NASA 2002 STTR Phase 1 Solicitation

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Ibex Healthdata Systems	NAME:	Johns Hopkins University
ADDRESS:	5600 North River Road Suite 150	ADDRESS:	720 Rutland Avenue
CITY:	Michael VanRooyen	CITY:	Baltimore
STATE/ZIP:	IL   60618 - 5102	STATE/ZIP:	MD   21205 - 2109
PHONE:	( 847 ) 993 - 2200	PHONE:	( 410 ) 614 - 3637

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Michael VanRooyen , mvanrooy@jhmi.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
The purpose of this project is to develop a portable, hands free device for emergency medical decision-making support to be used in remote or confined settings by non-physician providers. Phase I of the project will entail the development of a voice-activated device that will utilize an intelligent algorithm to provide guidance in establishing an emergent airway. The interactive, hands free software will process requests for assistance based on verbal prompts and algorithmic decision-making. The device will allow the crew to attend to the patient while receiving verbal instruction, guidance and graphic representations where it will be helpful in performing procedures. Testing in the Johns Hopkins Department of Emergency Medicine, in a real time clinical setting, will validate the efficacy of this mode of technology. Phase I of the project will focus on validation of the proposed technology as well as development of the necessary software and hardware into a beta-type device. In Phase II, we will produce the first generation software and hardware for hands-free, interactive medical decision for use in any situation in which an algorithmic guide would be useful.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The medical decision software, the algorithmic approach and the hands free technology will be integrated to create a product that will have wide-ranging uses in emergency situations. Following development and validation of the technology and software the product will be easily marketed and licensed to a medical/para-medical organization or medical equipment company. This technology?s greatest impact will be in the general population, with remote or mobile care environments being the target. First Aid publications may be impractical for the layperson, faced with illness or injury in remote locations and with precious little time. Cruise ships, oilrigs, reservations, remote military bases, municipalities, school districts and expeditions are obvious locations for the hands-free device. The potential of using such a system to save lives or to stabilize someone with an illness or injury prior to the arrival of trained emergency personnel is very real.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
To date, the only U.S. on/peri-orbit emergencies have been airway ones; Apollo-Soyuz inhalation injuries and explosive decompression and fire on the Mir. The frequent loss of communication events with ISS means that crews will be forced to operate more independently and a mission to Mars will necessitate a degree of autonomy never before achieved. It is not logistically possible to make an emergency medicine physician part of every crew so NASA relies on the C.M.O. program, which, in essence, places a layperson in charge of life or death decisions. The C.M.O.s have no clinical acumen on which to base their decisions, yet they are expected to make medical judgments. The device would allow laypersons to easily, reliably and quickly treat patients using sound, validated algorithms; the mainstay of pre-hospital care. Additionally, it would free the C.M.O. from having to manually locate and then read the appropriate guide.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Scientific Systems Co Inc	NAME:	University of California
ADDRESS:	500 West Cummings Park Suite 3950	ADDRESS:	336 Sproul Hall #5940
CITY:	Jovan D. Boskovic/Raman K. Mehra	CITY:	Berkeley
STATE/ZIP:	MA   01801 - 6580	STATE/ZIP:	CA   94720 - 5940
PHONE:	( 781 ) 933 - 5355	PHONE:	( 510 ) 642 - 8114

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Jovan D. Boskovic/Raman K. Mehra , rkm@ssci.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
The overall goal of this project is to develop a robust autonomous intelligent real-time system for Uninhabited Aerial Combat Vehicles (UCAV) to achieve the desired flight performance by integrating effective Health Monitoring and Failure Detection and Identification (HM-FDI) with optimal control strategies to accommodate unanticipated failures and multiple modes of operation. SSCI has already done ground-breaking research in this area, which will be fully leveraged to further advance the state-of-the-art in Intelligent Autonomy. In order to achieve these objectives, we plan to carry out the following tasks in collaboration with Professor Karl Hedrick of the University of California, Berkeley: (i) Formulate the HM-FDIR problem in multiple operating regimes for UCAVs; (ii) Derive algorithms for real-time calculation of Achievable Dynamic Performance (ADP) and reachable sets; (iii) Implement an efficient robust HM-FDIR system for the X-45A as a test vehicle; (iv) Implement higher decision-making levels including the trajectory generation, path planning and mission planning levels; and (v) Evaluate the performance of the proposed autonomous intelligent flight control and management system using a X-45A (Boeing-Darpa UCAV) simulation. NASA Ames Rotorcraft Research Center (Dr. Mark Tischler) will provide technical evaluation and flight demonstration support during Phase II of the project.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Current applications of the proposed autonomous intelligent flight control and management system are in the area of intelligent autonomy for single and multiple Unmanned Aerial Vehicles (UAV), and Uninhabited Combat Aerial Vehicles (UCAV). Autonomous intelligent control systems will find wide applications in other programs such as Air Traffic Control and Intelligent Vehicle Highways. Related applications are envisioned in the areas of robotics, and unmanned ground, underwater and surface vehicles.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The proposed autonomous intelligent flight control and management system and related technologies are critical for realizing the vision of the NASA Aviation Safety Program to reduce the aviation fatal accident rate by a factor of 5 by year 2007, and by a factor of 10 by year 2022. The technologies developed under this project are expected to predict and prevent mechanical and software malfunctions, and reconfigure the control when they happen. Our technologies will also help eliminate accidents involving hazardous weather and controlled flight into rough terrain.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	AeroAstro Corp	NAME:	University of Colorado
ADDRESS:	20145 Ashbrook Place	ADDRESS:	527 UCB
CITY:	Raymond Zenick	CITY:	Boulder
STATE/ZIP:	VA   20147 - 3373	STATE/ZIP:	CO   80309 - 0572
PHONE:	( 703 ) 723 - 9800	PHONE:	( 303 ) 492 - 2561

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Raymond Zenick , ray.zenick@aeroastro.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
AeroAstro and the University of Colorado propose to develop an autonomous satellite power control system to dynamically monitor, schedule and distribute power resources on microsatellites , while remaining sensitive to the mission objectives. The Autonomous Power Scheduler (APS) will maximize power efficiency and availability while being situationally-aware of bus conditions. The concept system would employ a component-based model to diagnose system status with embedded logic, and respond to anomalous power states and initiate recovery or mitigation actions pending further ground command, while remaining within defined spacecraft state-of-health parameters. The APS represents an innovative paradigm shift from conventional design practices. Conventionally, spacecraft power is managed using static, non-intelligent designs based on worst-case, lowest power scenarios, and subsystem operational power allocations are made with ?man-in-the-loop? decisions through transmitted commands. What is proposed here is a method to control primary power in an intelligent, semi- or fully autonomous fashion maximizing mission capability and performance. Appropriate power will be distributed when and where it is most needed. The autonomy of the APS concept and the resulting reduction in requirements for ?man-in-the-loop? decision making makes it particularly applicable to NASA?s future generation of distributed constellation missions.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Due to the autonomous nature of APS, we envision a wide range of power-limited, mobile platform applications. This system will make better use of the available power resources to reduce weight and increase system life. Weight can be reduced by requiring less energy stores to meet basic mission objectives. Smaller batteries or less fuel may be required to meet operational goals. Weight reduction often equates to increased endurance for ground-based, autonomous systems. Two specific areas of ground-based systems that can benefit from reduced mass and increased autonomy are Unmanned Aerial Vehicles (UAVs) and Deployable Sensors. UAVs are operated remotely or, at certain times, completely autonomously. The less weight, the further range and flight duration that is possible. Deployable Sensors are most commonly used for theater applications. They are used to track and identify the source of ground movements. Reduced weight allows the sensors to be deployed with minimum manpower in difficult areas for vehicle access.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
Over the next ten years NASA has planned numerous upcoming small satellite for near Earth and deep space missions which have a need for low mass, power efficient, survivable components and subsystems such as their electric power subsystems. The majority of these missions will be severely restricted in their ability to maintain batteries due to their limited power gathering capabilities, in particularly for deep space and constellation missions such as the Magnetospheric Constellation mission. These missions require components optimized for mass, power, and cost, while satisfying the reliability and efficiency needed for single string and deep space missions. To fulfill these requirements we feel the development of a highly efficient, semi-autonomous or even fully autonomous electrical power system based on APS which we are proposing will be beneficial and significantly contribute to life and capability of these missions.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Intelligent Automation, Inc.	NAME:	University of Cincinnati
ADDRESS:	7519 Standish Place Suite 200	ADDRESS:	One Edwards Center, Suite 7148
CITY:	Dr. Xiaodong Zhang	CITY:	Cincinnati
STATE/ZIP:	MD   20855 - 2785	STATE/ZIP:	OH   45221 - 0627
PHONE:	( 301 ) 294 - 5200	PHONE:	( 513 ) 556 - 4359

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Xiaodong Zhang , xzhang@i-a-i.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Here Intelligent Automation, Inc. (IAI) and its subcontractor, Prof. Marios M. Polycarpou of University of Cincinnati, propose a new approach for designing intelligent health monitoring supervisor and fault-tolerant controllers for nonlinear air vehicles operating in multiple regimes. First, a novel on-line monitoring system performs model validation and fault diagnosis. The monitor automatically distinguishes between fault occurrence and normal operating regime switching and determines the particular fault type after fault detection. It can directly deal with nonlinear fault models, handle unstructured modeling uncertainty and unanticipated failures, and is suitable for real-time operations. Second, a new reconfiguration supervisor makes decision regarding controller reconfiguration and resource management. The supervisor provides a unified framework for fault detection, fault isolation and fault-tolerant control, which is still lacking in literature according to a recent survey paper. Another new feature is that the effect of fault detection time on system stability has been explicitly taken into account. Third, a controller suite with novel robust adaptive controllers to deal with different failure modes in each regime is proposed. The fault-tolerant controllers are designed based on recently developed nonlinear adaptive/neural control techniques. The controller guarantees closed-loop stability for a general class of nonlinear systems. Moreover, it has an on-line tuning scheme that eliminates off-line training of the neural net, which is extremely important in rapidly varying environment.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
There are many potential NASA applications for this innovation, for instance, health monitoring of spacecraft, reusable launch vehicles, flight control systems, engine, etc.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The proposed method combines several breakthroughs in fault detection and isolation, and robust adaptive neural control techniques in a unified framework. The proposed method can be used for applications such as aircraft, motors, robots, submarines, and nuclear reactors. We expect the method to be widely used in many commercial and military applications.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Intelligent Automation, Inc.	NAME:	Vijay Kumar
ADDRESS:	7519 Standish Place Suite 200	ADDRESS:	113 Towne Building, 220 South 33rd St.
CITY:	Dr. Donald Myers	CITY:	Philadelphia
STATE/ZIP:	MD   20855 - 2785	STATE/ZIP:	PA   19104 - 6391
PHONE:	( 301 ) 294 - 5200	PHONE:	( 215 ) 898 - 8241

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Donald Myers , dmyers@i-a-i.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
When using autonomous systems in unknown environments, it will not be possible to anticipate all scenarios in which the devices will be involved and pre-program their response. It will be increasingly incumbent on the machines to ascertain the intent of the users and be able to learn from user actions to improve performance. Intelligent Automation Inc. (IAI) and the University of Pennsylvania (Penn) will explore several new algorithms that would enable a machine to learn some of the high-level strategies that humans use to control and monitor robotic devices remotely. By collecting data from human teleoperation, we propose learning a mode controlling mixture model that would approximate the decision boundaries that human operators use to switch strategies. This idea will take the skill and intelligence inherent in human operators and provide the basis for how the controller can adjust during autonomous operation. In order to optimize the parameters of the controllers, we propose using optimization techniques inspired from genetic algorithms (GAs) to find globally optimal parameters within these modes. To further optimize the learned mode switching behavior, we also plan to incorporate online reinforcement learning (RL) techniques to adaptively tune the learned parameters.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
As NASA extends its reach, it will be necessary to use unmanned vehicles to facilitate autonomous exploration and to support telepresence for human personnel. Since at such great distance, human interaction will be limited, these vehicles must learn both on their own and from the limited interaction when human assistance is possible. Learning from human demonstration can be used to automatically ?program? robots for space missions during the earth-based training periods when humans are also learning how to use the robots. Beyond robots, as the functions of all mission subsystems become increasingly complex, forms of adaptive learning will be necessary.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
These technologies will be applicable to commercial avionics systems and control and decision-making systems. The technology developed will provide greater integration at the system level, more affordable configurations, more efficient and supportable flight control architectures, and the ability to operate air vehicles safely and effectively in an inter-netted environment. All commercial aircraft manufacturers, suppliers, and airline would benefit from this technology.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	EMBEDDED RESEARCH SOLUTIONS, LLC	NAME:	Johns Hopkins Univ Applied Physics Lab
ADDRESS:	201 Defense Highway, Suite 202	ADDRESS:	11100 Johns Hopkins Road
CITY:	Dr. David B. Stewart	CITY:	Laurel
STATE/ZIP:	MD   21401 - 7096	STATE/ZIP:	MD   20723 - 6099
PHONE:	( 410 ) 571 - 7950	PHONE:	( 240 ) 228 - 7300

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. David B. Stewart , dstewart@embedded-zone.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
The proposed innovation is a solution that combines efficient dynamically
reconfigurable embedded software and extensions to model-based reasoning (MBR)to enable on-board planning, real-time control, and failure management of complex autonomous systems. The solution leverages Embedded Research Solutions (ERS)'s expertise in the area of embedded real-time systems and merges recent advances by Johns Hopkins University Applied Physics Laboratory (JHU/APL) and the Massachusetts Institute of Technology (MIT) in the area of MBR. ERS has used a state-based approach to building dynamically reconfigurably software, through the creation of resource-savvy real-time frameworks and software components for control and communication applications. This technology provides the underpinnings to incorporate JHU/APL's newest results in MBR, namely expressive state definitions, into MIT's second generation MBR system TITAN, and shrinking the resulting reasoning engine to a size suitable for on-board real-time processing in autonomous systems.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Areas of application and special interest to ERS include pervasive computing, environmental monitoring and machine health and diagnostics.
It is anticipated that this effort will define at least two viable commercial embodiments of the technologies: 1) a platform for embedded systems that includes MBR for planning and diagnostics and 2) tools that support the platform.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The solution directly addresses NASA's needs described in STTR 2002 Topic 1, subtopic, "Technologies for Autonomous Spacecraft, Rovers, and Other Complex Systems." It provides both an onboard capability for synthesizing operational plans from high-level goals, and on-board MBR methods to diagnose system health and then automatically reconfigure to respond to failures.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Nielsen Engineering & Research, Inc.	NAME:	University of Florida
ADDRESS:	526 Clyde Ave	ADDRESS:	P.O. Box 115500, 223 Grinter Hall
CITY:	Dr. Patrick Reisenthel	CITY:	Gainsville
STATE/ZIP:	CA   94043 - 2212	STATE/ZIP:	FL   32611 - 5500
PHONE:	( 650 ) 968 - 9457	PHONE:	( 352 ) 392 - 1582

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Patrick Reisenthel , phr@nearinc.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Aeroelastic studies, such as the prediction of flutter boundaries and limit cycle oscillations, play a critical role in aircraft safety and design. To perform these analyses with the required accuracy, nonlinear aerodynamic, and possibly nonlinear structural, effects must be included. Furthermore, these effects must be considered early in the design cycle in order to reduce life cycle costs. The Volterra theory of nonlinear systems addresses the need for efficient and accurate reduced-order modeling of unsteady aeroelastic effects. A critical problem, however, is the difficulty of identifying the Volterra kernels. We propose a new identification method that is suitable for use with wind-tunnel or flight-test data. The proposed innovation is a time-domain multiresolution Volterra kernel identification method which uses physically realizable inputs, is robust with respect to noise, and minimizes or eliminates the need for analytical assumptions. The Phase I work will integrate an existing kernel extraction technique with new multiresolution signal decomposition approaches and demonstrate the combined method on experimental data. The resulting technology is expected to facilitate linear and nonlinear system identification for aeroservoelastic analysis and design and will be applied, in Phase II, to data from the F18-AAW program.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The market for efficient aeroelastic analysis tools is driven by new aircraft, missile, and reusable launch vehicle design and by the need for multiple aeroelastic analyses over time as a consequence of aircraft modifications and expanded/changing missions. The proposed linear and nonlinear identification system has a broad range of applications, including but not limited to, electromagnetic pulse hardening of aircraft systems, computational electromagnetics (photopic switching devices, ultrawideband technology), noise reduction (acoustic liners), polymer processing (extrusion blow molding), and earthquake and geoenvironmental engineering.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The proposed multiresolution-based identification system provides a unique capability that will extend the usefulness of wind-tunnel and flight-test data by producing compact, reduced-order models for use in aeroelastic analyses. The formulation of reduced-order models in aeroelasticity is important for several reasons: (1) cost reduction and speed-up of preliminary design cycles, (2) understanding of nonlinear behavior and elimination of later surprises, and (3) real-time aeroservoelastic control applications. The proposed technology supports NASA's goal of increasing safety and efficiency of flight testing.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Advanced Engineering Solutions	NAME:	Oklahoma State University
ADDRESS:	670 Silver Spur Rd. Suite 209	ADDRESS:	218 Engineering North
CITY:	Andrew S. Arena	CITY:	Stillwater
STATE/ZIP:	CA   90274 - 3639	STATE/ZIP:	OK   74078 - 0002
PHONE:	( 310 ) 704 - 7490	PHONE:	( 405 ) 744 - 7873

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Andrew S. Arena , aarena@okstate.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
The ability to quickly estimate flight vehicle behavior in an operational environment is particularly important since engineers from a variety of disciplines require accurate predictions in order to plan flight test experiments, expand aircraft operating envelopes safely, and have access to diagnostic methods when problems arise. In order to minimize risks, and to maximize compatibility with present NASA efforts and personnel, the innovative software to be created and marketed through this effort will be written to ?seamlessly? interface with the NASA STARS suite of codes. This approach will also allow a focus on the new and innovative techniques to be implemented during this effort without the need to reproduce analysis tools which are already highly developed and validated. At the same time, this increases commercial viability of the product due to the broad distribution and familiarity with the STARS codes in the government and academic sectors. The products ultimately produced from this effort will have the capability for CFD-based multi-disciplinary analysis of flight vehicles including linear and non-linear aeroservoelastic analysis. Special emphasis will be placed on developing tools which may be used by engineers in a flight test environment where rapid turnaround times are critical.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Multidisciplinary modeling techniques and software proposed will reduce the design cycle time resulting in significant savings in R&D. Potential dual-use application will include the design of all types of commercial aircraft, jet engines, automobile and engine components, and civil engineering structures. Significant effort will be made to promote commercialization of the products developed in Phase I and Phase II for application in general aviation aircraft manufacturing industry, where the cost of R&D makes a great portion of the total budget and businesses are eager to adopt tools and methods to reduce design cycle time and cost.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
High-performance flight vehicles that are currently being designed have unprecedented levels of interactions of structures, aerodynamics, propulsion, and flight controls. This will impose considerable design margins for stability and control performance. Therefore, an accurate simulation of flight characteristics of these flight vehicles, prior to testing, will ensure safety of the craft and the crew, relaxes design margin requirements, improve performance, and cut cost. The novel techniques and tools proposed here will be of immediate use for achieving these objectives in NASA and military applications, as stand alone, or as an addition to the existing tools such as STARS.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Zona Technology Inc	NAME:	University of Florida
ADDRESS:	7430 E. Stetson Drive, Suite 205	ADDRESS:	PO Box 116250
CITY:	Dario Baldelli	CITY:	Gainesville
STATE/ZIP:	AZ   85251 - 3540	STATE/ZIP:	FL   32611 - 9500
PHONE:	( 480 ) 945 - 9988	PHONE:	( 352 ) 392 - 6745

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dario Baldelli , dario@zonatech.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
ZONA Technology and the University of Florida propose an R&D effort to establish a Robust Aeroservoelastic Toolbox (RASET) with emphasis on nonlinear identification, modeling and analysis. The RASET will serve the next-generation flutterometer. The toolbox augments the current mu-method analysis with nonlinear operators so limit cycle oscillations (LCO) can be predicted. Several representations of these nonlinearities, such as Volterra kernels and describing functions, are proposed. Flight data will be used to identify optimal estimates of these nonlinear representations and associated uncertainty. The resulting model will be used to compute stability margins that reflect both flutter and LCO instabilities. In Phase I, the developed RASET will formulate the foundation for the next-generation flutterometer. This toolbox will allow the computation of robust stability margins associated with explosive flutter or limit cycle oscillations (LCO). A feasibility study is proposed to validate this advanced flutterometer concept. In Phase II, RASET would be updated with advanced routines for system modeling, LFT representation, identification of nonlinearity, estimation of uncertainty, and stability analysis. The aim of the current approach is that the toolbox should be invaluable to the flight test community by extending the current modeling capabilities to include nonlinearity identified from flight data.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
ZONA envisions that the proposed research will result in a commercial product which can greatly impact the flight test community. The work toolbox could become a standard analysis package for aeroservoelastic instability and flutter clearance. If successful, the proposed methodology for a nonlinear flutterometer will complement and enhance the current capability for predicting instabilities during envelope expansion. ZONA plans to package the toolbox as stand-alone software for all phases, pre-flight to post-flight, of a test. A wide variety of military and commercial aircraft can adopt this analysis capability such as fighters, transports, UAV, and scaled-prototype versions. The potential customer base includes current ZONA customers including aerospace firms, DoD, NASA, USAF, USN, and flight test centers. Marketing the toolbox will be simplified by taking advantage of ZONA's current extensive customer network. In addition, these tools for data-based modeling and analysis of nonlinearities are needed for automotive, manufacturing, nautical, and materials applications.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
NASA, especially Dryden Flight Research Center, invests considerable resources into flight testing. The proposed Robust Aeroservoelastic Toolbox would increase the efficiency of such testing. The increased efficiency would result from reducing time and cost of the testing while, most importantly, increasing safety. The toolbox will provide an advanced on-line prediction capability for aeroservoelastic instabilities that identifies nonlinear dynamics directly from flight data. Such capability will dramatically reduce the risk of encountering unexpected instabilities associated with unmodeled nonlinearities.
Thus, the tools will be of use for aeroelasticians, aerodynamicists, and control engineers. The proposed toolbox could support NASA and partners on upcoming envelope expansion of the F/A-18 AAW, F-15 IFF, and UCAV at NASA Dryden along with the F-22 at Edwards Air Force Base.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Stirling Dynamics Inc	NAME:	University of California Santa Barbara
ADDRESS:	4030 Lake Washington Blvd NE, 205	ADDRESS:	University of California
CITY:	Pio Fitzgerald	CITY:	Santa Barbara
STATE/ZIP:	WA   98033 - 7870	STATE/ZIP:	CA   93106 - 2050
PHONE:	( 425 ) 827 - 7476	PHONE:	( 805 ) 893 - 3890

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Pio Fitzgerald , pfitzgerald@stirling-dynamics.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Future research into advanced air vehicle designs will benefit from the continued improvement of analysis methods and software tools. A research program is proposed to provide enhanced capabilities to the NASA STARS software package in two key areas. These are; the addition of a control system toolbox including classical and modern control system design procedures, and the introduction of parallelization into the computational process. Since most current and planned high performance air vehicles depend heavily on their flight control systems, and their structure is designed for low weight, and an efficient propulsion system is essential, a fully integrated analysis is required in the design process to produce overall optimized performance. All these factors motivate the need for the newly proposed developments. Also, as more complexity is added to the analysis software, computer throughput productivity inevitably drops, despite computer advances, and this drives the need for parallelization. The capability resulting from this research promises significant increases in the scope and efficiency of STARS such that its use will have a greater range of application and will contribute to the assurance of safety in flight testing. The planned reusable launch vehicle will be the initial application objective of the enhanced software.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Multidisciplinary analysis simulation packages, such as STARS, are in considerable demand both inside and outside of NASA. They are not confined to applications in the aeronautics and space fields, but are of high interest to many product areas. The proposed enhancements will increase the attraction of STARS as a commercial tool for these other industries, such as marine, automotive and civil engineering. A further spin-off benefit is the potential application to Stirling Dynamics? in-house software package, Hypac, which can use the same control and parallelization techniques, and which the company plans to offer as a commercial product.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
NASA will benefit from the expanded analysis capability and increased computational throughput made available by the addition of control systems and parallelization to STARS. NASA Dryden conducts research into the most advanced air vehicles and must maintain software analysis tools of the highest quality to assure safety of flight testing, to which the planned STARS enhancements contribute. The enhanced STARS tool can be offered to other NASA facilities, expanding the user base and ensuring its continued growth. The reusable launch vehicle is a suitable first application, such that the benefit from this STTR project has an early impact.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Mechanical Solutions Inc	NAME:	Rutgers University
ADDRESS:	1719 Route 10 East, Suite 205	ADDRESS:	98 Brett Rd
CITY:	Sherif Aly	CITY:	Piscataway
STATE/ZIP:	NJ   07054 - 4507	STATE/ZIP:	NJ   08854 - 8058
PHONE:	( 973 ) 326 - 9920	PHONE:	( 732 ) 445 - 0504

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Sherif Aly , Sherif.Aly@mechsol.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Modern airfoil design evaluation requires accurate analysis of both structural dynamic as well as fluid oscillatory response. The level of calculation reliability has, in principle, increased significantly, so that now the opportunity exists to optimize aeroelastic behavior in the design stage. This is made possible by new high fidelity structural and CFD tools which predict airfoil steady and transient aero loading, as well as stress and vibrational behavior. However, while single runs of the applicable COTS codes can be parallel-processed reasonably quickly, computational time becomes pacing in airfoil development due to the many iterations that must be performed in order to optimize lift/weight ratios, while ensuring that aeroelastic flutter is avoided. Automated Multi-Disciplinary Optimization (MDO) computer algorithms can address this analysis bottleneck, but attempts to date have had only limited success, due to problems with slow convergence and local minima. MSI will locate the true minimum of the multi-disciplinary objective function through a unique optimization approach making appropriate use of stochastic methods. The technique accounts for design constraints, such as component thicknesses and aspect ratios, for airfoils that are practical and cost-effective. Using MSI?s Stochastic Optimization of Airfoil Response (SOAR) methodology, time-savings of several-fold are expected in airfoil design optimization.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The SOAR algorithm may be applied to commercial aircraft airfoil design and development, for both large and small aircraft. The procedure may be used for winged aircraft or helicopters. In addition, with further commercial development in Phase III, the approach may be applied to other transportation fields, as well as to engineering optimization in general.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The SOAR approach is applicable to re-usable launch vehicles, efficient UAV development, new civilian and military aircraft, and improvement studies for existing aircraft, in particular those challenged by issues of relative weight or inappropriate aeroelastic response. In Phase III, other applications can be explored, such as entire airframe optimization.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Vexcel Corp	NAME:	Pennsylvania State University
ADDRESS:	4909 Nautilus Court	ADDRESS:	442 Deike Bldg
CITY:	Paul Bodnar	CITY:	University Park
STATE/ZIP:	CO   80301 - 3242	STATE/ZIP:	PA   16802 - 2711
PHONE:	( 303 ) 583 - 0225	PHONE:	( 814 ) 863 - 6742

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Paul Bodnar , bodnar@vexcel.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
In November 1998 a network of seismic stations was deployed by S. Anandakrishnan (now at Penn State) and others in West Antarctica. These autonomous stations returned state-of-health data via satellite, and stored high-volume instrument data for later retrieval. The satellite links demonstrated a novel and sophisticated application of technology to the problem of retrieving in situ data from harsh remote terrestrial environments. Using these Antarctic seismic stations as a starting point, we propose to make a second innovative leap in remote instrumentation by creating intelligent, self-organizing instrument networks capable of recording, storing, processing, and returning high volumes of geophysical data from the field. These instruments will be built from low-cost COTS components, will intercommunicate via wireless microwave protocol, and will return data through a high-rate telemetry system. As such the proposed instrument network will drastically reduce the costs of field instrumentation and data recovery. The notion of an intelligent autonomous array of sensors has gained in popularity and momentum in the scientific world with new technological advances. We believe this is the opportunity to implement such a concept, with considerable but surmountable technical challenges, direct application to NASA's Earth Science Enterprise, and tremendous potential for future commercial application.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
We propose to develop an intelligent self-organizing autonomous wireless network of sensor stations. The technology to be developed under this proposal would enhance both the reliability and cost of any distributed sensor array. Examples of commercialization potential include rapid and complete monitoring of an urban power grid or establishment of an environmental pollution/contamination warning system. This technology could also be used for traffic monitoring in order to optimize traffic flow, and sensors could also be used in this context for law-enforcement and homeland security purposes.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
This proposed research and commercial development is directly applicable to the future exploration of our solar system. For example, an array of sensors on Mars or Europa will have to collect data under harsh environmental conditions, including extreme temperatures and exposure to high winds and radiation. To optimize system redundancy and data return these sensor will intercommunicate, will process and store data, and will autonomously telemeter that data to earth via relay satellite. This scenario precisely mirrors our proposed intelligent regional sensor network in Antarctica. The knowledge and experience gained in designing and operating the Antarctic instrument network will hence become an invaluable part of the preparation for such future planetary missions.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Powdermet, Inc.	NAME:	Northwestern University
ADDRESS:	9960 Glenoaks Blvd., Unit A	ADDRESS:	Sponsored Programs
CITY:	Dean Baker	CITY:	Evanston
STATE/ZIP:	CA   91352 - 1064	STATE/ZIP:	IL   60208 - 3108
PHONE:	( 818 ) 768 - 6420	PHONE:	( 847 ) 491 - 5436

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dean Baker , powdermet@earthlink.ney

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
This phase I proposal with Powdermet and Northwestern University is combining two technologies to provide a new light weight mirror concept.
The combinatiom of the 2 technologies should provide for improved performance and lighter weight strucutre for space applications.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Light weight structure- engine, airframe, floats, Thermal Barrier applications

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
Space Mirror application, tehrmal barrier, cryo tank applications
Con-X and other NASA X-ray missions

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Boston Applied Technologies, Inc.	NAME:	University of Minnesota
ADDRESS:	62 Kerry Dr.	ADDRESS:	200 Oak Street S.E.
CITY:	Dr. Hua Jiang	CITY:	Minneapolis
STATE/ZIP:	MA   02048 - 3433	STATE/ZIP:	MN   55455 - 2070
PHONE:	( 508 ) 339 - 9247	PHONE:	( 612 ) 626 - 7718

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Hua Jiang , hjiang@bostonati.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
This proposal will enable the most efficient integration of NASA?s semiconductor lasers into strategic optical systems. To protect laser lifetimes and increase performance, these lasers will require isolators to protect them from back-reflections, similar to the isolators in all fiber-optic networks. This work proposes to monolithically integrate magneto-optical isolators with semiconductor platforms in order to reduce the size and weight, as well as increase the performance, of NASA?s semiconductor laser systems. The important elements in an integrated isolator are 1) magneto-optical waveguides and 2) permanent magnet biasing films. Yttrium iron garnet (YIG), the strongest magneto-optical material, is very difficult to grow onto semiconductor platforms. This work will use a novel technique, metallorganic chemical liquid deposition (MOCLD) to achieve this feat. Preliminary results have demonstrated the feasibility, but not the optimization, of this technique. Permanent magnet films of SmCo have also demonstrated promise as biasing magnets in waveguide isolators. Here, SmCo films will be made using a novel in-situ nitriding technique during Sm and Co codeposition. Also proposed is the optimization of buffer layers, which buffer substrates during growth and act as optical claddings. Ridge and interferometer components will be modeled using the beam propagation method before prototype isolators are fabricated.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Optical communications, optical signal processing, and optical data storage systems are all areas that will benefit from the realization of feasible Photonic Integrated Circuits (PICs). The proposed magneto-optical components, namely isolators, will allow this realization as they extend laser lifetimes and, in dramatic cases, prevent loss of mode lock. This work will also lead to advances in magneto-optical spatial light modulators (MO-SLMs), which when fabricated by standard photolithography have potential for ultrahigh resolution screens. Besides decreasing the size, weight and cost, monolithic integration of electronics with magneto-optical components will also increase the speed and reliability of MO-SLMs.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
At the heart of most NASA missions is the need for high performance devices with low power and small dimension requirements. The results of this proposal will lead to excellent photonics integrated circuits (PICs) that meet these rigorous NASA standards. Therefore, the results will most directly apply to ?Active Optical Systems and Technology? branch of Research Topic 3: Earth Science and Physics and Astronomy. Specifically, the photonic isolating components that emerge from this work will enable the most efficient integration of compact semiconductor lasers into Passive Remote Sensing Detector Systems.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	ADVR Inc	NAME:	Montana State University
ADDRESS:	910 Technology Blvd Suite K	ADDRESS:	Physics Dept. EPS 264
CITY:	Dr. Kevin Repasky	CITY:	Bozeman
STATE/ZIP:	MT   59718 - 4012	STATE/ZIP:	MT   59717 - 3840
PHONE:	( 406 ) 522 - 0388	PHONE:	( 406 ) 994 - 6082

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Kevin Repasky , repasky@physics.montana.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
A lidar laser transmitter useful for profiling of clouds, aerosols, and differential absorption measurements of atmospheric trace constituents such as carbon dioxide, water vapor, and ozone is proposed. The proposed laser transmitter is based on a master tunable external cavity diode laser (ECDL) used to injection lock a series of free running laser diodes (FRLD's). The FRDL's amplify the injected optical signal from the master ECDL so that the output of the laser transmitter maintains the tunability and narrow linewidth of the master ECDL. The amplified output signal of the laser transmitter is easily pulsed by modulating the drive current to the FRDL's. The innovative laser transmitter maintains the tunability and narrow linewidth of the master ECDL important for differential absorption lidar (DIAL) measurements while providing a pulsed amplified output. Cascading four injection locked FRDL's to a master ECDL can produce a peak power of 1W. An order of magnitude improvement in the signal to noise performance of a lidar system can be obtained using the cascaded injection locked laser transmitter compared to the state of the art pulsed flared amplifiers.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The successful completion of the Phase I and Phase II STTR work will benefit NASA by improving the performance and lowering the cost of diode based lidar systems. Lidar systems based on the cascaded injection locked laser transmitters have an order of magnitude improvement in the SNR when compared to the pulsed flared amplifier system. Laser diodes needed for the injection locked laser transmitter cost about $750 per laser while pulsed amplifiers run anywhere from $20,000 to $50,000. The savings in cost for the cascaded injection locked system (4 diodes needed) is over an order of magnitude.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The development of the cascaded injection locked laser transmitter involves the development of a tunable ECDL, an amplified cw or pulsed tunable laser system, and a diode based laser transmitter for lidar systems. Chemical sensing is an emerging market able to utilize the tunable ECDL. This work is of interest to both AdvR and Montana State University. The high power pulse injection locked ECDL and the cascaded injection locked ECDL have a potential market for pollution monitoring devices and line of sight chemical absorption measurements for process monitoring and control.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	MEMX, Inc.	NAME:	Johns Hopkins University
ADDRESS:	1368 Bordeaux Dr.	ADDRESS:	11100 Johns Hopkins Road
CITY:	Jeffry J. Sniegowski	CITY:	Laurel
STATE/ZIP:	CA   94089 - 1005	STATE/ZIP:	MD   20723 - 6099
PHONE:	( 408 ) 543 - 1717	PHONE:	( 240 ) 228 - 5000

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Jeffry J. Sniegowski , jeff.sniegowski@memx.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
A collaborative effort between MEMX and Johns Hopkins University Applied Physics Laboratory (JHU/APL) is proposed to develop an innovative approach to enhancing LIDAR and optical communication transmitter systems and components with Micro ElectroMechanical Systems (MEMS) beam steering components. The MEMS Optical Beam Steerers (MOBSTERs) will demonstrate a capability that is scalable to space or can be mounted on a relevant platform (UAV, long duration balloon, or aircraft) for calibration/validation of a spaceborne system. These Optical Beam Steerers are highly miniaturized with an emphasis on low weight, small volume and low power. The prototype system to be studied would consist of components that can be easily migrated to a space qualified design. To date, MEMS technology has not been used in these applications, and will allow by virtue of their size and mechanical integration significant miniaturization and weight reduction, as well as the potential for multiplicity and redundancy.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The evolving need for increases in satellite communication bandwidths is pushing the state-of-the-art beyond microwaves to optical frequencies. JHU/APL is moving forward on addressing this need by developing a multi-channel video communications paradigm that employs laser terminals in space using an open architecture and scanned optical beams, (which can be developed by MEMX) connecting both fixed and mobile users. Millimeter-wave backup will also be provided for severe weather conditions. Initial projected optical link capabilities at tera-bits per user channel are feasible, however, and they offer orders-of-magnitude improvement over existing RF systems in the near-term.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
A new multi-functional 3-D LIDAR system concept has been developed by JHU/APL that incorporates multi-channel micro-mirror arrays, which can be fabricated by MEMX. This technology can be combined with multi-wavelength fiber lasers and high-speed optical modulator arrays to support a wide variety of measurements from a single platform. This system can adapt in real-time to measure land surface profiles, map aerosols and clouds, measure atmospheric temperature, humidity, and wind speeds, and land surface vibrations. Agile laser tuning, pseudo-random coding, and continuous-wave modulation are additional features that can be used for atmospheric spectroscopy, profiling, and Doppler or laser vibrometry, respectively.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Larson Davis, Inc.	NAME:	Brigham Young University
ADDRESS:	1681 W. 820 N.	ADDRESS:	Physics Department
CITY:	Scott Sommerfeldt	CITY:	Provo
STATE/ZIP:	UT   84601 - 1341	STATE/ZIP:	UT   84602 - 4201
PHONE:	( 801 ) 375 - 0177	PHONE:	( 801 ) 422 - 2205

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Scott Sommerfeldt , scott_sommerfeldt@byu.edu

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
This research will make significant progress in developing energy-based acoustic sensors and measurement techniques which will provide new insights into acoustic fields. In Phase I, a robust, three-dimensional, energy-based sensor will be developed and commercialized. It will be implemented on an efficient digital platform for acquiring and transmitting data. Energy-based measurement techniques and related software will be developed to determine radiated sound power from sources, enabling efficient in-situ measurements. Energy-based sensor array techniques will be developed to extend characterization of complex acoustic sources by extracting radiation information from sound fields not available from conventional sound pressure measurements.

In Phase II, high temperature/pressure capabilities for close proximity rocket plume measurements will be implemented to the energy-based sensor. A more complete understanding of spatial radiation characteristics and energy propagation, both from the source to the sensors and to remote structures, will be determined from energy-based measurements. Energy-based active control techniques will be developed as useful diagnostic tools to acoustically probe rocket sources and increase understanding of radiation characteristics. Energy-based measurements will be used to update and validate CFD models, and relationships between the acoustic and flow fields will be developed such that flow-field predictions can be made from the energy-based measurements.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Industry will be given powerful new methods and high quality instrumentation to further characterize sound fields through acoustic energy quantities. These tools will allow users to improve their understanding of sound fields, to surmise global sound field conditions, and to conduct more efficient sound power measurements. They will facilitate in-situ measurements of sound power and radiation from noise sources in industrial settings and improve efficiency of these measurements in laboratory settings. They will enable practical but comprehensive sound field assessments for environmental monitoring, noise control, and active sound field control in aerospace, transportation, audio, manufacturing, construction, and many other industries.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The technological developments of this work will apply directly to the measurement and analysis of sound produced in rocket plume environments. They will provide new energy-based methods of sound field and source characterization to enhance both the understanding and prediction of acoustic near fields and far fields. Energy-based active control techniques will be developed as useful diagnostic tools to further probe rocket plume source characteristics. Results will be used to update and validate CFD models and to better understand the relationships between the acoustic and flow fields. The developments will also be useful for many other NASA applications, whenever comprehensive sound field analysis and characterization are required.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	SIERRA ENGINEERING INC.	NAME:	Cal Poly State University Foundation
ADDRESS:	603 E. Robinson Suite 7	ADDRESS:	1 Grand Avenue
CITY:	Dr. Jeffrey Muss	CITY:	San Luis Obispo
STATE/ZIP:	NV   89701 - 4046	STATE/ZIP:	CA   93407 - 0001
PHONE:	( 775 ) 885 - 8483	PHONE:	( 805 ) 756 - 1123

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Jeffrey Muss , jmuss@sierraengineering.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Spatial uniformity within combustion devices, especially circumferential, is extremely important to the reliability and durability of a liquid rocket engine. Conventional combustion diagnostics, e.g. pressure and thrust, characterize global engine behavior, but provide no direct information about thermal and species distributions across the engine. Sierra Engineering has shown that exhaust plume measurements can provide many of these details with sensitivity much greater than conventional diagnostics. We have developed a turn-key infrared emission-absorption spectroscopy system capable of planar measurements across a rocket exhaust plume. Data reduction from this single spectrometer system requires that the flow field be assumed axisymmetric. However, simultaneous measurements from three spectrometers allow complete resolution of non-axisymmetric flow fields. The necessary tomographic data reconstruction techniques are commonly employed in the medical field for CAT-scan analyses. The subject proposal adapts the current Sierra emission-absorption plume diagnostic to a compact fiber-optic system suitable for deployment under realistic rocket test situations. The fiber-optic system enables the integration of three sensor systems into a single test setup, thereby permitting accurate characterization of non-axisymmetric flow fields.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The data generated with the instrument is important to rocket engine and gas turbine manufacturers across a range of applications. The DoD plume phenomenology community is intensely interested in both exit plane measurements and their relationship to engine characteristics. The instrument can also be directly applied to gain detailed insight into any combustion phenomena, including industrial boilers to open pool fires.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The resultant instrument determines the cross-sectional species and temperature distributions at the engine exit, which is closely related to the distributions at both the throat and within the nozzle converging section. It is equally applicable to uni element research-scale and large scale prototype engines. These data are essential to NASA and their engine contractors if Gen2 and Gen3 life and reliability goals are to be achieved. The instrument is also applicable for exhaust flow field characterization of gas turbine engines and solid and hybrid motors. Data collected is essential to validate and improve analysis tools, especially computational fluids dynamics (CFD) models.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Omni Technologies, Inc.	NAME:	Louisiana State University
ADDRESS:	7412 Lakeshore Drive	ADDRESS:	2513E CEBA Bldg
CITY:	Sean Griffin	CITY:	Baton Rouge
STATE/ZIP:	LA   70124 - 2435	STATE/ZIP:	LA   70803 - 0001
PHONE:	( 504 ) 288 - 8211	PHONE:	( 225 ) 578 - 5891

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Sean Griffin , sgriffin@otiengineering.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Omni Technologies, Inc. (OTI) is proposing a unique acoustic method for measuring flow rate of liquid cryogens. Over the last 30 years, acoustic flowmeters have been demonstrated that non-intrusively measure flow rates in fluid filled pipes. The majority of these use pulsed time of flight techniques but none have used continuous wave (CW) techniques as is being proposed. The advantages of the proposed technique are simplicity of electronics, better signal detection capability, and continuous verses periodic measurements. This translates to a cheaper, smaller, more capable and highly accurate sensor suite. The risk of the proposed technique is reduced since proven pulsed time of flight systems use nearly identical sensor configurations and are based on the same physics. Measurement of fluid flow of liquid cryogens adds significant complexity to the sensor design due to material thermal effects but literature suggests that acoustic flowmeters are applicable for flow measurement of liquid cryogens. Upon completion of Phase I, OTI expects to have demonstrated the validity of the proposed method and have a working commercially viable flowmeter design by the end of Phase II. OTI expects the new flowmeter will provide NASA with a means to more accurately and more reliably measure cryogenic flow.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
Acoustic flowmeters are applied in many industrial process control applications from the oilfield, to nuclear power plants, to waste water treatment, to manufacturing facilities. Any plant where flow measurements are required is a potential application. The proposed flowmeter likewise has similar application but will be faster and less costly. The proposed flowmeter will be cost competitive with traditional flowmeters but provide better accuracy. Current acoustic flowmeters are costly and generally used only where wetted sensors are not feasible and the cost is not the driving factor.

Researchers have also demonstrated acoustic flowmeters that provide density estimates allowing a single sensor to provide mass flow. This is of particular interest in industries such as the paper industry where process control requires mass flow. OTI believes the proposed flowmeter capabilities can be extend in the future to include density calculations thus increasing market opportunities.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The primary NASA application is that stated in the request for proposal. NASA requires cryogenic flow measurements during fuel loading (liquid hydrogen and liquid oxygen) operations. Accurate flow measurements are required to insure that correct amounts of fuel and oxidizer are loaded for test operations as well as Shuttle missions. Accurate flow measurements are also required during test firings for plant control and monitoring. Due to the high pressures involved, wetted flow sensors are less desirable because of the increased risk of leaks. Higher maintenance is also an issue with wetted transducers. Acoustic flow sensors are more accurate and can be operated non-intrusively offering significant advantages. The proposed CW acoustic flowmeter offers inherent advantages. Sample rate is higher and cost is lower than acoustic flowmeters based on different methods.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Orbital Technologies Corp	NAME:	University of Wisconsin - Madison
ADDRESS:	Space Center, 1212 Fourier Drive	ADDRESS:	1415 Engineering Drive
CITY:	Dr. Martin J. Chiaverini	CITY:	Madison
STATE/ZIP:	WI   53717 - 1961	STATE/ZIP:	WI   53706 - 0000
PHONE:	( 608 ) 827 - 5000	PHONE:	( 608 ) 263 - 4980

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Martin J. Chiaverini , chiaverinim@orbitec.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
ORBITEC and the University of Wisconsin-Madison propose to develop a low-cost, non-intrusive, wavelength-agile optical rocket propulsion sensor (WORPS) to interrogate rocket exhaust plumes and cryogenic fluid properties. The innovative sensor system is based on a Chirped White Pulse Emitter (CWPE). By rapidly monitoring (1 ?Ys response time) broad absorption spectra, the CWPE can interrogate temperature, pressure, and multiple species concentrations in gases at arbitrary conditions and can simultaneously monitor cryogenic liquid properties, all with a simple design. Along a line-of-sight with non-uniform properties, the CWPE can also record gas temperature distributions rather than just the path-averaged temperature. These capabilities represent a dramatic enhancement of the best diode-laser sensors available just two years ago, which were not wavelength-agile. In Phase I, a prototype WORPS system will be designed and fabricated. The unit will be initially demonstrated by interrogating static gas cells at various mixtures and pressures, flat-flame burners, and dewars of LOX containing known amounts of trace constituents (such and N2). Additional demonstrations will be performed by measuring species concentrations and temperature in exhaust plumes from the combustion of GOX/GH2, GOX/RP-1, and GOX/HTPB in lab-scale thrust chambers operating over a range of pressures and nozzle area ratios.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
All industries requiring non-invasive sensing of gas or liquid properties with fast-time response will benefit from the technology. These include virtually all types of engines (rocket, gas turbine, piston, etc.) and associated systems as well as many industrial process monitoring applications (e.g., semiconductor processing). In addition, wavelength-agile light can be used to monitor solid properties, either directly or by embedding fiber-optic sensors. Large industries that may find the technology attractive include the automotive industry for internal combustion engine monitoring and emissions control, the commercial aircraft industry for jet engines and gas turbines, and the power production industry for coal, oil, and natural gas burners.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The goal of this work is to produce multi-purpose, rugged optical sensors from inexpensive components. By the conclusion of Phase II, a single WORPS system is expected to cost less than $5000 and have the capability to monitor multiple gas or liquid properties with time response of 1 ?Ys. Such devices are invaluable to propulsion system developers. Because the WORPS technology can be applied to both combustion and cryogenic systems, the NASA market is large. Potential NASA applications include use for propulsion system monitoring in testing facilities at NASA/SSC, NASA/MSFC, NASA/GRC, NASA/ARC, and NASA/KSC. Because the proposed WORPS system technology is lightweight and has only a few key components, it could potentially find use as a diagnostic tool for on-orbit microgravity combustion, gas, and fluid experiments aboard the Shuttle and ISS. Real-time, in-flight monitoring of the SSME for propulsion system health represents another applications for the mature WORPS system.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Tethers Unlimited	NAME:	Stanford University SSDL
ADDRESS:	19011 36th Ave W, Suite F	ADDRESS:	469 Lomita Mall, Stanford University
CITY:	Robert Hoyt	CITY:	Stanford
STATE/ZIP:	WA   98036 - 5752	STATE/ZIP:	CA   94305 - 4035
PHONE:	( 425 ) 744 - 0400	PHONE:	( 650 ) 723 - 8651

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Robert Hoyt , hoyt@tethers.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Space tether technology can provide propellantless propulsion for orbital maneuvering, orbital transfer, and spacecraft formation flying. The MAST (Multi- Application Survivable Tether) experiment team, consisting of Tethers Unlimited, Inc. (TUI) and the Stanford University Space Systems Development Laboratory (SSDL), propose to develop and test space-survivable tether technologies relevant to momentum-exchange tethers, electrodynamic propulsion tether systems, formation flying, and space elevator technologies. Specifically, the MAST team will develop both a very small tether deployer suitable for use on picosatellite experiments and a simple tether crawler/inspector, and use these in a very low-cost CubeSat flight experiment to obtain critical data on the survivability of tethers and other gossamer space technologies in the M/OD environment. In the Phase I effort, we will design and build breadboard prototypes of these picosatellite tether systems. In the Phase II effort, we will conduct a flight experiment on the CubeSat platform, obtaining critical data on space tether survivability and the dynamics of tethered spacecraft formations.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The technologies developed as part of the MAST STTR effort will find potential applications on every small satellite launched into LEO. The primary advantage of tether propulsion relative to other technologies is that they can provide microsatellites with propulsion for orbit raising, station-keeping, and inclination changes with zero propellant expenditure, and will thus be most competitive for missions requiring large total delta-V. They will permit commercial imagery satellites to station-keep indefinitely at much lower altitudes than currently possible, thus enabling small, inexpensive observation microsatellites to achieve resolutions currently available only with large, complex spacecraft. Although tether propulsion technologies will be developed specifically for the growing microsatellite market as part of this experiment, the technologies are easily scalable to application on larger spacecraft such as the next generation of telecommunications satellite constellations.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
The propellantless nature of tether propulsion will result in highly capable small spacecraft for future Earth science missions that can perform many more orbital maneuvers during their lifetimes than could be achieved with a propellant-limited propulsion. This will enable microsatellites deployed from the Shuttle SHELS payload adapter to raise their orbits up to 2,000 km, allowing longer-duration missions, while maintaining high payload fractions. Tethers will also make feasible formation flying missions, such for SAR and long-baseline interferometry studies, which require large total delta-Vs that are not feasible with propulsion systems that require propellant. Additionally, the technologies developed and demonstrated in the proposed STTR will be scalable to much larger applications, such as orbital maintenance of the International Space Station or a momentum exchange tether facility.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Ultramet	NAME:	Sandia National Laboratories
ADDRESS:	12173 Montague St	ADDRESS:	P.O. Box 5800
CITY:	Brian E. Williams	CITY:	Albuquerque
STATE/ZIP:	CA   91331 - 2210	STATE/ZIP:	NM   87185 - 1129
PHONE:	( 818 ) 899 - 0236	PHONE:	( 505 ) 845 - 3138

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Brian E. Williams , brian.williams@ultramet.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
Low-density, high specific stiffness ceramic and metal open-cell foam materials may be utilized for creation of an innovative fuel matrix for use in space nuclear reactors. Highly porous structural foam may be developed for high thermal efficiency, high temperature fuel elements for both propulsion and gas-cooled power reactors. Current designs, such as annular rods or pebble beds, cannot operate at extremely high temperatures and thus limit efficiency. In this project, the foam fuel material will ultimately consist of a tricarbide, UZrNbC, composed of enriched uranium that is vapor infiltrated into a foam matrix of niobium carbide (NbC) and zirconium carbide (ZrC), although tantalum carbide (TaC) will be substituted for uranium carbide (UC) during initial development. The porous structure provides an extended surface area for highly efficient heat transfer and reduces density, reducing hydrogen turbopump power demands and increasing thrust-to-weight ratio. The foam matrix can have 80-90% open porosity for maximum convection, and the ligament dimensions can be tailored to provide either good or poor thermal conduction as needed. Recent work on porous materials has demonstrated effective heat transfer coefficients with helium near 26,000 W/m2?K. NbC and ZrC foams have several important advantages over other high temperature materials, including low density, lack of degradation in hydrogen at 3000 K (where they also retain structural integrity), and minimal neutron cross-section. The dispersed fissile material is an integral part of a high-conductivity matrix. Thus, a much lower temperature difference can exist between the fuel and the propellant. Extremely high outlet temperatures can be achieved, yielding the high specific impulse required for interplanetary exploration. Ultramet will team with Sandia National Laboratories to demonstrate the feasibility of integrating porous foam fuel elements into a new reactor concept for compact, high-performance space reactors.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
In addition to compact, high-performance space reactors, the proposed technology will assist development of ion drive, plasma thrusters, and fusion propulsion. The foam fuel matrix could also contribute to a new DOE Generation IV power system that significantly lowers cost, improves passive safety, has no carbon dioxide emissions, uses an advanced, proliferation-resistant fuel cycle, and reduces nuclear waste. The foam fuel could also be used in ground-based power or in portable power systems for military or surveillance applications and remote deployment, as well as impact other applications in electronics, aerospace, and catalysis.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
Propulsion technologies are sought that will enable dramatic improvements in space transportation safety, reliability, and cost. Key to this goal is the application of innovative, non-traditional propulsion technologies, devices, and systems that could significantly increase the structural margins of future launch systems and substantially reduce the mission times for interplanetary and deep space spacecraft. Development of such technologies is sought to enable ambitious commercial, robotic, and human exploration missions in the future. Technology innovations are sought that would provide significant advancements in space transportation capability and lead to the development of safe, affordable, high-performance propulsion technologies, specifically including high-efficiency nuclear-electric propulsion systems.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	CU Aerospace LLC	NAME:	University of Illinois, U-C
ADDRESS:	2004 S. Wright St. Extended	ADDRESS:	306 Talbot Lab/104 S. Wright St.
CITY:	Victoria Coverstone / David Carroll	CITY:	Urbana
STATE/ZIP:	IL   61802 - 1000	STATE/ZIP:	IL   61801 - 2935
PHONE:	( 217 ) 333 - 8274	PHONE:	( 217 ) 333 - 0678

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Victoria Coverstone / David Carroll , vcc@uiuc.edu / carroll@cuaerospace.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
UltraSail is a complete sail system for the launch, deployment, stabilization and control of very large (km^2 size) solar sails enabling reduced mission times for interplanetary and deep space spacecraft. UltraSail is an innovative, non-traditional approach to propulsion technology achieved by combining propulsion and control systems developed for formation-flying microsatellites with an innovative solar sail architecture to achieve controllable sail areas approaching 1 km^2, sail subsystem area densities of 1 gm/m^2, and thrust levels 20 times those of ion thrusters used for comparable deep space missions. UltraSail can conceivably even achieve outer planetary rendezvous, a deep space capability now reserved for high-mass nuclear and chemical systems. The primary innovation is the near-elimination of sail supporting structures by attaching the sail tip to a number of formation-flying microsatellites which deploy the sail, and then articulate the sail to provide attitude control, including spin stabilization and precession of the spin axis. These tip microsatellites are controlled by a laser metrology system and maneuvered by a 3-axis microthruster system using solar-power to maintain low, constant velocity and proper sail film tension during deployment with negligible propellant mass.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
UltraSail is potentially useful for a range of robotic missions ranging from Mars to the Kuiper Belt. Although inner planet transfers are achievable, UltraSail?s greatest advantages are in outer-planet/solar system exploration. While the obvious first application for outer planet missions would be flyby missions including aerocapture, the large sail area and low density may make planetary rendezvous missions feasible. Phase I should provide initial answers as to the rendezvous question.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
UltraSail may have limited military applications for earth-observing missions at high orbit where stationary observing is useful ? e.g. pole-sitting missions. Also, NOAA and NSF have strong interests in the science that can be returned using sails in non-Keplerian orbits.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	New Era Technology	NAME:	Pennsylvania State University
ADDRESS:	3720 NW 43RD ST STE 105	ADDRESS:	PO Box 30
CITY:	Travis Knight	CITY:	State College
STATE/ZIP:	FL   32606 - 6190	STATE/ZIP:	PA   16804 - 0030
PHONE:	( 352 ) 380 - 9880	PHONE:	( 814 ) 863 - 3991

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Travis Knight , travis@confman.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
A new modular solar powered rocket engine is proposed to provide a few milligrams to a few kilograms of thrust at 900-1000 seconds of specific impulse by heating hydrogen propellant to average temperatures ranging from 2750 to 3250K. The proposed design utilizes one or several sunflower-like clusters of nonimaging concentrators coupled to optical fiber bundles that guide the solar energy with a throughput of greater than 80% into a Plank cavity/thrust chamber. The Plank cavity receives and entraps solar energy for direct heating of hydrogen and/or storage in a composite thermal storage unit. A nested flow path is designed to force hydrogen flow along the thermal storage/cavity temperature gradient, thereby, producing variable levels of thrust at relatively constant specific impulse of 900 to 1000 seconds. The innovative use of the sun tracking concentrators coupled to optical fibers, combined with the composite thermal storage unit/Plank cavity will allow for receiving and utilization of more than 80% of solar energy for producing thrust. This is a revolutionary improvement over existing solar-electric powered space propulsion systems and could lead to the development of an ultralight, compact, and an order of magnitude lower cost propulsion system for space transportation and solar system exploration.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
NeTech is planning to develop the following technologies that are expected to be of a wide range of applications to space power and propulsion industry: 1) The most significant application of the proposed work is the development of a low cost, ultra-compact, and lightweight solar thermal propulsion system for a wide range of space transportation applications. 2) Development and marketing of glassy carbon container for containment of high temperature corrosive materials. 3) Fabrication technology for low porosity forms of carbon. 4) Refractory carbide coating techniques for graphite and other forms of carbon. The EB-PVD and PVD-thermocarburizing techniques provide for gradient coating of graphite with stoichiometric and non-stoichiometric carbides. NeTech will pursue commercial applications of the modular solar thermal propulsion system as well as the glassy carbon and refractory carbide coating technology both as industrial products and also as service to the industry. NeTech will also pursue the marketing of its computational fluid dynamic and heat transfer capabilities to the aerospace power and propulsion industry.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
Dramatic improvement in utilization of solar energy and high temperature storage/processing of the solar thermal power result in development of very low cost space transportation system for a wide range of applications. Other potential NASA applications include: development of glassy carbon technology, development of refractory carbide coating technology for different forms of graphite, development of a CFD model for analysis of advanced space propulsion systems, and development of ultrahigh temperature furnaces for processing and testing of materials.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Orbital Technologies Corp	NAME:	University of Texas at Dallas
ADDRESS:	Space Center, 1212 Fourier Drive	ADDRESS:	Physics Department
CITY:	Dr. Eric E. Rice	CITY:	Richardson
STATE/ZIP:	WI   53717 - 1961	STATE/ZIP:	TX   75083 - 0000
PHONE:	( 608 ) 827 - 5000	PHONE:	( 972 ) 883 - 2846

PRINCIPAL INVESTIGATOR/PROJECT MANAGER(Name,Email):	Dr. Eric E. Rice , ricee@orbitec.com

TECHNICAL ABSTRACT (LIMIT 200 WORDS):
ORBITEC, working in cooperation with The University of Texas at Dallas (UTD), and others, proposes to develop a low-cost, tethered artificial gravity spacecraft system that can be launched from the STS in a hitchhiker GAS Can or expendible launch vehicle. This variable-gravity platform would be used by scientific researchers of the Texas and Wisconsin Space Grant Consortia as well as college students of Space Grant consortia. This program would allow specific scientific experiments to be flown as part of scientific research and outreach to the public. The Phase I effort involves: Defining the TAG Spacecraft System Requirements and capabilities; conducting deployment/recovery dynamics analysis; evaluation of the launch and operating loads; performing preliminary spacecraft system design specification/definition and analysis required to meet the system requirements; conducting testing of critical subsystem components, a cost analysis, defining the Phase III preliminary design; and establishing a plan for user/outreach program for experiments/payloads. Phase II of this STTR program will culminate in a flight of a model spacecraft in a non-ejected Get-Away-Special (GAS) Canister on the Space Shuttle. It will be operated under the aegis of the Texas Space Grant Consortium (TSGC). TSGC has such a GAS-CAN that it has agreed to make available to the program. Phase III will involve building and flying the TAGS.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS):
The tethered artificial gravity spacecraft system that can be launched from the STS in a hitchhiker GAS Can or an expendable launch vehicle is a low-cost variable gravity platform that could be used by scientific researchers for experiments that require various g force levels. Variable g levels up to several g?s can be produced by spinning the two end-masses about their common center of mass. This program would allow specific scientific experiments to be flown as part of scientific research and outreach to the public. The platform would also be available for many commercial applications.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS):
It is well-known that prolonged exposure in humans to a microgravity environment leads to significant loss of bone and muscle mass; this presents a formidable obstacle to human exploration of space, particularly for missions requiring travel times of several months or more, such as a trip to Mars. Artificial gravity may be produced by spinning a spacecraft about its center of mass, but unless the distance from the center of rotation is several kilometers, the rotation rate required to generate one ?g? would induce vertigo in the astronauts. By tethering the crew capsule to an object of nearly equal mass (such as the spent final rocket stage) at a distance of a km, the rotation rate would be reduced sufficiently to not cause discomfort for the astronauts. To develop this concept, the dynamics and stability of tethered systems with similar-sized end-masses must be modeled and then tested in space. This is the goal of this STTR proposal. There are many gravity-based research applications to the biological and physical scientific community, once TAGS is fully developed and operational. TAGS can be flown off ELVs, STS, and the ISS.

NASA 2002 STTR Phase 2 Solicitation

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Ibex Healthdata Systems	NAME:	Johns Hopkins University
ADDRESS:	5600 North River Road Suite 150	ADDRESS:	720 Rutland Avenue
CITY:	Rosemont	CITY:	Baltimore
STATE/ZIP:	IL   60618 -5102	STATE/ZIP:	MD   21205 -2109
PHONE:	(847 ) 993 -2200	PHONE:	(410 ) 614 -3637

PRINCIPAL INVESTIGATOR/ PROJECT MANAGER:	John Epler  Ibex Healthdata Systems
U.S. Citizen or Permanent Resident:	Y

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The purpose of this project is to develop a portable, hands free device for emergency medical decision support to be used in remote or confined settings by non-physician providers. Phase I of the project will entail the development of a voice-activated device that will utilize an intelligent algorithm to provide guidance in establishing an airway in an emergency situation. The interactive, hands free software will process requests for assistance based on verbal prompts and algorithmic decision-making. The device will allow the CMO to attend to the patient while receiving verbal instruction. The software will also feature graphic representations where it is felt helpful in aiding in procedures. We will also develop a training program to orient users to the algorithmic approach, the use of the hardware and specific procedural considerations. We will validate the efficacy of this mode of technology application by testing in the Johns Hopkins Department of Emergency Medicine. Phase I of the project will focus on the validation of the proposed algorithm, testing and validation of the decision making tool and modifications of medical equipment. In Phase II, we will produce the first generation software for hands-free, interactive medical decision making for use in acute care environments.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The medical decision software, the algorithmic approach and the hands free technology will be combined to provide a product that can have wide applicability to the emergency care community. Once the technology and software have been developed and tested in the clinical setting, and training programs designed for orientation, it should be an easily marketable technology to almost any medical/para-medical organization. Any algorithm based approach could be adapted to this technology, including Advanced Cardiac Life Support, pre-hospital/paramedic protocols and decision making support for remote or mobile care climates. While it will be useful in the hospital environment, its greatest impact might be on the military and other similar organizations whose infrastructure ?in the field? is not as developed as that of the civilian world. Any isolated population, ie, ship, base, etc. could easily benefit from intelligent, hands free decision-making technology and employ it with very minimal training. This will allow for emergency services to be accessed/provided with more speed, accuracy and reproducibility.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS)
Hands free medical decision support in the international space station. Potentially, medical decision support in all of NASA's ground and space facilities.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Tethers Unlimited	NAME:	Stanford University SSDL
ADDRESS:	19011 36th Ave W. Suite F	ADDRESS:	469 Lomita Mall, Stanford University
CITY:	Lynnwood	CITY:	Stanford
STATE/ZIP:	WA   98036 -5752	STATE/ZIP:	CA   94305 -4035
PHONE:	(425 ) 744 -0400	PHONE:	(650 ) 723 -8651

PRINCIPAL INVESTIGATOR/ PROJECT MANAGER:	Robert Hoyt  Tethers Unlimited
U.S. Citizen or Permanent Resident:	Y

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The MAST (Multi-Application Survivable Tether) team, consisting of Tethers Unlimited, Inc. (TUI) and the Standford University Space Systems Development Laboratory (SSDL), propose to develop and fly a very low cost nanosatellite experiment that will demonstrate the deployment of a lightweight multiline tether on orbit and obtain data on its survivability in the micrometeoroid and orbital debris environment. In the Phase I effort, we designed an experiment in which three CubeSats will deploy a 1-kilometer long Hoytether in space, and the middle CubeSat will slowly crawl along the tether, inspecting it for damage. We successfully prototyped and tested key components for this experiment, including a separation/ejection mechanism and avionics for communications, command, and data handling. During the Phase I we also secured $89K in additional, non-SBIR funding that is supporting the development of the crawler and inspector subsystems. In the Phase II effort, we will build and fly the CubeSat-based MAST experiment. The mission will obtain data on tether survivability and tether dynamics that are crucial to the design of all future tether missions.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
The Phase II effort will demonstrate a space-survivable tether structure that will enable tethers to be used for a wide range of long-duration space missions. The primary advantage of space tethers relative to competing technologies is that they can provide microsatellites with propulsion for orbit raising, station-keeping, and inclination changes with zero propellant expenditure, and can thus provide large total delta-Vs with very low mass requirements. Other tether applications include formation flying and modification of the radiation belts. During the Phase I effort, we were awarded three non-SBIR/STTR contracts from DARPA and NASA worth over $1,115,000 to develop tether technologies and applications. Although tether propulsion technologies will be developed specifically for the growing microsatellite market as part of this experiment, the technologies are easily scalable to application on larger spacecraft such as the next generation of telecommunications satellite constellations.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS)
The propellantless nature of tether propulsion will result in highly capable small spacecraft for future Earth science missions that can perform many more orbital maneuvers during their lifetimes than could be achieved with a propellant-limited propulsion. This will enable microsatellites deployed from the Shuttle SHELS payload adapter to raise their orbits up to 2,000 km, allowing longer-duration missions, while maintaining high payload fractions. Tethers will also make feasible formation flying missions, such for SAR and long-baseline interferometry studies, which require large total delta-Vs that are not feasible with propulsion systems that require propellant. Additionally, the technologies developed and demonstrated in the proposed SBIR will be scalable to much larger applications, such as orbital maintenance of the International Space Station or a momentum exchange tether facility that can reduce the cost of lunar, Mars, and deep-space missions.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Ultramet	NAME:	Sandia National Laboratories
ADDRESS:	12173 Montague Street	ADDRESS:	P.O. Box 5800
CITY:	Pacoima	CITY:	Albuquerque
STATE/ZIP:	CA   91331 -2210	STATE/ZIP:	NM   87185 -1129
PHONE:	(818 ) 899 -0236	PHONE:	(505 ) 845 -3138

PRINCIPAL INVESTIGATOR/ PROJECT MANAGER:	Brian E. Williams
U.S. Citizen or Permanent Resident:	Y

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Low-density, high specific stiffness ceramic and metal open-cell foams may be utilized for creation of an innovative fuel element for use in space nuclear reactors. Highly porous structural foam may be developed for high thermal efficiency, high temperature fuel elements for both propulsion and gas-cooled power reactors. Current designs, such as annular rods or pebble beds, cannot operate at extremely high temperatures and thus limit efficiency. In the proposed Phase II project, the foam fuel element material will consist of a tricarbide, U(ZrNbC), composed of uranium carbide that is vapor infiltrated into a foam matrix of niobium carbide and zirconium carbide (in Phase I, tantalum carbide was substituted for uranium carbide). The porous foam structure provides an extended surface area for highly efficient heat transfer and reduces density, reducing hydrogen turbopump power demands and increasing thrust-to-weight ratio. In Phase I, Ultramet teamed with Sandia National Laboratories to demonstrate the feasibility of these highly innovative foam fuel elements. This work included chemical vapor infiltration of the carbides into an open-cell foam skeletal structure by Ultramet and fabrication of a matrix of foam densities for thermal/gas flow testing at Sandia. The results of flow testing, coupled with the results of thermomechanical modeling performed at Sandia, confirmed the high potential of this design following continued development. In Phase II, Ultramet and Sandia propose to develop and demonstrate fabrication of the actual (U-Zr-Nb)C foam fuel material. Ultramet will finalize process optimization using the (Ta-Zr-Nb)C material and provide the processing conditions to Sandia which, in conjunction with the University of Florida Institute of Space Power and Propulsion (INSPI) facility, will produce and test (U-Zr-Nb)C foam in a hot hydrogen environment. Sandia will also perform comprehensive thermomechanical modeling, expanding on the modeling performed in Phase I.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
In addition to compact, high-performance space reactors, the proposed technology will assist development of ion drive, plasma thrusters, and fusion propulsion. The foam fuel elements could also contribute to a new DOE Generation IV power system that significantly lowers cost, improves passive safety, has no carbon dioxide emissions, uses an advanced, proliferation-resistant fuel cycle, and reduces nuclear waste. The foam fuel could also be used in ground-based power or in portable power systems for military or surveillance applications and remote deployment, as well as impact other applications in electronics, aerospace, and catalysis.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS)
Propulsion technologies are sought that will enable dramatic improvements in space transportation safety, reliability, and cost. Key to this goal is the application of innovative, non-traditional propulsion technologies, devices, and systems that could significantly increase the structural margins of future launch systems and substantially reduce the mission times for interplanetary and deep space spacecraft. Development of such technologies is sought to enable ambitious commercial, robotic, and human exploration missions in the future. Technology innovations are sought that would provide significant advancements in space transportation capability and lead to the development of safe, affordable, high-performance propulsion technologies, specifically including high-efficiency nuclear-electric propulsion systems. Specific NASA applications include the Jupiter Icy Moons Mission (JIMO), which will be the first program to take advantage of spacecraft power system development being performed under Project Prometheus. JIMO will utilize a nuclear fission reactor for propulsion as well as production of the large amount of electrical energy required for scientific instruments (including deep penetrating radar), mission design options, and telecommunications. The proposed high-value project can have a timely and direct impact on Project Prometheus goals.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	CU Aerospace LLC	NAME:	University of Illinois, U-C
ADDRESS:	60 Hazelwood Dr.	ADDRESS:	306 Talbot Lab/104 S. Wright St.
CITY:	Champaign	CITY:	Urbana
STATE/ZIP:	IL   61820 -7460	STATE/ZIP:	IL   61801 -2935
PHONE:	(217 ) 333 -8274	PHONE:	(217 ) 333 -0678

PRINCIPAL INVESTIGATOR/ PROJECT MANAGER:	Victoria Coverstone / David Carroll
U.S. Citizen or Permanent Resident:	Y

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
UltraSail, proposed by a team of CU Aerospace, the University of Illinois at Urbana-Champaign, SRS Technologies, and VACCO Industries, is a next-generation high-risk, high-payoff sail system for the launch, deployment, stabilization and control of very large (km^2 class) solar sails enabling high payload mass fractions for interplanetary and deep space spacecraft. UltraSail is an innovative, non-traditional approach to propulsion technology achieved by combining propulsion and control systems developed for formation-flying microsatellites with an innovative solar sail architecture to achieve controllable sail areas approaching 1 km^2, sail subsystem area densities approaching 1 g/m^2, and thrust levels many times those of ion thrusters used for comparable deep space missions. UltraSail can achieve outer planetary rendezvous, a deep space capability now reserved for high-mass nuclear and chemical systems. The primary innovation presented in Phase I was the near-elimination of sail supporting structures by attaching each blade tip to a formation-flying microsatellite which deploys the sail, and then articulates the sail to provide attitude control, including spin stabilization and precession of the spin axis. These tip microsatellites are controlled by a 3-axis microthruster metrology system to control sail film deployment.

POTENTIAL COMMERCIAL APPLICATION(S) (LIMIT 150 WORDS)
UltraSail may have military applications for earth-observing missions at high orbit where stationary observing is useful ? e.g. pole-sitting missions. Also, NOAA and NSF have strong interests in the science that can be returned using sails in non-Keplerian orbits.

POTENTIAL NASA APPLICATION(S) (LIMIT 150 WORDS)
UltraSail is potentially useful for a range of robotic missions ranging from Sun-Earth Lagrange point L1 to Mars to the Kuiper Belt. An attractive application is an outer planet mission such as a Titan orbiter. Initial results indicate that high payload mass fractions are achievable.

SMALL BUSINESS CONCERN (SBC):		RESEARCH INSTITUTION (RI):
NAME:	Advanced Engineering Solutions	NAME:	Oklahoma State University
ADDRESS:	6730 Abbottswood Dr.	ADDRESS:	218 Engineering North
CITY:	Palos Verdes	CITY:	Stillwater
STATE/ZIP:	CA   90275 -3018	STATE/ZIP:	OK   74078 -0002
PHONE:	(310 ) 704 -7490	PHONE:	(405 ) 744 -5900

PRINCIPAL INVESTIGATOR/ PROJECT MANAGER:	Maj Dean Mirmirani  Advanced Engineering Solutions
U.S. Citizen or Permanent Resident:	Y

TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The ability to quickly estimate flight vehicle behavior in an operational environment is important since enginee