NASA 2000 STTR Phase 1 and 2 SOLICITATION

2000 NASA STTR Phase-I Proposal Proposal #: 000056

2000 NASA STTR Phase-I Proposal Proposal #: 000104

1. Research Topic: 01 - Information Technology 2. Project Title: Brahms VE: A Collaborative Virtual Environment for Mission Operations,
Planning and Scheduling

3. Small Business Concern 4. Principal Investigator
Name: DigitalSpace Corporation Name: Bruce Damer
Address: 343 Soquel Avenue, #70
City: Santa Cruz
ST: CA Zip: 95062

5. Research Institution
Name: USRA/RIACS
Address: Mail Stop 19-39, NASA Ames Research Ctr
City: Moffett Field
ST: CA Zip: 94035

6. Technical Abstract (Limit 200 words)

We propose to combine the proven Brahms multiagent work practice simulator and the DSpace1 3D thin client VR system to produce Brahms VE, a visual simulator used to improve human practices within a model of the work environment. The prototyping of the ALSEP deployment on Apollo XVI within Brahms VE should qualify this approach for a broader applications in simulation and training for fully autonomous missions and manned spacecraft employing tele-operation and extensive ground support.

7. Potential Commercial Application(s)(Limit 200 words)

Brahms VE is anticipated to have a wide range of applications including: collaborative business virtual environments in shared problem resolution spaces, as learning spaces for educational and museum institutions, e-commerce service areas with agent-assistance for customers and as a training vehicle for industrial users.

2000 NASA STTR Phase-I Proposal Proposal #: 000118

1. Research Topic: 01 - Information Technology 2. Project Title: Intelligent Control For Autonomous Remote Spacecraft

3. Small Business Concern 4. Principal Investigator
Name: Accurate Automation Corporation Name: Dr. James C. Neidhoefer
Address: 7001 Shallowford Road
City: Chattanooga
ST: TN Zip: 37421

5. Research Institution
Name: University of Alabama
Address: P.O. Box 870104,G60 Rose Admin.
City: Tuscaloosa
ST: AL Zip: 35487

6. Technical Abstract (Limit 200 words)

We will apply the latest knowledge in learning control, adaptive control, and optimal control to develop a modular, state-of-the-art, adaptive, nonlinear, guidance, navigation, and control package for remote spacecraft. The system will incorporate planning and decision making modules to give the remote spacecraft on-line goal directed self-reliant behavior with a high degree of autonomy. At the highest level, an expert system based "Goal Executive" will monitor the spacecraft's environment and switch and/or adapt the performance indices of an adaptive critic based guidance system, and an evolutionary algorithm based navigation system. This will, in effect, change the near-term behavior of the remote spacecraft by changing what it considers "optimal". The navigation system will specify optimal way-points for achieving the specified mission goals. The guidance module will generate an optimal trajectory between the way-points and the control module will ensure robust and accurate trajectory tracking. The controller will be based on an improved version of an nth order multi-variate Neural Adaptive Controller (NACTM) developed at AAC.

7. Potential Commercial Application(s)(Limit 200 words)

In the near term, we anticipate a modular, portable, autonomous Guidance, Navigation, and Control (GN&C) software package to be the primary commercialization. There is a tremendous need for such a package in industries that apply advanced control technologies, especially the aerospace industry. Our software will fill a gap in the GN&C development software market. Currently, there are no easy-to-use tools that are highly general and powerful. The most powerful tools available require the user to select many parameters, usually iteratively, until an adequate solution is reached. We will investigate licensing the software to a software company. In this way, we can benefit from royalties without having to build a general support infrastructure. At the same time, we can continue to sell the product to specific customers and support them through individual agreement.

2000 NASA STTR Phase-I Proposal Proposal #: 000021

1. Research Topic: 02 - Atmospheric Flight Operations 2. Project Title: An Intermittency Transport Model for Practical CFD Designs of
High Speed Vehicles

3. Small Business Concern 4. Principal Investigator
Name: Taitech, Inc. Name: Chung-Jen J. Tam
Address: 1430 Oak Court, Suite 301
City: Beavercreek
ST: OH Zip: 45430

5. Research Institution
Name: University of Kentucky
Address: 102 Kinkead Hall 0057
City: Lexington
ST: KY Zip: 40506

6. Technical Abstract (Limit 200 words)

This proposed research is to present a general CFD subroutine for predicting flow transitions in hypersonic regimes. The subroutine makes use of an intermittency transport equation to describe the behavior of the flow transition, and is therefore compatible with existing CFD codes. The proposed model solves an additional transport equation for the intermittency distribution and the resulting intermittency is then used to adjust the turbulent eddy viscosity in the transition region. The major advantage of this approach is that it does not require pre-calculation of the mean flow but includes the laminar, transitional, and turbulent regions in a single computation. The current intermittency transport equation has been validated for subsonic flows with different freestream turbulence intensities and pressure gradients. The Phase I research will extend the capability of the model to high Mach number flight conditions by including compressibility and heat transfer effects.

7. Potential Commercial Application(s)(Limit 200 words)

For the design of hypersonic vehicles, it is important to predict flow transition reliably: Mach number effects cause a significant delay in flow transition and also give rise to a wider transition region, as compared to the transition behavior of incompressible flows. As a result, the capability of the current CFD code in predicting flow transition plays a significant role in hypersonic vehicle designs. The proposed intermittency model involves the solution of a transport equation for intermittency, and the resulting intermittency is used to modify the eddy viscosity such that the transition behavior can be described adequately. The current method has been tested in incompressible flows under a variety of flow conditions with impressive results. As compared with the available stability methods for transition preditions, the proposed intermittency method is a cost-effective method to predict transitional flows, for it can easily be incorporated into commercial and research codes used in the design of high transport aircraft and space launch vehicles.

2000 NASA STTR Phase-I Proposal Proposal #: 000063

1. Research Topic: 02 - Atmospheric Flight Operations 2. Project Title: Integrated software toolbox for aeroelastic modeling and dynamic
stability analysis of a Generic Hypersonic Vehicle

3. Small Business Concern 4. Principal Investigator
Name: Scientific Systems Company, Inc. Name: Ravi Prasanth
Address: 500 West Cummings Park, Suite 3000
City: Woburn
ST: MA Zip: 01801

5. Research Institution
Name: Sponsored Programs
Address: Virginia Poly. Tech & State Univ
City: Blacksburg
ST: VA Zip: 24061

6. Technical Abstract (Limit 200 words)

Aeroservoelastic (ASE) modeling and vehicle stability analysis are two major concerns in the accurate prediction of flight characteristics of
generic hypersonic vehicles (GHVs). We propose to develop an ASE modeling and vehicle stability analysis toolkit. System Identification (SI)-based black box models of CFD solvers is the primary focus in Phase I. Bifurcation and Chaos Theory Methodology (BACTM) is the main tool
for nonlinear stability analysis. The proposed software consists of a library of ASE model structures, SI routines, and BACTM modules. The software will enhance the capabilities of STARS code currently in use at NASA Dryden. Phase I work involves: (1) acquisition of GHV models, STARS training data and code, (2) development of ASE modeling toolkit for GHV, (3) nonlinear analysis of ASE, (4) trajectory optimization and GHV flight stability analysis, (5) integration of software modules into STARS, and (6) final report and software delivery. Specific problems addressed include nonlinear flutter analysis, effect of modeling uncertainties, nonlinear flight dynamics in the presence of inertia coupling and unsteady effects. Prof. Lutze of VPI and Prof. Klein of JIAFS/GWU will serve as subcontractors in this project.

7. Potential Commercial Application(s)(Limit 200 words)

SI-based modeling software has applications in flight testing, combustion processes, fluid mechanics, and process control. Nonlinear stability analysis software has applications in aircraft, jet engines, civil engineering structures, chemical instabilities, compressor stall, biology and communications.

2000 NASA STTR Phase-I Proposal Proposal #: 000122

1. Research Topic: 02 - Atmospheric Flight Operations 2. Project Title: Finite Element Multi-Disciplinary Analysis of Flight Vehicles

3. Small Business Concern 4. Principal Investigator
Name: Stirling Dynamics Inc Name: Dr. Ewald Schoemig
Address: 200 West Mercer Street, E410
City: Seattle
ST: WA Zip: 98119

5. Research Institution
Name: Naval Postgraduate School
Address: Code 09, Dean of Research, Rm 220
City: Monterey
ST: CA Zip: 93943

6. Technical Abstract (Limit 200 words)

Availability of engineering analysis and design tools for accurate prediction of vehicle flight performance characteristics is highly desirable. Existing programs that use panel methods are inadequate for complex geometry and for handling the full range of flight conditions. This proposal identifies the development and integration of finite element multidisciplinary analysis (FEMA) and design of flight vehicles. An existing Computational Fluid Dynamics (CFD) code will be used to couple structural, aerodynamic and flight controls interaction in an efficient and robust manner. In Phase I, we will establish criteria for critical performance and operation bounds, basic principles and concepts, spatial and temporal discretization and related methods of solution. We will evaluate the performance of FEMA tools with other available solutions. A pilot code that simulates CFD-structure-control integration to depict the effectiveness of the presently developed algorithm will be developed. Several algorithms for design optimization for integration into FEMA tools will be identified. Flight control systems integration will be evaluated and proposed for implementation. Improvements and integration of advanced flight control systems structures will be evaluated. In particular we propose to investigate the feasibility of integrating nonlinear control laws as well as specific control design methods into multiobjective optimization software.

7. Potential Commercial Application(s)(Limit 200 words)

The finite element multidisciplinary analysis (FEMA) computer program will be available for immediate usage for dual-use commercialization. Potential dual-use applications include the design of all types of military and civilian aircrafts, automobile and engine components, various mechanical subsystems, marine and civil engineering structures, and applications in other disciplines. Both linear and nonlinear aeroelastic and aeroservoealstic simulations for subsonic to hypersonic speeds will be possible by the program.We will make every effort to render the software developed in both Phase I and II user friendly and provide good documentation. Ease of use and robustness in capabilities of the software will ensure the fullest use of the tools by the government and commercial sectors.

2000 NASA STTR Phase-I Proposal Proposal #: 000011

1. Research Topic: 03 - Scientific Research 2. Project Title: Novel Very Fast Tunable Filter for Hyperspectral Imaging

3. Small Business Concern 4. Principal Investigator
Name: Opto-Knowledge Systems, Inc. Name: Nahum Gat
Address: 4030 Spencer St. Suite 108
City: Torrance
ST: CA Zip: 90503

5. Research Institution
Name: Brown University
Address: Division of Engineering, Box D, 182 Hope
City: Providence
ST: RI Zip: 02912

6. Technical Abstract (Limit 200 words)

Spectral imaging has broad potential applications ranging from remote sensing in areas such as agriculture or geology, to medical use. The remote sensing sensors use complex opto-mechanical and expensive techniques to operate in pushbroom and whiskbroom modes. Ground based stationary applications require mechanical scanning to build up the image cube. An alternative for all these devices is based on the use of an electronically tunable filter that is mounted in front of the monochrome camera system. Such spectral imaging sensors present great simplification and cost reduction for all applications including air- or space- borne, and ground based stationary sensors. Such techniques are already in use, but present day tunable filters suffer from very poor optical throughput, are polarization sensitive, and very expensive to produce. This proposal capitalizes on recent progress in new optical polymers research, to develop a novel tunable filter that will have an order of magnitude improvement in light transmission, a factor of 500 faster switching time. This polymer dispersed liquid crystal has wide applications in displays, and therefore its production costs will also be but a small fraction of the cost of present systems.

7. Potential Commercial Application(s)(Limit 200 words)

For the past several years OKSI has been the first company to market customized turn key spectral imaging systems. Its market now extends into several fields including surgical imaging, dental, precision agriculture, geology, inspection and manufacturing, forensics, and more.

2000 NASA STTR Phase-I Proposal Proposal #: 000070

1. Research Topic: 03 - Scientific Research 2. Project Title: Self-Deploying Foam Antenna Structures

3. Small Business Concern 4. Principal Investigator
Name: Adherent Technologies, Inc. Name: Dr. Andrea E. Hoyt
Address: 9621 Camino del Sol NE
City: Albuquerque
ST: NM Zip: 87111

5. Research Institution
Name: Jet Propulsion Laboratory
Address: 4800 Oak Grove Drive
City: Pasadena
ST: CA Zip: 91109

6. Technical Abstract (Limit 200 words)

There is an increasing need for large, reliable, and cost-effective inflatable space antennas for communications applications. This Phase I program will focus on the design and development of open-celled foams as structural elements in self-deploying antenna systems. Foams offer the following significant advantages over conventional materials for these applications: open cellular structure allowing compaction of large structures into small volumes; high dynamic damping, strains due to mechanical movement of the structure (turning moments, etc.) will damp out very rapidly and the spacecraft will return to its required dimensions in a few seconds; restoring force, results in its self-deploying property and its utility as an antenna construction material; and glass transition-based rigidization. The goal of the Phase II follow-on program is the use of an open-celled foam rigidization system in conjunction with specialized high accuracy membrane materials to create a stable "eggshell" antenna in space.

7. Potential Commercial Application(s)(Limit 200 words)

The proposed work will result in a new materials technology for self-deployable spacecraft based on open-celled foam support structures. Use of this new technology will provide a much needed advance in inflatable and deployable technology by providing a controlled deployment and rigidization method for a lightweight, compact, and long storage life structural material. As such, it is expected that antennas and other structures based on this technology will quickly transfer from government and military applications into the commercial communications arena.

2000 NASA STTR Phase-I Proposal Proposal #: 000083

1. Research Topic: 03 - Scientific Research 2. Project Title: A compact, UAV compatible, high-definition hyperspectral imaging system 3. Small Business Concern 4. Principal Investigator
Name: Flight Landata, Inc. Name: Xiuhong Sun
Address: One Parker Street
City: Lawrence
ST: MA Zip: 01843

5. Research Institution
Name: Trustees of Boston University
Address: 881 Commonwealth Avenue
City: Boston
ST: MA Zip: 02215

6. Technical Abstract (Limit 200 words)

The innovation is a compact, UAV compatible, high-definition hyperspectral imaging system. The system concurrently-acquires a hyperspectral image using a compact grating imaging spectrometer and a much-higher spatial resolution color photographic image using a portable, measurement-grade, high-definition CCD camera (2,000 x 1,312 pixel). The spectral resolution of the hyperspectral image is better than 5nm covering a spectral range from 400nm to 1700nm (expandable to 2500nm) with a swath width better than 320 pixels. The quantization bit resolution of the system is better than 10-bits. The system is for NASA's stated need of spectral imager instrument for UAV with a weight less than 15 kg
and a volume no large than 0.1 cubic meters. It achieves state-of-the-art system integration with built-in data acquisition, positioning/attitude measurement, on-board flight plan, map-matched system automation, and seamless real-time operation into a compact airborne computer. The software package developed has an excellent point-and-click graphic user interface that supports spectral and radiometric calibration, post data processing, and pointing-device-activated pixel spectrum visualization over its registered high-definition photographic image. With seamless
data fusion of high-resolution photographic imaging and pushbroom- scan hyperspectral imaging at the measurement level, well-balanced spatial, spectral, and radiometric information is obtained with optimized and manageable data volume.

7. Potential Commercial Application(s)(Limit 200 words)

The commercial product is a novel, versatile, and ultra-compact airborne high- resolution hyperspectral imaging system, which can be fit onto divers small aircraft, UAV, airship and balloon for low cost and operational remote sensing. Its immediate applications include NASA calibration/validation for the multitude of hyperspectral and multispectral satellites and new application development. The potential commercial applications of this innovative instrument product include operational remote sensing for precision agriculture, crop and forest growing status monitoring, mineral exploration, geological prospecting, coastal environment studies, surface pollution detection, hydro-carbon related gas
leakage detection, and land-use surveys.

2000 NASA STTR Phase-I Proposal Proposal #: 000142

1. Research Topic: 03 - Scientific Research 2. Project Title: Imaging and Analyzing Plant Stresses in the Ag-Ecology

3. Small Business Concern 4. Principal Investigator
Name: GrowTech Inc. Name: Robert Lussier
Address: 1 Piper Road
City: Lexington
ST: MA Zip: 02421

5. Research Institution
Name: University of Massachusetts
Address: Stockbridge Hall
City: Amherst
ST: MA Zip: 01003

6. Technical Abstract (Limit 200 words)

The proposed R/R&D effort will obtain new improved, in situ measurements of vegetation using a computer-based fluorescence imaging system that images and processes the plant's cellular energy emissions to quantify and diagnose the plant's photosynthetic pathways. With multi-spectral bandwidths and image processing which increase the system's sensitivity, fluorescence-imaging diagnoses early plant stresses, pre-symptom, days to weeks before the unseen symptoms become visible. The R/R&D effort will test the pre-symptom detection of difficult vascular and root pathogen stresses, nutrient deficiencies, water and other environmental stresses in tomato, corn and soybean. The test program will also serve to test the system's diagnosis of the imposed stresses. The plant stress test program and data acquisition will develop and provide a base-line, plant stress image database for input to NASA science databases. In addition, the innovation is important as a ground-based imaging system that detects, quantifies and diagnoses plant stress and physiological characteristics as ground-truth data, meeting a NASA need for validating Remote Sensing systems.

7. Potential Commercial Application(s)(Limit 200 words)

The proposed R/R&D effort, assuming the goals are achieved, will lead to the commercialization of a ground-based fluorescence imaging system that will provide computer-based imaging, diagnostic and plant stress information to commercial growers and to users for environmental inspection. The on-site, real- time inspection of field crops using an innovative imaging and diagnostic system will be advantageous to growers as a crop management information system. A portable imaging and processing system with real-time data acquisition will enable the crop producer to recognize and diagnose early plant stress and physiological characteristics, undertake managed alternatives to reduce or minimize a yield loss and improve his profitability. A ground-truth system will similarly enable users to monitor vegetation for environmental and remediation applications. The benefits available are to replace today's visual inspections with an innovative imaging system that quantifies and diagnoses the plant's physiological characteristics and is capable as a management information system.

2000 NASA STTR Phase-I Proposal Proposal #: 000159

1. Research Topic: 03 - Scientific Research 2. Project Title: Position Sensitive Gamma Ray Sensor

3. Small Business Concern 4. Principal Investigator
Name: Constellation Technology Corporation Name: Raymond DeVito
Address: 7887 Bryan Dairy Rd., Suite 100
City: Largo
ST: FL Zip: 33777

5. Research Institution
Name: University of Michigan
Address: College of Engineering
City: Ann Arbor
ST: MI Zip: 48109

6. Technical Abstract (Limit 200 words)

Mercuric Iodide has several properties that make it an ideal detector material for space-based astronomy applications. Due to its high atomic number (Z=80,53) and high density (r= 6.3 g/cm3), a significantly higher quantum efficiency for x-ray and gamma ray detection can be achieved with a relatively small amount of material. The project objectives are to: - develop the technology to readout signals from a large number of anode pixels on a mercuric iodide detector. - demonstrate the ability to produce a large volume mercuric iodide detector with excellent spectroscopic and spatial resolution. - construct a mercuric iodide position sensitive spectrometer with greater thickness than has yet been produced. Completion of these objectives will allow us to demonstrate the performance of the mercuric iodide detector system for application to gamma ray imaging and spectroscopy.

7. Potential Commercial Application(s)(Limit 200 words)

The proposed position sensitive mercuric iodide detector has broad utility across many applications in gamma-ray detection. For example, pixelated mercuric iodide detectors and systems would be a compelling candidate for nuclear and particle physics laboratories. The proposed mercuric iodide detector has direct application to health care through gamma detection and imaging applications such as Nuclear Medicine gamma cameras and PET systems. Pixelated mercuric iodide detectors have the potential to improve image quality and diagnostic accuracy of these devices and reduce healthcare costs in areas such as the diagnosis of cardiac disease and the detection and staging of cancer. Other potential applications include systems designed for: radioactive materials monitoring, baggage and cargo inspection using planar or tomographic imaging, nuclear weapons treaty verification, and explosives and contraband detection using gamma backscatter detectors.

2000 NASA STTR Phase-I Proposal Proposal #: 000022

1. Research Topic: 04 - Space Propulsion 2. Project Title: Carbon Sails for Gossamer Spacecraft Attitude Control

3. Small Business Concern 4. Principal Investigator
Name: Energy Science Laboratories, Inc. Name: Timothy Knowles
Address: 6888 Nancy Ridge Drive
City: San Diego
ST: CA Zip: 92121

5. Research Institution
Name: Univ of Kentucky Research Foundation
Address: 102 Kinkead Hall
City: Lexington
ST: KY Zip: 40506

6. Technical Abstract (Limit 200 words)

It is well known that light and other electromagnetic radiation can exert pressure on matter, which is the basis for photon sail propulsion. Less well known is that light can also exert controlled torque and in-plane tension on sails that have suitable electromagnetic properties. Although these effects are potentially effective aids to deployment and remote control of gossamer spacecraft, they have not been investigated either analytically or experimentally. This project shall investigate these effects with the goal of developing materials, design tools, and gossamer spacecraft control strategies. Phase 1 will analyze the thrust, tension, and torque produced when polarized electromagnetic radiation interacts with anisotropic sails. Experiments will be performed on tailored carbon microtruss sails using an ultra-sensitive vacuum torsion wire technique to directly measure low-power microwave radiation pressure and torque. Advanced sail designs will be drafted and applications to gossamer spacecraft control will be assessed. Phase 2 would further develop the technology, including numerical and analytical methods, carbon sail processing, and ground testing in vacuum at low power. Concepts for experiments in microgravity (parabolic flight) and at higher power will be developed.

7. Potential Commercial Application(s)(Limit 200 words)

The proposed sails offer novel flight control for sails and gossamer spacecraft. The potential exists to provide long-term attitude control for gossamer spacecraft without consumption of on-board fuel, which would greatly reduce the cost of launching and maintaining earth-orbiting satellites. The development may be useful for control of space interferometer spacecraft that require precision formation. The carbon materials also have application to lightweight large-area microwave spacecraft antennas as well as wireless handsets with novel directional and polarization-sensitive properties.

2000 NASA STTR Phase-I Proposal Proposal #: 000062

1. Research Topic: 04 - Space Propulsion 2. Project Title: Superconducting Magnetic Energy Storage for Maglifter Launch Assist

3. Small Business Concern 4. Principal Investigator
Name: Advanced Magnet Lab, Inc. Name: Rainer Meinke
Address: 2730 Kirby Avenue - Bldg. 5
City: Palm Bay
ST: FL Zip: 32905

5. Research Institution
Name: Massachusetts Institute of Technology
Address: 167 Albancy Street
City: Cambridge
ST: MA Zip: 02139

6. Technical Abstract (Limit 200 words)

NASA is considering an electromagnetic catapult, the "MagLifter" to lower the cost of cargo delivery to space and improve launch reliability. A carrier sled, levitated and propelled by magnets, provides an inintial velocity to a space transportation vehicle. For Large payloads, the required energy for this launch assist is in the range of 20 gigajoule with peak-power requirements of several gigawatt. Using power for this application directly from a utility grid seems prohibitive, and intermediate storage of energy is necessary. Superconducting magnetic energy storage (SMES), which charged from the local power grid and discharged during launch sequence, offers a highly efficient and environmental benign solution. The technology is well developed and SMES systems are considered worldwide for stabilization of increasingly complex power distribution grids. Cable-in-conduit conductor, developed at M.I.T. is enabling technology for such a SMES system. It is the goal of the proposed project to determine an economical SMES configuration for the MagLifter concept, which enables reliable spaceport operation. A conceptual design of the major components of this energy storage system will be performed. During Phase II the conceptual design of the major components, the magnet system and the power converters would be worked out in detail.

7. Potential Commercial Application(s)(Limit 200 words)

The proposed SMES system is enabling technology for commercially competitive, electromagnetic space launch infrastructure. Such SMES systems are also of great interest for utility applications in particular after the deregulation of the U.S. power industry.

2000 NASA STTR Phase-I Proposal Proposal #: 000107

1. Research Topic: 04 - Space Propulsion 2. Project Title: A Mass-Reducing End-Plugging Scheme for the Gasdynamic Mirror Propulsion
System

3. Small Business Concern 4. Principal Investigator
Name: Advent Engineering Services, Inc. Name: Dr. Terry Kammash
Address: 24 Frank LLoyd Wright Dr., Lobby A
City: Ann Arbor
ST: MI Zip: 48106

5. Research Institution
Name: University of Michigan
Address: Dept. of Nuclear Engin. & Rad Sci.
City: Ann Arbor
ST: MI Zip: 48109

6. Technical Abstract (Limit 200 words)

A very promising approach to a significant reduction of the mass of the gasdynamic mirror (GDM) fusion propulsion system is proposed. It
makes use of field-reversal techniques whereby a rotating magnetic field is employed to induce an azimuthal current in the plasma, which in turn gives rise to the desired magnetic field at an appropriate plasma radius in the mirror region. This has the effect of preserving the needed larger plasma mirror ratio without the use of large mirror magnets. This proposal is aimed at an investigation of this approach and how it might apply to the GDM propulsion system. The results generated will constitute the basis of a Phase II proposal aimed at applying this technique to the GDM experiment at the Marshall Space Flight Center (MSFC).

7. Potential Commercial Application(s)(Limit 200 words)

NASA's often stated objective with regard to future space transportation system is that they be faster, cheaper, and better. The field reversed GDM presented in this proposal truly meets these objectives. The very large specific impulse and thrust expected to be generated by the
modified GDM would allow it to serve as a space transport for space tourism. In addition to its space application, the GDM device can serve as
a neutron source for materials testing for terrestrial fusion power reactors and as a source of radiation for potential applications to radioactive
waste disposal considerations.

2000 NASA STTR Phase-I Proposal Proposal #: 000141

1. Research Topic: 04 - Space Propulsion 2. Project Title: Specific Impulse Analysis of Solid Materials for Ablative Laser Propulsion

3. Small Business Concern 4. Principal Investigator
Name: Information Systems Labs, Inc. Name: Dr. Andrew V. Pakhomov
Address: 6767 Old Madison Pike, Ste. 180
City: Huntsville
ST: AL Zip: 35806

5. Research Institution
Name: University of Alabama in Huntsville
Address: 301 Sparkman Dr.
City: Huntsville
ST: AL Zip: 35899

6. Technical Abstract (Limit 200 words)

The proposed work is directed towards the understanding and utilization of the relatively unexplored concept of ablative laser propulsion (ALP). The work will include direct measurements of the specific impulse imparted to solid targets under short-pulse laser irradiation. The purpose of the proposed work is to demonstrate the viability of the ALP concept and to develop a set of specific requirements for solid materials best suited for ALP, supported by data on specific impulse as a function of material properties and irradiation conditions. Pulse width, pulse repetition rate and laser wavelength are expected to be important parameters. Anticipated results of the Phase-I work are an understanding of factors defining
specific impulse due to material properties and irradiation conditions and selection of candidate elements for the Phase-II research. In Phase II,
we anticipate discovering the factors, such as material composition and irradiation conditions, determining specific impulse and other parameters (such as mass removal rates, angular distributions of ion energy and number density, charge states, etc.) critical for ALP.

7. Potential Commercial Application(s)(Limit 200 words)

Because our concept obviates the conventional rocket engine, it will provide improvements in the cost and reliability of space propulsion. It will lead to safe, affordable, high-performance propulsion for space vehicles and thus promote commercialization of space. Some potential commercial applications of this work include satellite station keeping, satellite attitude control, satellite maneuvering (gross movements, orbit maintenance), and even 'nano- satellite' development. Space station and other similar construction activities as well as Space Shuttle missions will also benefit from this technology. Some aspects of this research will be useful for cleaning up space debris at LEO (NASA Project ORION).

2000 NASA STTR Phase-I Proposal Proposal #: 000025

1. Research Topic: 05 Rocket Engine Test Operations 2. Project Title: Autonomous Control System Components

3. Small Business Concern 4. Principal Investigator
Name: Expert Microsystems, Inc. Name: Randall Bickford
Address: 7932 Country Trail Drive, Ste. 1
City: Orangevale
ST: CA Zip: 95662

5. Research Institution
Name: Argonne National Laboratory
Address: 9700 South Cass Avenue
City: Argonne
ST: IL Zip: 60439

6. Technical Abstract (Limit 200 words)

We will develop and demonstrate smart system component designs and algorithms enabling real-time autonomous control systems. Autonomous control system components will improve facility safety and reduce maintenance costs by enabling automated operation, system fault tolerance, on-condition maintenance and fewer false alarms. Our innovation consists of novel algorithms for fault detection and classification that enable real-time self-diagnostic surveillance and autonomous fault accommodation by a smart system component. Our approach combines smart sensor and actuator designs, previously developed for NASA Stennis Space Center, with patented multivariate state estimation algorithms from Argonne National Laboratory (ANL) that have been shown to provide high fidelity sensor and component failure detection for nuclear power plants and rocket engines. We will develop microcontroller-compatible versions of the ANL algorithms and combine these with a new Bayesian belief network expert system algorithm to automatically classify and respond to a detected fault of a smart sensor or control component. Phase I will culminate in demonstration of prototype smart components that perform automated self-diagnostic monitoring and fault management for a hazardous gas detection and control system applicable to a wide range of NASA ground test facilities, test articles and flight systems.

7. Potential Commercial Application(s)(Limit 200 words)

Autonomous control system components with embedded self-diagnostic fault management will enable improved safety, reduced maintenance cost, and optimal economics for many process control applications including aerospace ground test and vehicle systems, power plants, manufacturing equipment, and chemical processing plants. Requirements for autonomous fault management exist in all types of process critical control and safety systems where unexpected process interruptions due to sensor or control component failures or false alarms are unsafe or uneconomical. Our competitive advantage comes from the ability of each smart system component to automatically fuse information from numerous other sensors and components and interpret this data for autonomous control and self- diagnostic monitoring. We will initially develop a family of inter-operable smart gas leak detection and control components built around a standard industrial automation protocol. Our targeted market niche is safety, diagnostic and predictive maintenance monitoring for aerospace, utility and chemical process industries. Near term commercial applications include the next generation Reusable Launch Vehicle and supporting ground infrastructure as well as a wide variety of industrial process control systems.

2000 NASA STTR Phase-I Proposal Proposal #: 000079

1. Research Topic: 05 - Rocket Engine Test Operations 2. Project Title: Nanostructured High Temperature Optical Filters for Protection of
Spectroscopic Instrumentation

3. Small Business Concern 4. Principal Investigator
Name: NanoSonic, Inc. Name: Dr. Kristie L. Cooper
Address: PO Box 618
City: Christiansburg
ST: VA Zip: 24068

5. Research Institution
Name: Virginia Tech
Address: 340 Whittemore Hall
City: Blacksburg
ST: VA Zip: 24061

6. Technical Abstract (Limit 200 words)

The objective of the proposed STTR program is to develop and demonstrate robust, high temperature optical low-pass filters that may be formed directly on the windows of spectroscopic instrumentation used for rocket engine analysis. This work would solve the existing problem of excessive thermal loading of spectroscopic systems typically used to analyze rocket engine performance. Very high temperature metallic oxide nanocluster thin films with heat-blocking low- pass optical filtering functions and graded coefficients of thermal expansion would be formed by molecular-level electrostatic self-assembly processes demonstrated by Virginia Tech. This nanoscale self-assembly process inherently leads to the formation of low-defect structures, and the precise ability to achieve graded material properties in functional thin film coatings. During Phase I, NanoSonic would work with Virginia Tech to design, synthesize and demonstrate the optical, mechanical and thermal properties of these coatings on representative instrument window material substrates. Thermal performance of the optical filter coatings to temperatures as high as 1400 C are anticipated based on prior Virginia Tech research. A technology demonstrator test article will be fabricated and evaluated in cooperation with a major U.S. aerospace contractor. During Phase II, NanoSonic will develop methods for upscaling and transitioning the fabrication process to manufacturing.

7. Potential Commercial Application(s)(Limit 200 words)

The electrostatic self-assmbly process may be used to form a variety of high performance thin film materials and devices integrated directly onto structural and other functional components, including instrumentation filters. Low-cost ESA processing will allow the manufacturing of competitive aerospace optical, electronic, optoelectronic, sensor and actuator materials, devices and integrated function structures.

2000 NASA STTR Phase-I Proposal Proposal #: 000092

1. Research Topic: 05 - Rocket Engine Test Operations 2. Project Title: Nonintrusive Cryogenic Mass Flow Rate Sensor

3. Small Business Concern 4. Principal Investigator
Name: Florida Laser Systems Name: John Justak
Address: 50 Kindred St. Suite 311
City: Stuart
ST: FL Zip: 34994

5. Research Institution
Name: Florida Institute of Technology
Address: 150 West University Boulevard
City: Melbourne
ST: FL Zip: 32901

6. Technical Abstract (Limit 200 words)

The Stennis Space Center has identified a need to perform continuous facility and test article Health monitoring. Florida Laser Systems proposes the development of an innovative non-intrusive cryogenic mass flow rate sensor. The sensor system is based on the Extrinsic Fabry-Perot Interferometric (EFPI) sensor technology being refined at the Florida Institute of Technology. These fiberoptic based sensors are capable of determining several measurands including strain, temperature, pressure, force, vibration and shock. Their advantages include immunity to electromagnetic interference and cross talk, light weight, compact size, large bandwidth, corrosion resistance, ability to operate in hazardous and explosive environments, and remote real-time operation in cryogenic environments. This technology will be combined with an innovative mechanical design that will allow the non-intrusive detection of temperature, pressure, fluid velocity and mass flow rate. There are currently no products available for determining cryogenic mass flow-rate non-intrusively with high dynamic response. During phase I of this program proof of concept tests will be performed utilizing this technique.

7. Potential Commercial Application(s)(Limit 200 words)

This fiber optic sensor has substantial application to the commercial aviation industry. The sensors small size and low cost make it suitable for implantation into aircraft engines and attachment to aircraft skin and structural members. When integrated into the data stream of flight data recorders, the information derived would be beneficial in monitoring the life cycle performance of aircraft structures. In this way any flight activity resulting in increased stress on the aircraft could be detected and used to flag maintenance crews to perform visual inspections. In addition, changes in the vibration spectrum coupled with increased displacement in the sensor could provide warning of imminent failures in the aircraft components in time for replacement.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Phase I of this effort has proven key concepts of our proposed comprehensive health management solution: namely remote and shadow diagnosis over low-bandwidth network and prognosis based on statistical techniques. Our telediagnosis solution has been demonstrated to Honeywell and NASA-JSC, and is being considered for remote monitoring of the Space Station. It is also the centerpiece of Honeywell?s NOVA program (www.wipnova.com). Encouraged by the strong response from NASA and the Aerospace industry, we would like to develop on the shadow reasoning framework and statistical prognosis techniques from our Phase I effort and make RDS the most capable and scalable Intelligent Vehicle Health Management solution, onboard or remote. In Phase II we will add a novel new feature in our reasoner to explain in intuitive terms the diagnosis inferred by the reasoner. Such a capability will speed the adoption of the reasoner by experts, and will have applications in training. We will also address challenging issues of test sequencing in the presence of uncertainties and diagnosis in the presence of variable delay in detection of the fault(s) by tests. The new algorithms will be incorporated into our telediagnosis product, the Remote Diagnosis Server (www.teamqsi.com/rds).

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
Potential applications include monitoring and diagnosis of commercial and military jets, space systems, manufacturing systems, building heating ventilation and cooling systems, embedded automotive diagnosis, etc. The remarkable aspect of the proposed technology is that the data acquisition module can be implemented as single-board or even single chip solutions that can be mass produced and embedded in any networked system, while a network based server can monitor and assess health of thousands of such systems. This makes real-time diagnosis universally accessible at a low cost to a wide variety of applications, including home and office automation, smart appliances, battlefield soldier and equipment health monitoring, and in-home health care of patients in need of round the clock monitoring.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In Phase I we developed, integrated, and demonstrated a real-time adaptive navigation system, and a companion real-time adaptive guidance system for UAVs. The underlying project goal is to provide an aircraft with the capability to autonomously reroute itself in real time through dynamic hazard environments and still achieve its mission objectives. The adaptive naviagtion system uses an evolutionary algorithm to determine a set of waypoints which define an optimal discrete path between the current position and the final desired position. The waypoint location search space is constrained such that calculation of the performance index is very fast. The adaptive guidance module uses an adaptive critic to generate smooth, realizable paths between the waypoints. The critic utilizes information gathered off-line about the closed loop system to adapt the natural frequencies of a system of second order smoothing filters. The smoothing filters accept a series of step inputs (the waypoints) and output smooth paths between the waypoints. During the proposed Phase II STTR program we will take development of the system to the next level including analyzing its stability characteristics. The Phase II will culminate with an actual flight test demonstration/verification of the system on one of AACs research UAVs.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
As a result of the technology developed under this project, as well as the results of several other SBIR projects, we have received a three million-dollar investment from D.B. Captial. Part of this money is being committed to support the Phase II project. This project will result in two products. The first product will be a nonlinear adaptive critic guidance and control computer. The second product will be a software package that uses that tool for remote and autonomous operation of air vehicles. These products are an important part of an operator station for a group of Unmanned Aerial Vehicles (UAV). An obvious application is to Unmanned Combat Aerial Vehicles (UCAV). By enabling a ground station to more easily operate an aircraft, the efforts of a remote pilot can be minimized and response time can be reduced. These products are important to NASA because they can be applied to control of semi-autonomous agents of any sort, including spacecraft, rovers, and submersibles.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The overall objective of Phase II project is to enhance the capabilities of STARS and similar software to perform fast and accurate analysis of unsteady aerodynamic and aeroservoelastic (ASE) problems. Phase I work demonstrated the feasibility of using system identification to obtain accurate models of unsteady aerodynamics from STARS data and their use in ASE analysis. Phase II work encompasses: (i) reduced order modeling of fluid-structure interaction, (ii) modeling of aerodynamic uncertainties, (iii) bifurcation analysis, (iv) software development, (v) modeling and simulation of aeroelastic and aeroservoelastic problems of aircraft, (vi) modeling of material and geometric nonlinearites as applied to aircraft, and (vii) integration of STARS multidisciplinary software into design environment. The techniques and tools developed in these areas will be applied to a fluid-structure interaction problem such as F/A-18 tail buffet load alleviation problem. SSCI will develop software modules for aerodynamic modeling and ASE analysis. These advanced technology modules will be integrated into STARS software system and thus furthering its multidisciplinary features.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
System Identification-based modeling software has applications in flight testing, structural dynamics and modal analysis, combustion processes, aerodynamics, and process control. Nonlinear stability analysis software has applications in aircraft , jet engines, civil engineering structures, chemical instabilities, compressor stall, biology and communications.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Flight in continuous atmospheric turbulence can cause the pilot to be subjected to severe buffeting, leading to cumulative fatigue that can impair mission performance and endanger the aircraft and aircrew. Future military aircraft concepts have been proposed with planforms that are different from present configurations, resulting from the need for low radar cross-section. The low wing loading and low-level, high-speed flight operational requirements of some new configurations can lead to extreme buffeting of the aircrew when flying for relatively long periods in turbulence. In severe turbulence aircrew tolerance may be limited to only a few minutes of sustained performance before the pilot?s abilities become impaired. There is therefore a need for a means of assessing the likely ride quality characteristics for the proposed aircraft configurations and how susceptible they may be to this problem. It is proposed to apply analytical methods for quantifying cumulative aircrew fatigue by enhancement of existing analysis software. Further, it is proposed to develop a ride quality meter that can be used in practice to provide real time or off-line information about the extent of fatigue exposure either directly to the aircrew or to aircraft operational personnel.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
The objectives of the research are to provide enhancements to the NASA Dryden STARS analysis software package for commercial exploitation, and to develop a related product, a ride quality meter, to provide real time and/or off-line information about cumulative fatigue of aircrew and passengers during flight in continuous turbulence. Together, these objectives provide both service and product routes to commercialization.
The development of a gust and turbulence response capability in STARS will increase the application range at NASA Dryden for test and evaluation clearance work for future advanced aircraft projects. It will be suitable for potential sales and services marketing to various research facilities and aircraft manufacturers where similar advanced flight testing is undertaken.
The ride quality meter will be able to assess ride quality using a device that is independent of the aircraft systems. It will be of interest where excessive cumulative fatigue of the pilot clearly can potentially lead to failure to achieve the mission objectives and in the extreme can endanger the aircraft, and also for other aircrew and passenger comfort assessments. An existing vibration meter is to be used as the basis for the development, which will be carried out in collaboration with the original manufacturer.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This program addresses an opportunity to develop unique electronically tunable filters for multi- and hyperspectral imaging with characteristics that surpass all other present tunable filter technologies. The approach is based on holographically formed polymer dispersed liquid crystal material that were under development at Brown University for display and telecommunication applications. The H-PDLC constitute a stack of polymer and liquid crystal layers whose index of refraction can be changes by the application of electrical potential, thus changing the optical properties of the stack.

The operating requirements for displays and telecommunications, under development for several years at a significant level of funding, are vastly different from the requirements for tunable filter based sensors. The Phase-I STTR investigation, therefore, focused on identifying H-PDLC properties that need to be tailored to meet sensor requirements, and on developing technical approaches to implement such changes.

We have successfully completed this evaluation and developed plans for a series of modifications including special tailoring of material, assembly process changes and control steps, addition of other additives, etc., all of which will lead to a filter with the correct properties for the sensor applications. Under Phase-II, H-PDLCs optimized for multi- and hyperspectral sensor applications will be assembled and incorporated into sensor prototypes for laboratory and field testing.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
The H-PDLC promise is in a unique combination of very fast switching filter, high throughput and most important of all, low production cost. These characteristics open the possibilities for several commercial and NASA applications. OKSI is already working with a commercial partner that will invest in Phase-III provided the Phase-II reaches certain milestones. The sensors that will be developed with this partner will be used for precision agriculture on farm equipment. This partner has already invested in complementary research at OKSI sums that are greater than the Phase-I STTR value, and continues to invest in sensor development.

The properties of these tunable filters also make them a perfect match for future NASA spaceborne Earth observing sensors. In such applications, the high throughput and fast switching time match the sensor requirements for typical operating characteristics of sensors on board sun-synchronous, polar-orbit platforms.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The elemental composition of meteors is one of the keys to understanding their origin and in turn the evolution of the solar system. Spectroscopic measurement of the emission spectra of meteors as they are heated by entry into the Earth's atmosphere can yield this information. An objective-grating spectrograph instrument payload designed to capture the ultraviolet emission spectra of metoers is proposed. This Shuttle and or Space Station payload will detect and record randomly occurring transient upper atmosphere phenomena such as meteors and upper atmospheric lightning. In this Phase II effort Princeton Scientific Instruments will complete the design and fabrication of the high frame rate CCD camera portion of the payload. Villanova University will complete their thermal analysis and design to include the proposed International Space Station payload "SUMS" (Slitless UV Meteor Spectrometer). It should be noted that high speed, real time, image analysis is of broad interest with applications such as missile guidance and cell morphology in biological image data reduction and image analysis.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
The direct application of the proposed research and development is a Shuttle and International Space Station instrument to acquire the ultraviolet spectrum of meteors, Sprites, and other targets of opportunity when viewing the Earth's atmosphere, in the UV. While these NASA-commercial applications are sufficient justification for this program, there are other commercial market reasons as well. This research and development is applicable to the increasing use of imaging in industrial, scientfic, and military applications, and the collateral need for real-time image processing to make decisions in real time. There is an increasing need to recognize, respond to and measure transient events and to do this at high speed, high resolution and good photometric fidelity. The software algorithms for detecting and characterizing rapidly changing spectral images and differentiating between meteors and Sprites will be applicable to other problems. One example is real time analysis of rocket engine exhaust plume images and spectra to make quick decisions as to whether to proceed with a missile launch. The ultraviolet image sensor and optics are also of commercial interest. There is increasing interest in the hard UV for achieving smaller dimensions in photolithography to make higher density integrated circuits.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Inflatable or self-deployable systems offer the only practical way to achieve space deployed antennas with low mass at large aperture. In this Phase I program, open-celled rigid polyurethane foams were developed for use in self-deploying antenna structures. Advantages of such a system relative to current systems include high volumetric efficiency of packing, inherent restoring force, low (or no) outgassing, low thermal conductivity, high dynamic damping, mechanical isotropy, infinite shelf life, and easy fabrication with methods amenable to construction of large structures (i.e., spraying).
In Phase I, it was demonstrated that rigid polyurethane foams with a variety of glass transition temperatures (Tgs) can be easily formulated using commercially available urethane components; foam systems with Tgs ranging from 30 to 150?C were prepared. The ability to tailor the system Tg is a critical element in tailoring the deployment of these systems on-orbit. The ability to create open cells in rigid polyurethane foams was also demonstrated; a sample was prepared with greater than 50% open cell content. Open-celled foams are critical for achieving high packing efficiency and maintaining dimensional stability of the structures during thermal cycling. It was also demonstrated during the course of the Phase I program that metallized open-celled foams can perform well for antenna applications. RF insertion loss testing in the frequency range 12-17 GHz on foam samples coated with approximately 3.5 microns of metal indicated a minor loss of 0.2 dB, clearly demonstrating the promise of metallized foams for antenna applications.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
Large space-deployed antennas are receiving a great deal of interest in both the NASA and commercial sectors. The reason is the increasing need for a variety of applications that include communications, long baseline interferometry, micro-spacecraft, and DoD space-based radar. Investigators in these areas identify the need for structures up to tens of meters in aperture size and 1 to 90 GHz operations.

The eventual markets for communications antennas and radars are extremely large. In the commercial sector, over 200 satellites are expected to be launched in the next 10 years to meet consumer demand for cellular phones and other communication devices. A large number of military satellites are also expected to be launched in that timeframe. Current mesh antennas sell for $25-40 million each. Self-deploying antennas using the foam technology demonstrated in this Phase I program should be priced in the $3-4 million range each. As such, self-deploying and inflatable spacecraft should claim the majority of the market for antennas and radiometers.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Our Phase-I investigations were completely successful and gave new life to the concept of ablative laser propulsion (ALP). New measurement techniques and equipment have been incorporated into the basic experimental apparatus constructed in Phase I, and this improvement will add considerably to our capabilities and to the fundamental understanding of laser-matter interactions. Three materials (lead, aluminum, and carbon) showed the greatest promise for ALP in Phase I and we will concentrate on these in Phase II. Our interest has previously been directed toward investigating the fundamental physics of ALP and we believe that the important concepts are now understood well enough to take the next step and actually produce a flight demonstration of a prototype ALP-powered craft. Phase II will begin with further investigation of the selected materials and will conclude with the construction and flight of a laser-propelled craft of our own design. The proposed work will demonstrate the viability of the ALP concept.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
Commercial applications of ALP fall into two broad categories: satellite launches and satellite altitude maintenance. A laser-propelled craft could be used for temporary global positioning satellite applications; launching of specialized cellular telephone communications antennae for communications with remote areas and satellite-to-satellite communications; rapid delivery of tools and components for Space Shuttle or Space Station missions; remote visual inspection and diagnostics of satellites; maintenance of low orbits, using periodic boosts from the ground, for controlled-altitude data gathering in global hydrology applications and high-altitude weather monitoring; and cost-effective, efficient clearing of space debris. Secure communications would be possible by storing the information in a small laser-launched payload that would communicate with the satellite when it is within a short range, obviating the use of signals transmitted from the ground and making interception of the signal impossible using ground-based antennae. In addition to relevant NASA programs, this project has direct potential application to DoD BMD programs. In particular, it is relevant to divert motors for miniature kill vehicles employed in mid-course systems such as Trajectory-Optimized High-Altitude Targeting (TOPHAT), a system authorized by Congress for funding of its Concept Development phase in FY02.

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The objective of the proposed STTR program is to develop and demonstrate
robust, high temperature optical low-pass filters that may be formed
directly on the windows of spectroscopic instrumentation used for rocket
engine analysis. This work would solve the existing problem of excessive
thermal loading of spectroscopic systems typically used to analyze rocket
engine performance. Very high temperature metallic oxide nanocluster thin
films with heat-blocking low-pass optical filtering functions and graded
coefficients of thermal expansion would be formed by molecular-level
electrostatic self-assembly processes demonstrated by Virginia Tech. This
nanoscale self-assembly process inherently leads to the formation of low-
defect structures, and the precise ability to achieve graded material
properties in functional thin film coatings. During Phase II, NanoSonic
would work with Virginia Tech to design, synthesize and demonstrate the
optical, mechanical and thermal properties of these coatings on
representative instrument window material substrates. Thermal performance
of the optical filter coatings to temperatures as high as 1400 C are
anticipated based on prior Virginia Tech research. A technology
demonstrator test article will be fabricated and evaluated in cooperation
with a major U.S. aerospace contractor.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 200 WORDS)
The ESA process may be used to form a variety of high performance thin film materials onto structural and other functional components, including instrumentation filters. Low-cost ESA processing will allow the manufacturing of competitive aerospace optical electronic, optoelectronic, sensor and actuator materials and devices.