Few surfaces resist biofilm formation, most promote it. Biofilm formation poses problems in water systems as they can clog pipes and pores, block filters, reduce heat transfer, and in general restrict flow. Their metabolic products can aid corrosion, even of stainless steel. In potable water systems, both their metabolic products and the bacteria or fungi themselves directly pose a health hazard. A space environment appears to be a particularly favorable one for biofilm formation. Cell cultures have shown far higher rates of growth in low-gravity environments. Space radiation seems to accelerate microbial growth and foster their mutation. Within a closed environment with many non-replaceable resources, prevention of biofilm formation is paramount. To meet this need, Agave BioSystems and the Universities Space Research Association, propose to develop carbon nanotubes (CNTs) and other nanostructures for the prevention of biofilm growth. In this Phase I, we propose to demonstrate that the use of nanostructured materials can prevent or inhibit growth of biofilms due to geometry effects and that they can also be functionalized with a biocide.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
On long-term space missions, waste water and recovery systems will be integral to closed loop life support. Air and water revitalization and recovery systems are susceptible to many microbes within each of these categories. Disinfection is neither complete nor applicable to all systems. Immediate needs include the condensing heat exchanger, both for its functional importance and health impact, and the water system currently in use on ISS. In these system and future systems, antibacterial surfaces could sufficiently contribute so as to reduce if not eliminate the need for such high levels of disinfectants.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Microbial biofilms on surfaces cost the nation billions of dollars yearly in equipment damage, product contamination, energy losses and medical infections. Conventional methods of killing bacteria (such as antibiotics, and disinfection) are often ineffective with biofilm bacteria. The huge doses of antimicrobials required to rid systems of biofilm bacteria are environmentally undesirable (biocides and environmental antimicrobials cost $1.2 Billion per year) and medically impractical (since what it would take to kill the biofilm bacteria would also kill the patient!). So new strategies based on a better understanding of how bacteria attach, grow and detach are urgently needed by many industries.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Kevin Zou
kzou@bostonati.com
150H New Boston St.
Woburn, MA 01801-6204
(781)935-2800

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In recent years there has been an increasing interest in the propagation of polarized light in randomly scattering media. The investigation of backscattered light is of particular interest since most medical applications aimed at the in-vivo characterization of biological tissue rely on backscattered light. By recording the spatially dependent response of a medium to a polarized point source, one may obtain information about the scattering particles that are not accessible to mere intensity measurements. In this program, Boston Applied Technologies Incorporated (BATI), together with the Catholic University of America (CUA) proposes an innovative NIR polarization imaging solution based on high performance fast tunable phase retarder and novel algorithm. It will have the ability to record both scattering images and Stokes polarization imaging. It allows very fast recording the polarization images at the speed limit of a CCD. It contains no moving parts and can accommodate to most of the existing CCD cameras. The unique measurement procedure allows efficient, accurate sensing of the polarization imaging. A computer-aided diagnosis (CADx) software will be developed for the proposed polarization imaging system.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Application of the proposed high performance polarization imaging system would find tremendous applications in NASA mission. The development effort of this program will result a space applicable instrument. Potential application of the proposed technology will allow microscopic imaging and biophysical measurements of cell functions, effects of electric or magnetic fields, photoactivation, and testing of drugs or biocompatible polymers on live tissues. The proposed portable device can also be a powerful and convenient tool for non-biological studies during the NASA mission.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The potential for this device in commercial clinical practice is also enormous, from early detection of skin cancers, to microscopic tissue analysis. It also can be used as an analysis tool for material research and industrial processing.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Anna K Stewart
astewart@nextgenaero.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NextGen Aeronautics, Inc. and their partner, Virginia Tech, propose to develop a self-healing material for wire insulation using a class of poly(ethylene-co-methacrylic acid) (EMAA) and poly(tetramethylene oxide) ionomer polymers. The self-healing property of these materials is strongly correlated with the thermal processes that occur during and after damage initiation. Recent experimental results have demonstrated that penetration of the polymer by a projectile causes localized heating near the puncture. The heating then causes a localized melt elastic response which serves to close the puncture and 'heal' the polymer.

Since self-healing has already been demonstrated using these materials, the major technical challenge of this STTR effort is to stimulate the localized melt elastic response that has been shown to initiate self-healing. Our concept is to incorporate a magnetically-response phase into the insulating polymer for the purpose of causing localized heating during high-frequency excitation of the polymer. This magnetic phase will be located close to the electrical conductor. Localized heating will cause flow into the crack and, upon cooling, the crack will close over the wire and eliminate the exposure of the bare wire.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Utilizing self-healing materials for wire insulation will have direct benefits to an array of NASA commercial applications. These include development of smart, low-maintenance commercial transport and business aircraft, the next generation of spacecraft and inter-planetary vehicles, as well as mission critical infra-structures such as launch platforms and complex support equipment.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Self-healing wire insulation materials will have wide-spread commercial applications wherever electrical power is utilized ? all kinds of automobiles, commercial buildings, homes etc. They could also be used in computer systems to improve reliability and reduce maintenance.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Brian O. Klinka
boknext@aol.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop a foundation for the Airworthiness Certification of the Personal Air Vehicle (PAV), This framework will recommend a model for Quality Assurance, consistent with the "consensus" based industry standards, and acceptable to the FAA.

Further, our focus will include the review of certain FAA Regulations (CFAR) that create economic barriers to entry to the aircraft industry for high-volume automotive manufacturers and to offer alternative concepts for certification that remove or reduce these barriers.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
It is NASA's intent for the PAV, program to identify the current baseline and research concepts, technologies and missions that enable faster and farther solutions for point to point air travel in the future.

In principle, NASA's goals include the utilization of technologies and manufacturing processes employed in mass production, in order to produce a vehicle affordable for personal transportation.

As a result of implementing the framework established by this investigation, and incorporating the "consensus" standards, the acquisition cost of the PAV can be significantly reduced. As the aircraft acquisition cost decreases, the PAV will become more affordable as a commercially viable means for public transportation of the future.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The framework for the Airworthiness Certification of the PAV, established as a result of this investigation, will provide a basis for future certification activities in the General Aviation industry.

Further, this approach will significantly reduce the non-recurring engineering cost associated with the typical approach to FAA Certification, as well as provide for reduction in the acquisition cost of the PAV, therefore making the PAV more affordable, and begin to compete with luxury automobiles as a means for personal transportation, enabling point to point transportation in the future.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Hans Neubert
hansn@pciaerospace.com
6051 Prado Street
Anaheim, CA 92807-3938
(714)998-2504

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation is a low aspect ratio all-lifting configuration for personal air vehicles. This configuration uses an architecture fundamentally different from conventional aircraft to achieve large reductions in cost and improvements in safety. The concept features an integrated all-lifting body that performs the functions of the wing, tail and fuselage of a conventional light airplane with a single, simple structure.

The integrated lifting body has an aspect ratio between approximately 1.0 and 2.5, and is deep enough to contain the crew and payload without a conventional fuselage.

A further innovation is the use of a faceted shape composed of flat panels. The faceting greatly simplifies the manufacture of the major parts of the airframe, further reducing cost.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Structural design technology for low-cost PAV airframes.

PAV research aircraft: A low aspect ratio all-lifting research aircraft would demonstrate technologies and a configuration that would dramatically reduce the cost of personal aircraft, and improve safety significantly over current-generation configurations

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Personal Air Vehicle: The configuration and structural concepts from this research could be used to develop an aircraft for owner-operated personal transportation that would be safer and lower-cost that current generation general aviation airplanes.

Light Sport airplane: The light weight and low wing loading of the low aspect ratio all-lifting configuration are well suited to meeting the requirements of the recently enacted "Light Sport Aircraft" regulations.

Utility Aircraft: The configuration offers the combination of large internal volume and short takeoff and landing distances.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
John A. Violette
aciprops@aol.com
49 CAMBRIDGE HEIGHTS
KENSINGTON, CT 06037-2310
(860)829-6809

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ACI proposes a design for a Propulsor (Low Cost/Low Noise Variable Pitch Ducted Fan) that has wide application in all sectors of Aviation. Propulsor hardware of this low cost design can be integrated with a broad range of aircraft engines (e.g. existing piston engines, automotive derivative piston engines, new design turbine engines) for use in new design aircraft.

The proposed Propulsor design will incorporate known acoustic design features that support low noise aircraft operation. These features include the use of duct acoustic liners, attenuating harmonic stator vane and rotor blade configurations, and duct designs that direct/condition the exhaust air stream to minimize noise heard by individuals on the ground during aircraft takeoff, landing, and fly-over.

The proposed Propulsor design makes possible the fabrication of low cost and low weight variable pitch fan blades and rotors. The new composite blade/retention design avoids the need for heavy and expensive ball bearings and other complex hub pitch change mechanism components.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
ACI's proposed Propulsor (Low Cost/Low Noise Variable Pitch Ducted Fan) design makes possible the manufacture of low noise and low cost aircraft propulsion systems. The Propulsor design implementation in personal air vehicles (PAV) will make possible compliance with growing low noise restrictions. Importantly, the low cost Propulsor design will help NASA meet its PAV cost targets. This will help pave the way for high volume PAV aircraft sales in the future and realization of the NASA PAV/GA vision.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
ACI's proposed Propulsor (Low Cost/Low Noise Variable Pitch Ducted Fan) design has wide application in Aviation beyond just General Aviation. In Military Aviation, the ACI design low cost Propulsors are particularly well suited for applcations such as in VSTOL vehicles (e.g. twin counter rotating ducted lift fans, UAV vehicles where low noise signature is critical to mission success, and helicopter tail rotors. In Commercial Aviation, the Propulsor low cost design can be used for fans in turbofan engines such as the ADP (Advanced Ducted,

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
James Patterson
jamesp@hypercompeng.com
1080 North Main Suite #2
Brigham City, UT 84302-0505
(435)734-1166

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The intent of this proposal is to develop key building block technology for lightweight composite structures suitable for cryogenic fuel depot storage as well as human in-space habitat. The effort will incorporate and expand on previous work by the participants in the cryogenic performance of composite materials as well as improved impact technologies for micro-meteor/space debris survivability. It will then develop radiation resistant capabilities.

In order to develop reliable composite structures for use as cryogenic fuel storage, human habitation, or other mission critical application a solid understanding of constituent material environmental capabilities is required. While good progress has been made in expanding the knowledge of how composite fibers and matrix systems (resins) react to loads and strains at extremely cold temperatures little to no effort has been made to incorporate radiation exposure such as would be encountered with in-space fuel storage depots.

With a view to developing dual-use lightweight composite structures the proposed effort will develop improved composite material resistance to the harsh radiation environment a spacecraft would be expected to encounter during the life of its mission. Our intent is to develop robust light weight composite structures which are cryogenic capable as well as impact and radiation resistant.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
NASA applications for the technologies we propose researching and developing would be light weight composite structures that could be used for reliable and safe cryogenic propellant (i.e. fuel depots) storage, radiation resistant/shielding human habitat structures, and robust structures and tankage capable of withstanding micrometeroid and space debris impacts while also being radiation robust.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The commercial pressure vessel industry is always hungry for improvements in performance (i.e. weight) and safety. There has been some significant discussion on the usage of cryogenic pressure vessels for efficient gaseous fuel storage, particularly with regard to the transportation of large volumes of gaseous fuels such as CNG.

The improvement in environmental robustness of cryogenic capable light weight pressure vessels will be noted by the commercial industry and this technology will be incorporated into specialized application.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Dean Baker
stbaker2000@cs.com
10010 cucklebur Circle
Houston, TX 77095-0001
(281)256-7636

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of this STTR is to determine the capability of Net Shape LENS processing with Nano-coated powders. The unique composites produced using regualr processing and these powders ahs provided unique material properties. The use of nano-coated powders witht he rapid prototype LENS process should also provide unique data.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Applications for the LENS are in low production net shape componenets. For many NASA programs which only make one or two components this system could be invaluable. The ability to provide quick components of various materials systems would be helpful on all exploration programs. If higher properties are achieved during the rapid cooling proces than more appliations will benefit from these new materials.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Coomercial appliations include automotive, aerospace, thermal control areas, electronics to name a few.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Timothy N McKechnie
timmck@plasmapros.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Revolutionizing the space propulsion industry through innovative, relatively low-cost, manufacturing techniques is extremely needed. Specifically, advancements are needed for components in new high-powered electrical, beamed energy, and nuclear propulsion systems. Innovative processes for fabricating large, net shape, nanostructured tungsten-rhenium components are proposed. Innovative liquid precursors, tungstic acid and perrhenic acid, will be used in conjunction with powders. Vacuum Plasma Spray parameters will be developed to deposit nanostructured W-Re material. The techniques will then be used to fabricate samples for microstructural characterization and tensile testing. After optimization, non-eroding throats will be fabricated and hot fire tested at ATK/Thiokol at no cost to the Phase I effort. Tungsten is being used for its high melting temperature and chemical stability, and rhenium is used to improve ductility. The ability to fabricate nanostructured tungsten-rhenium components to net shape will revolutionize the ultra high temperature materials industry.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Rocket engine components will be developed for nuclear, electrical, beamed energy, and chemical propulsion. Other NASA applications are arc jet thrusters, heat exchangers, welding electrodes, nuclear power and propulsion components, crucibles, cartridges, heat pipes, etc. Non eroding solid rocket nozzles meets one of the IHPRPT goals.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Commercial applications are for solid and hybrid rocket nozzles, high powered electrical contacts, X-ray targets, heat pipes, crucibles, fuel cells, valves, nuclear power, furnace parts, armor penetrators, heat shields, sputtering targets, and other high temperature applications.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Manju Singh
msingh@amseta.com
3604 Townehouse Drive
Coram, NY 11727-2842
(631)355-2371

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This STTR Phase I project will establish the feasibility of an innovative manufacturing process to fabricate a range of unique hafnium/silicon based carbide composites and material systems that cannot be processed using conventional techniques. These materials are expected to have a host of unique mechanical and thermal characteristics making them highly suitable for ultrahigh temperature aerospace and commercial applications. The manufacturing technique offers a viable, low-cost, environmentally friendly, and highly flexible processing technology that can also be used to generate various material forms (fiber reinforced and graded structures) and complex, net-shape components. In addition to the primary feasibility tasks, the Phase I effort will also quantify mechanical and thermal properties, and oxidation resistance characteristics of the processed materials, as functions of composition and microstructure. This will serve to guide the identification of specific applications for the fabricated materials. Phase II activities will expand the initial effort to demonstrate the use of these materials for structural elements by refining the processing technique, developing other material systems, and fabricating structural components that incorporate graded and fiber-reinforced morphologies. In conjunction with the STTR effort, we will pursue a commercialization plan that involves specific collaborations with commercial partners and end-users.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Our novel ultrahigh temperature materials offer the potential to meet high-performance goals at significantly lower weight, while simultaneously improving safety by operating with a higher margin between design temperature and material upper use temperature. These materials are expected to have broad impact on a host of applications within NASA's Next Generation Launch Technology (NGLT) Program. Aerospace applications include rocket propulsion components, single stage-to-orbit vehicles and hypersonic leading edges. Our flexible fabrication technique could also be adapted for processing solid nuclear fuels and in-core materials for Prometheus and land-based nuclear programs.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Commercial applications of our materials are in the power generation, transportation and process industries. These materials could be used to improve the performance of air-breathing engines, resulting in lower emission and higher cycles efficiency. Other applications include high-speed machine tools, high temperature furnaces, and process equipment for molten metal processing.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Daniel A Greisen
dag@sierraengineering.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The pace and cost of developing an engine system for future explorations is strongly influenced by the inadequacies of design tools and the supporting databases. The inability to predict the internal operating environments of a combustion chamber during the design process necessitates design iterations during the development process. NASA and the Department of Defense are working to increase the fidelity and accuracy of the tools used during the design process to define these internal operating environments. Key to the development of advanced analysis tools is appropriate validation data of adequate fidelity. The goal of this STTR is to develop a comprehensive hot-fire liquid-rocket engine test database that is appropriate for the validation of advanced two and three-dimensional computational fluid dynamics (CFD) models and the anchoring of lower-fidelity analytical design tools. The initial focus will be to generate high-quality data on wall heat flux, axial energy release and exit-plane species concentration distribution.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
These data are needed by NASA, their engine contractors and model developers to evaluate, validate and improve analysis tools, especially computational fluid dynamics (CFD) models. The data generated by this STTR is at relevant rocket engine operating conditions. The injector and chamber concepts offer simple geometry and clean boundary conditions. The parametric film cooling and injector performance data generated as part of the Phase II effort will be invaluable during the development of booster, upper stage and in-space engines. NASA has initiatives to improve CFD tool prediction reliability and robustness. These data will directly support improvements in Simulation Readiness Level.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Film cooling is an essential component in all engine designs, even those that employ regenerative cooling jackets, as it enables management of the gas-side thermal environment. The USAF Upper Stage Engine Technology (USET) program is focused on tool development and validation. This data will have a direct impact on the USET program. The DoD plume phenomenology community is intensely interested in film cooling effectiveness, exit plane measurements and their relationship to engine operating characteristics. The high fidelity data collected in this program is useful for the validation of CFD codes that include chemical reaction.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Neeraj Sinha
sinha@craft-tech.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The innovation is the systematic "building-block" validation of CFD/turbulence models employing a GUI driven CFD code (RPFM) and existing as well as new data sets to be generated in this proposed program. Unified ke and algebraic stress (EASM) turbulence models, shown to adequately simulate fundamental high-speed jet data sets and now being validated with PIV data sets in a NASA Glenn program, will be used. These jet turbulence models will be improved to provide agreement with base region data for cold air data sets. Hot jet base region data sets are not readily to evaluate Prandtl number models affecting base heating. Inadequacies pose major issues with regard to analyzing base regions of rocket motors. A key innovation is to obtain high speed, hot jet base region data sets in the new, U.Miss/Oxford 12" quiet tunnel facility using advanced diagnostic techniques, extending the hot, supersonic jet data of Seiner. In Phase I, consistent modeling of cold flow base region data will be achieved, and, the hot jet base region problem will be initiated. This innovation fills a major gap at NASA improving upon base region simulation capabilities required for launcher design aerothermal predictions.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed effort is directly supportive of NASA's activities related to the design. testing and flight certification of future generations of space vehicles. Specifically, to accurately develop thermal protection systems and establish base heat shield requirements will require a basic understanding of the physical mechanisms governing radiative and convective heat transfer resulting from the plume aerothermal environments. The proposed simulation tool, that will be well-validated against test-data, will play a crucial role in supporting production-oriented analysis relevant to design optimization, definition of test procedures, supporting launch requirements and test data interpretation

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The base flow modeling capability development is directly applicable to major DoD initiatives of current relevance. Specifically, it supports missile plume signature characterization of tactical/strategic systems as related to Missile Defense Agency (MDA) requirements for Boost Phase Intercept (BPI) and threat detection via signature spike ("launch flash") during missile engine ignition. The simulation tools are directly applicable to the development of commercial launch vehicles. The simulation software will be licensed to prime vendors and supporting organizations engaged in development of commercial launchers, missiles and interceptors, propulsion systems for space applications e.g. Boeing/Rocketdyne, Pratt & Whitney, Northrop Grumman, Lockheed, Raytheon, etc.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Rex Chamberlain
rex@tetraresearch.com
2610 Spicewood Trail
Huntsville, AL 35811-2604
(256)539-1075

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The use of multidisciplinary analysis (MDA) techniques for complex fluid/structure interaction phenomena is increasing as proven numerical and visualization algorithms and high performance computing (HPC) platforms become more prevalent. Parallel solution methodologies and networked computing clusters are readily available, yet the challenge of bringing highly sophisticated MDA research algorithms into a fast-paced NASA engineering environment still remains. In particular, if the time accurate solution of fluid and thermal structural responses becomes practical, then significant improvements in the analysis of modern rocket engine combustion chambers and other space transportation subsystems will be achieved. Continued improvements in current research tools and further validation of physical models are needed to develop practical MDA capabilities within the growing multidisciplinary engineering community. Our research will produce an innovative MDA system based on an existing multi-physics code (CHEM) to compute the turbulent, chemically reacting flow and coupled structural heating of given configurations. Our unique approach, involving solution adaptive algorithms on generalized unstructured grids, will provide NASA with an important capability to solve fluid/structure interaction problems in a collaborative engineering environment. Furthermore, our hands-on experience with complex MDA problems will help ensure that the research product will offer NASA a significantly improved, commercially viable analysis tool.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
This technology will provide NASA with an enhanced multi-disciplinary analysis capability for the prediction of chemically reacting flows in combustion devices with transient conjugate heat transfer of multiple solid materials. Potential enhancements to the proposed MDA tools include solid propellant burning with surface mass injection and pressure dependence, rotating reference frames for steady state turbomachinery analyses, more complex real fluids models, improved low Mach number performance, and extended model validation. The proposed methodology for the analysis of complex fluid/structure interaction problems is also well suited for extensions to additional multi-physics capabilities of commercial interest to NASA.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The growing trend toward collaborative and multi-disciplinary engineering is opening significant new markets as more complex problems can be addressed using advanced computational techniques. The ability to easily set up and analyze multi-disciplinary problems in a timely manner will allow industry to speed development of new products and streamline testing. Further enhancements to the CHEM MDA system, including a user-transparent extension to incompressible flows, will find application in the aerospace, automotive, electronics cooling, environmental, and nuclear industries. The basic architecture of the MDA tools will remain the same while new plug-in physical models will be developed to address niche markets.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Razvan Rusovici
rrusovici@sti-tech.com
1800 Brighton-Henrietta Town Line Rd
Rochester, NY 14623-2508
(585)424-2010

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This research focuses on fully developing energy density sensors that will yield a significant benefit both for measurements of interest to NASA, as well as for general acoustic measurements. Previous research has developed prototype energy density sensors. The Phase I research will focus on developing effective calibration techniques for these probes, testing and validating the probes to identify the most effective design, developing a software interface to facilitate user-friendly data acquisition, and developing software to measure acoustic directivity and sound power using the energy density sensors. An initial feasibility study will also be carried out to investigate high-temperature, high-pressure designs that are suitable for NASA needs.
Phase II research objectives extend the use of these sensors to measure source directivity and sound power. Energy propagation will be determined from these measurements. A major Phase II focus will be the development of a high-temperature, high-pressure design for the energy density sensor, as well as investigating nonlinear effects on these energy-based measurements.
NASA applications of the technology include characterizing radiation from rocket plumes to better understand the mechanisms involved and to match numerical codes. Non-NASA applications are many, including such tasks as in-situ measurement of sound power and radiation characteristics of sources.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The proposed research will contribute directly to NASA interests. The energy density measurements will provide information about the combustion and flow processes which occur during the burn cycle of the rocket motor. The sound field characterization data could be used to update CFD and FEA models, as well as to provide data to determine acoustic loads on surrounding structures of concern. These energy density sensors could also be used in conjunction with active noise control techniques to alter the acoustic field and thereby probe the field to gain a better understanding of the radiation mechanisms.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The energy density sensors developed will be capable of making acoustic sound power measurements, in both free-field and reverberant field conditions, and under less stringent conditions than is currently required. The sensors will also be useful for acoustic holography applications, and will significantly reduce the measurement time required for this application. With these reconstruction techniques, the energy density measurements can be processed to determine source directivity, and can possibly be used for source identification. A final potential application is for sound field equalization, in which the sound field is equalized using energy density sensors, rather than pressure sensors.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Sandra Klute
vogtw@lunainnovations.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The John C. Stennis Space Center's primary mission is testing rocket propulsion systems and components for the Space Shuttle and for future generations of space vehicles. Research to develop new instrumentation technologies and techniques for test facility monitoring and control during propulsion testing includes the need for instrumentation to improve reliability and performance of ground test facilities. Current sensors can not survive the harsh conditions (high pressures and high flow rates) that are required for ground based rocket propulsion systems testing. Luna Innovations proposes to develop a high-speed, cryogenic fiber optic temperature sensor housed in a ruggedized, aerodynamic probe to increase sensing capabilities for ground-based rocket testing. Luna will be teaming with the Aerospace Department at a partnering university to develop a materials-compatible housing designed for survivability in high flow and high pressure cryogenic conditions. Computational fluid dynamics (CFD) modeling will be conducted to optimize the aerodynamic design for frequency response and ruggedization of the sensor and housing. Special attention will be given to designing smart features into the sensor, such as self-diagnostics to monitor sensor health, and on-board storage of calibration data.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Because of the cutting edge technology development within NASA, cryogenic systems are essential to some applications such as rocket ground testing, space stations applications, shuttle launch operations, and space and flight support applications. Instrumentation is key to the safe and efficient operation of these systems; hence, the technology proposed by Luna Innovations will enable monitoring of various systems with temperature measurements designed for cryogenic harsh-environments.

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Cryogenic temperature and pressure sensors can find use is a variety of applications such as rocket engines, superconducting magnets, and more recently hydrogen handling and storage infrastructure. Though the market is limited for cryogenic applications, the potential use of cryogenic storage in the fuel cell industry will open up a large market in the future for industry and consumer products.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Douglas Morris
doug.morris@alphabetatech.com
3411-C Triana Blvd.
Huntsville, AL 35805-4059
(256)534-9067

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed R&D is to develop a wireless data networking capability. A prototype capability will result from the Phase 1 and 2 contracts. The Versatile Wireless Data Net (VWDN) employs an 802.11x wireless protocol for a network of sensor, recording, and monitoring nodes. The concept combines extensive computational capability with a family of transducers in self-contained packages with an electrical and environmental immunity. Plug-in transducers include microphones, extensometers, toxic gas, pressure sensors, explosive gas, strain gauges (both resistance and fiber-optical), load cells, electromagnetic flux, pyrometers, and accelerometers; many will be MEMS devices. The net enables coordinated, efficient transmission of measurement signals; self test metrics, and environmental metrics to a recording computer. This computer also performs data display and network control for operator intervention to set network functional priorities and implement appropriate responses to monitoring trouble messages. An existing ABT wireless nodal prototype and workstation computer will be used as the basis for the developing the full network capability, that will primarily use commercial-off-the-shelf (COTS) MEMS transducers. After the concept is sufficiently defined, Phase 1 tasks will include a simulation to demonstrate proof of concept.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The VWDN is expected to have substantial value. For NASA the network can be installed in rocket test and launch facilities to monitor operations of propellant and gas transport and storage systems. These benefits can be extended to other Government and contractor operations with dispersed engineering facilities for energy, chemical, fuel, food, water, waste processing

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
Commercially, the VWDEN capability to autonomously sense, measure, evaluate and transmit useful decision making data meets a numerous functional needs, particularly in the energy sector. The wireless networking of a variety of operating metrics enables the network application to many uses in oil and gas distribution, water purification, food processing, and waste management operations. Insightful use of the network will enable these industries to improve continuity of operations, reduce risk of unscheduled and damaging disruptions, reduce manpower required to obtain the vital data for timely adjust to system operations and maintenance, and extend useful life of the assets.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name, E-mail, Mail Address, City/State/Zip, Phone)
Jagdish P. Singh
singh@dial.msstate.edu
109-A Garrard Road
Starkville, MS 39759-0000
(662)323-2666

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The SSC needs a hydrogen temperature sensor that can provide high accuracy, fast response and can be operated on a superheated hydrogen (SHH2) environment. This will help prepare the SSC testing facility to support the new NASA mission for US space exploration as proposed by the President in January 2004. Here, we propose to develop an innovative, non-intrusive temperature sensor based on Spontaneous Raman Scattering (SRS). SRS has been known for years as a relatively simple analytical method. The goal of the proposed effort is to demonstrate a SRS sensor, which is able to provide millisecond sampling time for temperature measurements in SSH2. During Phase I, a SRS system based on a 0.5 spectrometer and ICCD detector will be used to find the best hydrogen bands for the temperature measurement. The fast response PMTube - based SRS system will then be designed for selected spectral lines. Experimental parameters will be evaluated to achieve optimum response time and sensitivity for this application. The study from Phase I will provide the necessary information to design a phase II prototype unit to achieve millisecond response time and better sensitivity in a compact package. In Phase II, the prototype SRS system will be developed and tested at the SSC and will be delivered to NASA/SSC for their evaluation.

POTENTIAL NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
A Raman based sensor can provide an on-line, real-time temperature measurement with millisecond response time which is needed by NASA/SSC for testing superheated H2 as part of a system for deep space exploration. This sensor can also be used for real-time temperature profile measurements during hydrogen-based engine testing. In addition, this sensor can be used as a hydrogen leak detector

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS (LIMIT 100 WORDS)
The uses of a Raman sensor to measure superheat H2 temperatures has several other applications. This sensor, or a modified version, can also be used for hydrogen fuel technology, the generation of liquefied gases, gasification plants, various chemical industrial processes, and biomedical research. The sensor based on Raman spectroscopy developed for this proposal can be readily modified to measure the temperature in certain high temperature industrial furnaces. This hydrogen sensor can measure both low and high temperatures for gas or liquid phase. It can be used for combustion diagnostic and also as a hydrogen leak detector at facilities that produce and handle hydrogen.

STTR 04-II Proposal Abstracts

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
NEMOmetrics Company
28 Constitution Road
Boston, MA 02129-3108

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Massachusetts Institute of Technology
77 Massachusetts Avenue
Cambridge, MA 02129-4307

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
John Rodriguez
john@nemometrics.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Proposal Title: Aerospace Systems Monitor PHASE 1 Technical Abstract: This Phase II STTR project will continue development and commercialization of the Aerospace System Monitor (ASM). This technology transforms the power distribution network in a spacecraft or aircraft into a multiple-use service, providing not only power distribution but also a diagnostic monitoring capability and system health monitoring based on observations of the way in which loads draw power from the distribution service. Careful measurements are made power transients and this data is used to assess system functioning and identify potential faults and failures. In the Phase II project, development will continue on the ASM software and on power line sensors to obtain data in ground testing and in flight. ASM will be applied to reaction wheels and momentum wheels. A test bed will be built and we will demonstrate the ability to verify correct operation and identify faults and flaws in prototype and operational reaction wheels. Phase III will continue this work and apply it further to reaction wheels and to other systems and components in ground testing and in flight.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Aerospace System Monitor is a new, inexpensive, lightweight and non-space consuming method to measure system operation and system health. It will be a new method to obtain this information on satellite systems and provide a new source and type of data. It also represents another "string" of data for manned and high value unmanned systems which require multiple sources of sensor data. It will be useful in ground testing and in flight and will also be useful in manned spacecraft and in aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
This Non-intrusive electrical monitoring technology (NEMO) will also have applications in military and commercial automotive vehicles, in ships and boats and for monitoring of HVAC and other electrical systems in buildings and facilities.

PRINCIPAL INVESTIGATOR/PROJECT MANAGER (Name,Email)
William   Morrison
bill@teamqsi.com

TECHNICAL ABSTRACT ( Limit 2000 characters, approximately 200 words)
Space exploration is a unique challenge with many difficulties in its implementation. With a goal of the return of man to the moon and travel to Mars, the stage has been set for the expansion of human knowledge beyond comprehension. Traveling to the moon and Mars, however, will require new and innovative technologies. Key to this will be system health management (SHM). For any given system of the myriad that will be required for space missions, a way of safely and efficiently managing the system health will be required. These goals are the motivation behind the proposed Phase II effort.

POTENTIAL NASA COMMERCIAL APPLICATIONS ( Limit 1500 characters, approximately 150 words)
The proposed technologies will prove useful to a wide variety of NASA applications. A complete unified SHM approach will provide safety and efficiency to many system level applications. Demonstration on a power subsystem will provide many offshoot technologies with commercial applications such as the battery impedance monitoring technique developed in Phase I (patent pending).

POTENTIAL NON-NASA COMMERCIAL APPLICATIONS ( Limit 1500 characters, approximately 150 words)
Potential Non-NASA commercial applications exist in many different sectors. QSI's diagnostic tools are currently being used in military and commercial applications on three continents. Enhancements to the QSI toolset will be of great value to current customers and open the door for new sales. The application of the battery monitoring and prognostics technology is very promising for such market sectors as electric/hybrid-electric vehicles, consumer electronics (laptops, cell phones, etc...), residential and commercial power generation and storage technology (e.g. home solar power generation units), etc...

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
Space Micro, Inc.
10401 Roselle Street, Suite 400
San Diego, CA 92121-1526

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
Clemson University
118 Kinard Laboratory
Clemson, SC 29634-1180

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
David Strobel
dstrobel@spacemicro.com
12872 Glen Circle Road
Poway,  CA 92064-2029

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Space Micro will extend our Phase I R&D to develop a family of miniature, active space radiation dosimeters/particle counters, with a focus on biological/manned dose levels. A single board design will support both manned level and space electronics level dosimetry needs. This is enabled by the density and features of commercial high density silicon semiconductor memory devices, coupled with innovative patented programming algorithms. We plan to augment this core dosimeter technology with other emerging novel miniature radiation detectors to enhance single particle detection, including heavy ions and secondary neutrons. A flight dosimeter will be delivered to NASA for flight demo on ISS or other platform. Space Micro will then commercialize for both NASA markets (manned and electronics grade levels) with a standard product offering through our established marketing channels.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
NASA applications include both human and life sciences/biological programs. This dosimeter directly supports ISS, NASA's Mission to the moon, Mars, and beyond, by monitoring astronaut radiation dosage real time during long duration missions. New specific programs include CEV and Robotic Lunar Exploration Program (RLEP) In addition, Space Micro will develop a derivative product targeting the higher radiation levels seen in unmanned missions. In these programs the electronics and materials are impacted by the space radiation.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Non-NASA applications include detectors and dosimeters for the Department of Homeland Security (DHS). US and NATO ground military forces also could benefit. Planned commercial space tourism ventures will need stringent passemger monitoring. Commercial and DoD space programs such as imaging, weather and telecommuncations satellites will be benefit and be future customers for this standard product.

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

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
California Polytechnic State University Foundation
1 Grand Avenue
San Luis Obispo, CA 93410-0001

PRINCIPAL INVESTIGATOR/PROJECT MANAGER: (Name, E-mail, Mail Address, City/State/ZIP, Phone)
Thomas Carpenter
tcarpent@calpoly.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent success of an annular aerospike flight test by NASA Dryden has prompted keen interest in providing thrust vector capability to the annular aerospike nozzle (AAN). The AAN with a moveable spike for thrust vectoring and throttling could provide a more efficient alternative to traditional bell nozzles. Cal Poly, which has a thrust vector research facility, has teamed with Rolling Hills Research Corporation, with CFD capability, to experimentally and analytically determine the optimal approach to thrust vectoring and throttling the AAN. In Phase I, several scale AAN models were fabricated with movable spikes that could be displaced and/or gimballed. One set of studies quantified thrust changes as a function of spike axial position for throttling. Other studies examined the thrust vectoring effectiveness of various proprietary nozzle configurations. Schlieren photography and 3-axis force measurements showed excellent correlation to predictions made with the OVERFLOW CFD code. The most promising of the nozzle configurations for thrust vectoring and throttling were shown to produce stable flow that generates a resultant turn angle whose magnitude is in the neighborhood of current rocket booster technology. These promising configurations have been selected for extensive laboratory testing and computational analysis for optimization in the Phase II program. The objective of Phase III will be flight test.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In the near term, aerospike nozzles with optimal thrust vector control will provide added safety and improved capability to the NASA Dryden Aerospike Rocket Test project, as well as economic benefit through the reuse of nozzles. Thrust vectoring and throttling capabilities would provide control of flight regimes (speed, angle of incidence, transients, and other flight conditions). In addition, flights with thrust vector control would have less dispersion and therefore could be confined to a smaller test area, which would improve range safety. An aerospike nozzle with thrust vector control would be appropriate for future NASA single-stage-to-orbit programs.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Now, in the early 21st century, we stand at the threshold of affordable commercial access to space. In the future, single-stage-to-orbit (SSTO) reusable launch vehicles (RLV) will provide relatively inexpensive (less than $5M) and widespread commercial access to space. Due to their inherent altitude compensation, aerospike rocket nozzles are ideal for SSTO vehicles. A self-contained aerospike nozzle with thrust vectoring and throttling capability would provide a practical, cost-effective means of controlling the rocket flight path for such vehicles. Commercial applications for relatively inexpensive SSTO RLVs are virtually unlimited, but certainly include the economically significant small satellite launch business.

SMALL BUSINESS CONCERN: (Firm Name, Mail Address, City/State/ZIP, Phone)
KALSCOTT Engineering, Inc.
PO Box 3426
Lawrence, KS 66046-0000

RESEARCH INSTITUTION: (RI Name, Mail Address, City/State/ZIP, Phone)
North Carolina State University
Research Administration/SPARCS, 2701 Sullivan Drive
Raleigh, NC 27695-7514

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

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The need for aerodynamics-based efficiency enhancements for air vehicles is presented. The results of the Phase I investigation of concepts for morphing aircraft are discussed. Morphing enables the aircraft to optimize its configuration for various flight regimes. This translates to benefits in range, endurance, manueuvering and speed characteristics of the air vehicle. Using simulations, live testing, and benchtop hardware development, the feasibility of the concepts was established in Phase I. In Phase II, key additions to the design, such as trailing edge flaps, and an intelligent, sense-and-adapt method to achieve continuous aerodynamic optimization flight testing will be integrated. Wind tunnel testing and flight testing will be performed to refine and finalize the designs.

POTENTIAL NASA COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
These innovations can be applied to several NASA subsonic aircraft, including manned and unmanned platforms. Some of the work here can be extended to gust alleviation for high altitude UAVs as well. This STTR effort complements other work underway at NASA in the areas of adaptive aircraft, morphing aircraft configurations, robust controls, intelligent/distributed vehicle health monitoring, and intelligent aircraft.

POTENTIAL NON-NASA APPLICATION(S) (LIMIT 150 WORDS)
Several federal agencies are using (or planning to use) large unmanned aircraft for civilian (science mission) and homeland security roles. Also, military groups are planning to use high altitude long endurance UAVs for reconnaissance and sensor platform missions. Morphing enables such aircraft to optimize their configuration for various flight regimes. This translates to benefits in range, endurance, manueuvering, handling, and speed characteristics of the air vehicle.