| PROPOSAL NUMBER: | 02- A1.01-8269 (For NASA Use Only - Chron: 023730 ) |
| SUBTOPIC TITLE: | Flight Deck Situation Awareness and Crew Systems Technologies |
| PROPOSAL TITLE: | Constraint-based Analysis of Aircraft Operations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Charles River Analytics Inc.
625 Mount Auburn Street
Cambridge , MA 02138 - 4555
(617 ) 491 - 3474
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Dan L. Grecu
dgrecu@cra.com
625 Mount Auburn Street
Cambridge , MA 02138 - 4555
(617 ) 491 - 3474
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced technologies for on-board data recording allow the collection of increasingly sophisticated information during aircraft operation, reflecting decisions and actions taken by the crew, external flight conditions, and the behavior of flight systems. Such data, when subjected to a systematic and focused methodology of analysis, offers a tremendous opportunity for analyzing overall crew behavior, action patterns, and responses. To do this, we propose a novel analysis framework centered on the use of constraint-based safety models. In contrast to data-driven analysis techniques, we propose an approach in which aviation safety experts would define constraint-based models of aircraft operational safety, and then apply these models against recorded data logs to detect and analyze exceedances. Data segments that reveal deviations from the model are then submitted to specialized analysis components that attempt to infer general behaviors across aircraft crews, or across individuals, to assess correlations with the detected deviations. The resulting recommendations can be incorporated in training sessions, simulated flight experiments, and actual test flights, to improve overall safety of maneuvers and performance of crew actions.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Potential commercial applications of the proposed effort include safety critical environments, where operational data is available for processing and analysis. Immediate application areas include railway safety, control rooms for nuclear plants, and for other complex high-value ecologically-sensitive industrial processes. The proposed approach also has immediate application for aircraft safety applications in the military domain.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The full-scope environment for Constraint-based Analysis of Aircraft Operations will have immediate benefit in supporting the Aviation Performance Measurement System (APMS). The proposed capability provides a mixed initiative approach to analyzing vast amounts of data collected during routine flights, by detecting and facilitating the analysis of behaviors that are transient, and may potentially remain undetected. The proposed effort has also integration potential with components of NASA?s Aviation Safety Program by capitalizing on the results of the Aviation System Monitoring and Modeling effort, and on the data sources it provides. The proposed approach can complement the Single Aircraft Prevention Program by integrating the results into a capability that can predict safety hazards due to technical problems, aircraft operation issues, and adverse conditions. Finally, the Constraint-based Analysis of Aircraft Operations can provide valuable input to the System-Wide Accident Prevention Program that looks into aviation safety issues associated with human error and non-procedural compliance.
| PROPOSAL NUMBER: | 02- A1.01-9623 (For NASA Use Only - Chron: 022376 ) |
| SUBTOPIC TITLE: | Flight Deck Situation Awareness and Crew Systems Technologies |
| PROPOSAL TITLE: | Cockpit System Situational Awarness Modeling Tool |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Micro Analysis & Design Inc
4949 Pearl East Circle, Suite 300
Boulder , CO 80301 - 2477
(303 ) 442 - 6947
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. John Keller
jkeller@maad.com
4949 Pearl East Circle, Suite 300
Boulder , CO 80301 - 2477
(303 ) 442 - 6947
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Cockpit System Situational Awareness Modeling Tool will use the principles of discrete event simulation to predict pilot situational awareness (SA). The human performance modeling environment of IMPRINT combined with the cognitive modeling tool ACT-R will provide a powerful tool for the designers of cockpit systems. IMPRINT can already be used to predict pilot workload and assess the effects of performance shaping factors on pilot tasks. The use of ACT-R to add the SA prediction capability will dramatically increase the usefulness of the tool. The capability of predicting pilot SA will allow design concepts to be assessed early in the design process and supplement data collected through comparatively more expensive pilot in-the-loop experiments. NASA is continuing to play an important role in the development of new operational concepts for the National Airspace System (NAS) as they explore the feasibility of transferring separation responsibility from the ground-based air traffic control system to the flight deck. The impact on the pilot?s SA of new tools designed to support these efforts must be understood to ensure that safety and efficiency of the NAS is maintained. Likewise any commercial developer of cockpit systems will benefit from the use of this tool.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Cockpit System Situational Awareness Modeling Tool could assist air transport cockpit designers with developing decision aids and displays that would provide new levels of pilot SA needed to support the Free Flight concept of transferring separation responsibility from the ground-based air traffic control system to the flight deck. In addition, a general aviation derivative of the tool could be used for designing cockpit systems for general aviation pilots whose wider range of experience and skills require displays and instrumentation that must be robust to situational awareness needs while inhibiting information overload.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA often includes SA in the standard data collection process during simulator experiments and flight tests of new systems. The ability to predict pilot SA during the design of a new system will greatly improve the efficiency of the design process while reducing the costs. In addition, the required investigation to support the modeling effort will lead to a greater understanding of SA in aviation safety from a basic research perspective.
| PROPOSAL NUMBER: | 02- A1.02-7454 (For NASA Use Only - Chron: 024545 ) |
| SUBTOPIC TITLE: | Propulsion and Airframe Failure Data and Accident Mitigation |
| PROPOSAL TITLE: | Damage Tolerant Sandwich Composite Structures for Turbine Engine Components |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
WebCore Technologies Corp.
591 Congress Park Dr.
Dayton , OH 45459 - 0000
(937 ) 435 - 5034
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Rob Banerjee
rbanerjee@webcoreonline.com
591 Congress Park Dr.
Dayton , OH 45459 - 0000
(937 ) 435 - 5034
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new capability for building lightweight, damage-tolerant, and affordable composite sandwich structures for turbine engine components will be developed. The new sandwich composites proposed herein will be produced with an innovative composite core material (TYCOR), braided fabrics for the facings, and Vacuum Assisted Resin Transfer Molding (VARTM) process. The combination of these three elements will lead to an integrated composite sandwich panel that is affordable and offers improved damage tolerance compared to traditional composites. This Phase I SBIR program will comprise several technical tasks involving sandwich panel design and optimization for ballistic impact performance, mechanical testing of flat panels, VARTM molding of a full case and half case, ballistic testing of flat panels and cases, fabrication and mechanical testing of attachment flange sub-elements, and a material and process cost analysis. GE Aircraft will serve as a key partner on the program. The goal is to demonstrate that TYCOR composite panels meet the structural, manufacturing, and affordability requirements for primary, complex-shaped turbine engine components, while offering adequate damage tolerance and reduced weight compared to metallic components.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
This technology is pervasive and can be used for aerospace, marine, industrial, and transportation applications for ligtweight and durable composite structures.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This technology can be used for general aviation aircraft engines.
| PROPOSAL NUMBER: | 02- A1.02-8080 (For NASA Use Only - Chron: 023919 ) |
| SUBTOPIC TITLE: | Propulsion and Airframe Failure Data and Accident Mitigation |
| PROPOSAL TITLE: | Development of a rugged, fuel tank compatible, oxygen concentration sensor |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Advanced Projects Research Inc
1925 MCKINLEY AVE SUITE B
LA VERNE , CA 91750 - 5800
(909 ) 392 - 8853
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tobias Rossmann, Ph.D.
toby.rossmann@advancedprojects.com
1925 MCKINLEY AVE SUITE B
LA VERNE , CA 91750 - 5800
(909 ) 392 - 3155
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to engineer a compact, robust, optically-based sensor for measuring local oxygen concentration in aircraft fuel tanks. This system will utilize absorption of rapidly scanned Vertical Cavity Surface Emitting Diode Lasers (VCSELs) by molecular oxygen. This proposed system can measure 100 ppm to 100% oxygen in ambient temperatures from -100 to 300 F utilizing a new spectroscopic frequency domain detection scheme known as the wavelength agile spectral-harmonic (WASH) technique. The wavelength agile aspect of the laser source allows for temperature insensitive measurements of oxygen concentration over a wide range of pressures (0.1 atm to 50 atm). The system will also possess auto-calibration capabilities, the ability to withstand temporary immersion in all liquid fuels, fast time response (~100 msec), and long operating life (> 10,000 hrs).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
There are many commercial and military applications for an accurate and rugged fuel tank oxygen concentration sensor. The fuel tank oxygen sensor could be used in both new and retrofit commercial aircraft as a control sensor for fuel tank protection systems. The reliable and precise instrument can be used to control onboard inert gas generation systems (OBIGGS) for cargo compartment fire suppression, fuel tank inerting, and emergency breathing oxygen systems (OBOGS) for passengers and crew. The key to the commercial viability of this product is the accuracy of the sensor, its ability to handle harsh environments including highly variable temperatures and pressures, and its reliability and lifetime, which we propose to engineer into the system. The long operating lifetime and stability of this measurement system in challenging operating environments are superior to existing oxygen measurement strategies.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA is concerned with the prevention of hazardous and accident conditions and the mitigation of their effects when they do occur. One particular emphasis is on fire. The prevention, detection, and suppression of fires are critical goals of accident mitigation. Aircraft fires represent a small number of actual accident causes, but the number of fatalities due to in-flight, post-crash and on-ground fires is large. The proposed oxygen concentration sensor provides a key element for an inerting system for the prevention of fires in fuel tanks.
| PROPOSAL NUMBER: | 02- A1.03-7779 (For NASA Use Only - Chron: 024220 ) |
| SUBTOPIC TITLE: | Automated On-Line Health Management and Data Analysis |
| PROPOSAL TITLE: | Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on OSA |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
WILLIAMS-PYRO, INC.
200 Greenleaf street
Fort Worth , TX 76107 - 1331
(817 ) 872 - 1500
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Kartik Moorthy
Kartik.Moorthy@williams-pyro.com
200 Greenleaf Street
Fort Worth , TX 76107 - 1331
(817 ) 872 - 1500
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR describes diagnostic and reasoning approaches that are applicable in a wide set of domains, specifically the design and development of Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on Open Systems Architecture for Aircraft Wiring Systems. An Embedded Locator And Breaker (ELaB) will be designed that will not only identify arc faults before they occur, but also provide a precise location of potential causes, such as insulation damages, that could lead to an arc. The ELaB will be a self-contained, portable test set based on open systems architecture, thus allowing state-of-the-art technologies such as Reflectometry Techniques to be integrated with existing Arc Fault Circuit Breakers (AFCB). Each ELaB will be based on VLSI/MEMS technology and will incorporate several systems on a microchip: a wiring testing and fault location system based on RF reflectometry techniques, a dynamic on-line wire failure analysis and diagnosis system based on Artificial Neural Network combined with signal processing techniques, and a switching system that automates the testing process for large bundles of multiple wires. Electromechanical adaptability of existing systems will allow on-board data transfer capabilities from wires under test to an on-board Automated Test System (ATS).
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
WPI?s proposed Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on Open Systems Architecture for Aircraft Wiring Systems will further efforts to extend the life of aging aircraft as well as reduce maintenance related costs by using Embedded Locator and Breaker (ELaB) to locate arcing conditions and determine insulation degradation within electrical wiring. ELaB will also improve safety by identifying and preventing arcing conditions before a fire can occur. Significant commercial applications exist outside of the aerospace industry including ships, vehicles, manufacturing equipment, and electrical equipment where arcing can cause fire and loss of life.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
WPI?s proposed Embedded Dual-Function Arc Fault Circuit Breaker/ Locator based on Open Systems Architecture for Aircraft Wiring Systems will further efforts to extend the life of aging aircraft as well as reduce maintenance related costs by using Embedded Locator and Breaker (ELaB) to locate arcing conditions and determine insulation degradation within electrical wiring. ELaB will improve maintenance efficiency and reduce maintenance costs by reducing the amount of maintenance time spent inspecting wire for microscopic cracks that could lead to arcing. For NASA, ELaB will also improve crewmember safety by identifying and preventing arcing conditions before a fire can occur and enhance operational readiness.
| PROPOSAL NUMBER: | 02- A1.03-8719 (For NASA Use Only - Chron: 023280 ) |
| SUBTOPIC TITLE: | Automated On-Line Health Management and Data Analysis |
| PROPOSAL TITLE: | Control of Systems with Actuator Failures |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Techno-Sciences Inc
10001 Derekwood Ln
Lanham , MD 20706 - 4388
(301 ) 577 - 6000
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Gaurav Bajpai
gaurav@technosci.com
10001 Derekwood Ln
Lanham , MD 20706 - 4388
(301 ) 577 - 6000
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A number of fatal aircraft accidents in recent years have been linked to component failures. With the predicted increase in air traffic these numbers are likely to increase. With reduction of fatal accidents as motivation, the proposal plans to investigate design of fault tolerant control system for aircrafts undergoing actuator failures. The feasible approach for such a control scheme is to predesign various controllers anticipating these failures and switching to appropriate controller when the failure occurs. It is found that use of nominal controller when actuators fail may lead to catastrophic accidents. Switching to an appropriate controller enabled by the available redundancy in actuation allows the system to perform adequately even when these failures occur. However, the predesign for actuator failures is not trivial as the position at which the actuators fail is not known a priori. For linear systems the problem has been solved in recent literature; however failures when they occur can cause excursions into nonlinear regimes. The primary thrust of this research would be to extend the results in nonlinear control theory to accommodate actuator failures in aircraft.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Actuator failures such as stuck control surfaces when they occur in commercial aircraft can cause catastrophic accidents and fatal loss of life. The primary application area of the proposed work is to improve the safety and performance of these vehicles in face of such failures. Since the proposed work addresses the problem of actuator failures using the systems approach these techniques will be applicable to a broad range of systems including other aerospace vehicles, ground and sea vehicles, hazardous chemical plants, nuclear power plant, robotic manipulators and others. The value addition in increased safety and performance achieved because of the control techniques to be developed from this research cannot be overestimated. Additionally, the design techniques will also provide a framework in order to synthesize fault tolerant systems making contributions to the development of autonomous systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Several design techniques to be developed in the proposed work are directly applicable to improve the safety and performance of aerospace vehicles in case of components failures involving the actuators. Since NASA has a great interest in developing autonomous systems, the work will provide a means to synthesize fault tolerant systems which can continue to perform under adverse operating circumstances even after failures. These techniques prove to be invaluable when especially when the system is deployed in a remote location or when continued safety and performance are desired features of the system.
| PROPOSAL NUMBER: | 02- A1.03-9284 (For NASA Use Only - Chron: 022715 ) |
| SUBTOPIC TITLE: | Automated On-Line Health Management and Data Analysis |
| PROPOSAL TITLE: | Smart Low-Cost Electronic Module for Simultaneous Sensor and Process Faults Moni |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Intelligent Automation, Inc.
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5242
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Roger Xu
hgxu@i-a-i.com
7519 Standish Place Suite 200
Rockville , MD 20855 - 2785
(301 ) 294 - 5200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The detection and isolation of air vehicle process failures is difficult because air vehicle dynamics are nonlinear and the vehicle has many important and complicated sub-systems. The fault diagnosis performance is further complicated by the presence of sensor failures. In this proposal, Intelligent Automation, Incorporated (IAI) proposes a novel approach to perform simultaneous diagnosis of sensor and process faults for air vehicles. This algorithm can be embedded into low cost electronics. First, two independent residual vectors (RVs) for detection and isolation of the sensor and process faults are built. This is in sharp contrast to conventional methods, which can deal with either sensor failures or process failures but never both. Second, to isolate faults, the RV is transformed into a set of structured residual vectors (SRVs), where one SRV is made insensitive to a specified subset of faults, while remaining sensitive to other faults. The proposed technology is relevant to this subtopic because we will develop an electronic module that can be embedded in low cost sensor electronics to quickly identify both sensor and process faults.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed sensor and process faults diagnosis module is novel by itself and will have many practical NASA applications such as spacecraft, flight control systems, etc. The developed technology will result in an increase in inspection efficiency and inspection unit autonomy while reducing the demand on NASA maintenance personnel and the total ownership cost for NASA asset.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Health monitoring technology has many applications such as health monitoring for engines, helicopter gearbox systems, jet and automotive engine diagnostics, and commercial and military aircraft. The jet and automobile industries are multibillion dollar industries that are commercial targets for this technology. Our goal is to develop a generic electronic module, which can be used for many systems.
| PROPOSAL NUMBER: | 02- A1.04-8884 (For NASA Use Only - Chron: 023115 ) |
| SUBTOPIC TITLE: | Aircraft Icing Systems |
| PROPOSAL TITLE: | Low-Power Aircraft Deicing System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ 08618 - 2302
(609 ) 538 - 0444
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert M. McKillip, Jr.
bob@continuum-dynamics.com
34 Lexington Avenue
Ewing , NJ 08618 - 2302
(609 ) 538 - 0444
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Two novel approaches for providing de-icing of aerodynamic surfaces are proposed for research and development. The first represents a ?snap through? actuation mechanism that can abruptly and reversibly alter the shape of aerodynamic surfaces in-flight to discrete self-locking positions. The snap-through system is ideally suited for deicing by providing mechanical debonding and removal of accreted ice with minimal weight and power requirements. The second mechanism incorporates interleaved sliding surfaces that provide suitable surface strains for debonding accreted ice on airfoils. Both systems incorporate Shape Memory Alloy (SMA) materials as their prime movers. SMA-based systems are more durable than pneumatic systems and provide higher force and strain output per unit volume than other smart material based actuators. The proposed methods offer up to an order of magnitude reduction in required power over other impulsive electromechanical technologies due to the modest currents required for SMA wire heating. In Phase I, dynamic models of each of the devices will be developed and demonstration models constructed and tested to establish effectiveness for representative deicing situations. Construction and testing of a full-scale prototype will be performed in Phase II.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed deicing system(s) for aerodynamic surfaces can be applied on all commercial aircraft certified for flight in instrument meteorological conditions. The device?s low power, light weight, small size, robust operation and potentially low cost give it a significant market advantage over current technology de-icing systems. The technology may provide enhanced icing protection for rotorcraft, with significant power reductions over current thermal surface heating systems.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The deicing systems proposed for R&D directly supports NASA?s continuing interest in researching the most effective means for aircraft icing detection, removal, and mitigation. The resulting system could be used to help support various research programs investigating these technologies in the NASA Glenn Icing Tunnel or on NASA?s Icing Research Aircraft (Twin Otter); additionally, it may also provide technology to support various NASA initiatives in rotorcraft icing research.
| PROPOSAL NUMBER: | 02- A2.01-8024 (For NASA Use Only - Chron: 023975 ) |
| SUBTOPIC TITLE: | Propulsion System Emissions and Noise Prediction and Reduction |
| PROPOSAL TITLE: | Artificial Neural Net Chemistry Module for Large Eddy Simulations |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
CFD Research Corp
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Steven Cannon
jls@cfdrc.com
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Combustion Large Eddy Simulation (LES) is a vastly improved method of modeling turbulent-combustion in gas turbine combustors, and will provide improved emissions/instability prediction capability of UEET combustors. It is widely recognized that one of the best subgrid turbulence-combustion models is the Linear Eddy Mixing (LEM) model with multi-step reactions. However, this model is not commonly used in the design environment for one main reason: computational time.
In this SBIR, we propose to develop a subgrid LEM module with multi-step Jet-A kinetics that is 100 times faster than the state-of-the-art direct LEM. This new, innovative method performs off-line LEM calculations over a range of turbulence levels and compositions to train an artificial neural net (ANN). The ANN is then used to determine the chemical source terms required in the combustion LES calculation. In Phase I of this SBIR, the feasibility of developing the LEM/ANN module will be demonstrated by training a one-step, five species Jet-A fuel oxidation mechanism. The preliminary LEM/ANN module will be implemented into the CFD-ACE+ code, validation performed, and speed-up demonstrated. At the end of Phase I, the module will be delivered to NASA for incorporation into the NCC code. In Phase II, the LEM/ANN approach will be extended to include multi-step Jet-A kinetic mechanisms, and applied to UEET combustor configurations.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The LEM/ANN chemistry module will significantly improve combustor design methods. The ability to reduce emissions, avoid combustion-driven instability, and to investigate high-payoff ideas will be possible. The software will be useful for gas turbine manufacturers, burner and boiler manufacturers, chemical processing industry, and the automotive industry. The module will be incorporated into CFDRC's commercial code, CFD-ACE+.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The LEM/ANN chemistry module developed in this SBIR will be useful in the cost-effective design and analysis of liquid-fueled, high performance combustors. The LES combustor design tool will be used to help meet the NASA UEET emission goals. The module will be supplied to NASA for incorporation into the National Combustion Code.
| PROPOSAL NUMBER: | 02- A2.01-9022 (For NASA Use Only - Chron: 022977 ) |
| SUBTOPIC TITLE: | Propulsion System Emissions and Noise Prediction and Reduction |
| PROPOSAL TITLE: | High Temperature Polyimides for Resin Transfer Molding Process |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Triton Systems Inc.
200 Turnpike Road
Chelmsford , MA 01824 - 4000
(978 ) 250 - 4200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Lawino Kagumba
lkagumba@tritonsystems.com
200 Turnpike Road
Chelmsford , MA 01824 - 4000
(978 ) 250 - 4200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Triton Systems, Inc. proposes to develop novel low melt flow viscosity, environmentally friendly high temperature polyimide resin that can address the need for low cost, lightweight, complex geometry composite manufacturing. Triton has teamed with composite manufacturer and end users to assist in evaluation of its new RTM/VARTM high temperature polyimides. The proposed program will develop resins with melt flow viscosity lower than 10 poise at greater than 280?C processing temperature. High temperature RTM/VARTM resins would allow ?out-of-autoclave? manufacturing, which reduces manufacturing cost and allow for large, complex shape designs. The new high temperature resin will be applicable to propulsion systems such as aircraft gas turbines, rocket and turbine engines, and auxiliary power in aircraft and space vehicles.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Triton has teamed with end users to evaluate the development of the new RTM/VARTM high temperature resins for compatibility with their current composite manufacturing. This teaming arrangement will assist Triton to develop the resin within the manufacturer production specifications. The potential commercial applications are aircraft jet engines, rocket and turbine engines, and auxiliary power in aircraft and space vehicles.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Development of new low melt flow viscosity (RTM/VARTM), environmentally friendly high temperature polyimide resins would allow ?out-of-autoclave? manufacturing of large structures such as large composite tanks for the next generation Reusable Launch Vehicles (RLVs). Currently the size of the autoclave predicts the size of the components that can be fabricated, which is a limitation for development of the next RLVs.
| PROPOSAL NUMBER: | 02- A2.01-9731 (For NASA Use Only - Chron: 022268 ) |
| SUBTOPIC TITLE: | Propulsion System Emissions and Noise Prediction and Reduction |
| PROPOSAL TITLE: | Acoustic Test Method for Turbofan Engine Exhaust Systems at Cruise Conditions |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Aero Systems Engineering, Inc.
358 East Fillmore Avenue
St. Paul , MN 55107 - 1289
(651 ) 220 - 1290
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Dean F. Long
dlong@aerosysengr.com
358 East Fillmore Avenue
St. Paul , MN 55107 - 1289
(651 ) 227 - 7515
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The exhaust flow from a turbofan engine operating at typical cruise conditions generates noise as turbulent flow interacts with the basic shock cell pattern. This can be a significant source of noise within the aircraft cabin. The proposed innovation is a new method for testing the acoustics of model scale turbofan engine exhaust systems at cruise conditions in a transonic wind tunnel. This would complement the aerodynamic tests now conducted in the wind tunnel. Currently, acoustic data at cruise conditions is only obtained from costly flight tests. Wind tunnel tests are desirable to simulate the proper flight conditions, but acoustic measurements are difficult in this environment. Microphone arrays and specialized array processing techniques are required to separate model noise from tunnel induced noise and reverberation. The new method involves three specific areas of innovation: a) phased-array noise measurement methods, b) evaluating potential modifications to an existing wind tunnel, and c) evaluating means for reducing model air supply noise. Preliminary measurements demonstrate that each of these problems is solvable. The proposed research will then lead to a successful commercial ?service? to airframe manufacturers interested in increasing passenger comfort through better understanding of the noise sources that influence the passenger cabin environment.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The principal commercial application of this research will be an expanded ?test service? available at our test laboratory to conduct model scale acoustic tests on aircraft components in a 66-inch transonic wind tunnel where aerodynamic performance measurements on exhaust nozzle systems are currently conducted. This service would be available to commercial airframe and engine manufacturers interested in minimizing cabin interior noise levels created by the operation of turbofan engines. Another application relates to acoustic diagnostics of full scale turbofan engines under test conditions. During maintenance procedures an engine is extensively tested prior to remounting on the aircraft to ensure proper operation. These tests occur in hard walled test cells, not unlike the hard walls of a wind tunnel. We have begun discussions with engine manufacturers to determine how acoustic array technology can be applied to maintenance diagnostics.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA conducts acoustic measurements on aircraft systems and components in several wind tunnels. The research to be conducted on this program will complement NASA tests. The subspace methodology described in this proposal is being developed on a related Air Force SBIR and will be refined for use on this program. It is common in the field of communication but has not been applied to aeroacoustic studies. It is not restricted to the transonic problem and may provide superior performance to standard techniques now in use for the low speed aeroacoustic problem. In particular, it may improve the noise source location techniques now used to identify source locations for tests conducted in NASA wind tunnels, such as the 40- X 80-Ft wind tunnel at NASA ARC. This research will provide significant advancement of adaptive beamforming techniques applied to conventional aeroacoustic wind tunnel tests.
| PROPOSAL NUMBER: | 02- A2.02-8033 (For NASA Use Only - Chron: 023966 ) |
| SUBTOPIC TITLE: | Electric and Intelligent Propulsion Technologies for Environmentally Harmonious Aircraft |
| PROPOSAL TITLE: | The Double-Mixing Vortex Mixer/Injector |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Sun Valley Technology Inc.
26700 Renaissance Parkway, Unit 4
Warrensville Heights , OH 44128 - 5764
(216 ) 464 - 1322
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Tai-Yen Sun
svtfrank@aol.com
26700 Renaissance Parkway, Unit 4
Warrensville Heights , OH 44128 - 5764
(216 ) 464 - 1322
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The performance of the currently used Auto Thermal Reformer(ATR) in the Solid Oxide Fuel Cell (SOFC) suffers degradation from carbon depostition due to inadequate mixing of fuel/steam/air in the reformer. An innovative concept of Double-Mixing Vortex (DMV) mixer/injector is proposed to remedy the defect of the ATR. The improved mixing outcome from the DMV mixer is resulted from two consecutive mixing steps built in the device. The primary mixing is achieved by direct-impinging scheme of fuel, air, and steam jets in the fuel passages. The secondary mixing of the fluid is achieved by setting-up swirling vortex in the mixing chamber of the mixer in the later stage. Finally, extremely fine drops in the spray are formulated due to the expansion of small air/steam bubbles which are entrapped in the fuel during the mixing process in the mixing chamber. A two-fluid mixer of similar design has been tested by SUN VALLEY TECHNOLOGY (SVT) successfully in the industrial burners. The DMV mixer will be expected to achieve improved mixing of fluids and extremely fine drops in the spray for the proper fuel distribution in the ATR applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed Double-Mixing Vortex (DMV) mixer/injector will achieve a much superior quality for fluid mixing. It can be used in the Auto Thermal Reformer (ATR) of a Solid Oxide Fuel Cell (SOFC) for the auxiliary power unit (APU) in an aircraft. The sprays generated from this mixer/injector are extremely fine and uniform, which is great for gas-turbine-combustor or industrial-burner applications for high turn-down ratio runnings. It can also be used in the general liquid/gas or gas/gas mixing where fast mixing within a compact space is required.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed Double-Mixing Vortex (DMV) mixer/injector will achieve a much superior quality for fluid mixing. It can be used in the Auto Thermal Reformer(ATR) of a Solid Oxide Fuel Cell (SOFC) for the auxiliary power unit (APU) in an aircraft. The extremely fine sprays generated from this mixer/injector along with its high turn-down ratio will be beneficial to gas-turbine-combustor runnings. It can also be used in the desulfurizing process for the hydrocarbon fuels.
| PROPOSAL NUMBER: | 02- A2.02-9354 (For NASA Use Only - Chron: 022645 ) |
| SUBTOPIC TITLE: | Electric and Intelligent Propulsion Technologies for Environmentally Harmonious Aircraft |
| PROPOSAL TITLE: | Co-Generation of High Purity Hydrogen and Electric Power |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ceramatec, Inc.
2425 South 900 West
Salt Lake City , UT 84119 - 1517
(801 ) 978 - 2163
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joseph Hartvigsen
jjh@ceramatec.com
2425 South 900 West
Salt Lake City , UT 84119 - 1517
(801 ) 972 - 2455
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Hydrogen centered technologies such as fuel cells have generated much attention as a means of reducing emissions and dependence on fossil fuels. Unfortunately there are no ideal solutions to the problems of hydrogen production and storage. An innovative integrated hybrid solid state electrochemical system is proposed as a means of overcoming many of the fundamental problems pertaining to hydrogen production and purification, fuel reformation, and fuel cell operation. The proposed process is a physical, chemical and thermal integration of three operations; (1) hot electrolysis of steam to produce high purity hydrogen, (2) electrochemical partial oxidation of hydrocarbon fuel, (3) electric power generation by a solid oxide fuel cell fueled by the reformed hydrocarbon. Required process inputs are air, steam and hydrocarbon fuel, producing electric power, high purity hydrogen and an exhaust stream suitable for CO2 sequestration, containing only carbon dioxide and steam. The concept allows design flexibility in meeting the desired mix of electric power produced by the integrated solid oxide fuel cell, and high purity product hydrogen suitable for use in low temperature fuel cells. Current developments in intermediate temperature electrolyte materials will enable operation of this device in the temperature range centered around 600?aC, favorable to reforming thermodynamics.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The proposed innovation would be generally applicable to the following non-NASA commercial applications:
(1)Aircraft and automotive auxiliary power
(2)Highway truck hotel power
(3)Fuel processing for automotive fuel cell electric vehicles
(4)Point of use hydrogen generation
(5)Stationary electric power generating plants
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed innovation would find application in meeting NASA needs related to:
(1)Fuel processing for electric aircraft propulsion and power systems
(2)Ground based hydrogen production with CO2 sequestration
| PROPOSAL NUMBER: | 02- A2.03-8342 (For NASA Use Only - Chron: 023657 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Flow Test for Rotating Chamber Pulse Detonation Engine |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SPIRITECH Advanced Products, INC.
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric J. Gamble
egamble@spiritech.cc
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Pulse detonation engines hold promise to increase performance of air-breathing propulsion systems by taking advantage of the increase in cycle efficiency due to the constant-volume heat addition characteristics of detonative combustion. SPIRITECH is developing a pulse detonation engine, the Rotating Chamber PDE, which utilizes multiple combustion chambers on a rotating spool to improve inlet and nozzle performance and to eliminate the need for valves. Efficient flow of the fuel-air mixture into the detonation chambers as they rotate is critical for achieving high levels of thrust. A flow test is proposed using a rotating plate to simulate the flow characteristics into the rotating detonation chamber. This Phase I study will provide the data necessary to quantify the flow efficiency through pulse detonation engines. Additional testing of other critical PDE engine components and key technologies will be performed in the Phase II program to develop the technology base required for a prototype in Phase III.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The potential commercial market for this device is enormous, since the successful execution of this concept could revolutionize aviation and aerospace markets.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Rotating Chamber PDE is a lightweight, air-breathing engine offering high specific impulse. This engine offers advantages to replace more expensive turbojets and less capable rockets in high speed aircraft. Additionally, it may be incorporated in combined cycle applications, where it is combined with a scramjet for a single-stage-to-orbit reusable launch vehicle (RLV) or as the first stage in a two-stage-to-orbit RLV using rockets or a rocket-based combined cycle for the second stage.
| PROPOSAL NUMBER: | 02- A2.03-8358 (For NASA Use Only - Chron: 023641 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Improving Off-Design Nozzle Performance Using Fluidic Injection |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SPIRITECH Advanced Products, INC.
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Eric Gamble
egamble@spiritech.cc
880 Jupiter Park Dr. #8
Jupiter , FL 33458 - 8901
(561 ) 741 - 3441
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Use of fluidic injection of high-pressure air is proposed to improve nozzle performance and reduce the off-axis component of thrust at off-design flight conditions, generally at low Mach number and low pressure ratio. Hypersonic flight vehicles are typically designed with a high expansion ratio single expansion ramp nozzle (SERN) with a design point at high Mach number flight conditions. However, at low Mach number flight, lower nozzle expansion ratios are required for optimum performance. Thus, these vehicles suffer from poor performance throughout much of the low-speed flight regime. In addition, the long SERN ramp creates a significant off-axis thrust at off-design, which must be overcome by shifting the vehicle center-of-gravity or by using the vehicle?s control surfaces. This concept manages the engine and freestream flows to alleviate these problems and improve the overall vehicle performance. The Phase I effort will focus on employing 1-D and CFD analyses to prove concept feasibility and to define the injectant pressure and flow requirements. The Phase II program will focus on a preliminary design, including integration issues, design of the secondary valve and injection features, and component testing to verify overall performance gains.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The industries within this market are large and include Airframers, Aircraft Engine Manufacturers, the DoD, and NASA. Some products that stand to benefit from this innovation are Advanced Military Aircraft, Unmanned Air Vehicles, Hypersonic Vehicles, and LO Vehicles.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Fluidic Nozzle benefits NASA?s development of Hypersonic and high speed vehicles by providing a lightweight, low cost aircraft system for achieving high vectoring effectiveness while maintaining optimum thrust performance. As a result, the commercial benefit is three-fold:
- It reduces aircraft weight,
- It improves nozzle performance, and
- It reduces life-cycle cost by providing a low-cost vectoring solution.
| PROPOSAL NUMBER: | 02- A2.03-8672 (For NASA Use Only - Chron: 023327 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Front Turbine Engine Concept |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AP Solutions, Inc
21000 Brookpark Road, MS501-6
Brookpark , OH 44135 - 3191
(440 ) 331 - 7875
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Leo Franciscus
marinerleo@aol.com
21000 Brookpark Road, MS501-6
Brookpark , OH 44135 - 3191
(216 ) 433 - 3646
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This SBIR will determine the feasibility of an innovative gas turbine engine concept which has a turbine in front of the compressor. This engine concept, referred to as the "Front Turbine Engine Concept" (FTEC), has the potentials for extending the flight speed at which turbomachinery can operate. At hight flight speeds the front turbine extracts sufficient energy from the incoming air thus reducing the air temperature into the compressor and enabling the turbomachinery to operate at high flight speeds (up to Mach 5).
Engine simulations will be conducted on the FTEC to determine the requirements of the components to match the cycle requirements over the complete flight path (takeoff to Mach 5 cruise). The most feasible engine configuraton (one or two spools) will be determined.
Preliminary design will be conducted on the front turbine to identify a prelininary turbine configuration to meet cycle requirements.
Technology requirements for all of the engine components will be assessed.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The FTEC has potential applications for hypersonic propulsion systems up to Mach 5. The most immediate applications would be in the military arena for manned or unmanned hypersonic aircraft (cruise missile). However, It also has potential in commerical
applications in the high-speed transport arena.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The FTEC has potential application in the high-speed transport.
| PROPOSAL NUMBER: | 02- A2.03-8862 (For NASA Use Only - Chron: 023137 ) |
| SUBTOPIC TITLE: | Revolutionary Technologies and Components for Propulsion Systems |
| PROPOSAL TITLE: | Novel Titanium-based Lattice Block Structures |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
TITECH INTERNATIONAL, INC.
4000 West Valley Boulevard
Pomona , CA 91769 - 3060
(909 ) 595 - 7455
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Edward Chen
ti_castings@msn.com
4000 West Valley Boulevard
Pomona , CA 91769 - 3060
(909 ) 595 - 7455
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Lattice Block Materials (LBM) are innovative periodic cellular materials that derive their outstanding mechanical performance from a structure of highly ordered internal triangles, rather than the properties of the parent material. To date, they have been successfully cast for many ferrous and non-ferrous metals, but not reactive metals such as titanium and gamma titanium aluminides. As titanium is a critical aerospace material, and gamma is a key candidate for many future aerospace systems, TiTech International, Inc. proposes to use its unique casting production technology to manufacture prototype titanium-based LBM in this SBIR Phase I effort. The goal is to produce titanium and g-TiAl LBM as near-net shape and affordably as possible, while meeting performance and properties requirements for future aerospace systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Essentially, any application and/or industry that need superior strength-to-density within relative affordability while retaining the physical properties of titanium and gamma alloys could use LBM structures. Furthermore, those that require potential replacements for Ni-based superalloys at lower temperatures and for titanium alloys at higher temperatures could consider gamma alloys. Potential commercial applications include aero engine components, automotive engine components, and aircraft and spacecraft structural applications. Other possible uses of LBM include components for furniture, shipboard structures, building structures, automotive vehicle frames, and a potentially limitless number of other possibilities.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Titanium and gamma alloy LBM can be used as low weight structures for numerous applications for the engine and frame for next generation space launch and hypersonic vehicles. For example, gamma LBM could be considered for engine tiles and sandwich structures for TPS.
Other potential NASA applications include aircraft engine components such as casings and nozzle flaps for next generation aircraft gas turbines.
| PROPOSAL NUMBER: | 02- A2.04-8134 (For NASA Use Only - Chron: 023865 ) |
| SUBTOPIC TITLE: | Airframe Systems Noise Prediction and Reduction |
| PROPOSAL TITLE: | Improving Binaural Simulation of Structural Acoustics |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AUSIM, INCORPORATED
241 Polaris Avenue
Mountain View , CA 94043 - 4514
(650 ) 322 - 8746
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Agnieszka Jost
jstorckman@ausim3d.com
241 Polaris Avenue
Mountain View , CA 94043 - 4514
(650 ) 322 - 8746
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovation is an implementation of an improved, more efficient method for processing individual Head-Related Transfer Function (HRTF) data during the process of rendering audio in a structural acoustic simulated environment. Binaural or 3D-simulated audio has been identified as a useful method for analyzing acoustic and vibro-acoustic data. The highest quality audio simulation requires the processing of HRTF data to create the most accurate 3D audio rendering; however, such processing requires an extensive amount of CPU cycles and is one of the biggest limiting factors of the complexity of the audio simulation. By significantly improving the efficiency of HRTF processing, through such techniques as Singular Value Decomposition (SVD) and Equivalent Source Reduction (ESR), the complexity of the structure being acoustically modeled can be increased. In fact, the capacity of the audio rendering engine can be increased to the point where not only single point audio sources can be modeled, but surface-defined audio sources can be defined, using an array of single-point sources. Such surface-defined audio sources make the audio simulation of vibro-acoustic systems feasible. Such a system will act as an effective tool for assessing the noise characteristics and ?sound quality? of structural acoustic prototypes.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial applications of this technology would be in the automobile industry, where millions of dollars are spent every year in order to find ways to make new vehicles operate more quietly. The acoustics analysis capabilities that would be enabled with the development of the SVD/ESR-enhanced 3D audio simulation software could be applied widely throughout the automobile business by licensing it to be integrated with existing and broadly used industrial acoustics analysis packages such as the Virtual Acoustics Sciences product line. Such a combined package would offer significantly more capability to engineers designing to optimize acoustics than any other package available today.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
When designers are given the ability to simulate the expected noise generated from an object or structure with a force applied which induces vibration, this noise can be characterized by examining its volume and tonal qualities and determinations can be made regarding how perceptually problematic the projected noise might be in field conditions. This capability will allow more accurate analysis of and experimentation with the acoustics of designs for aircraft and International Space Station structural components.
| PROPOSAL NUMBER: | 02- A2.04-9271 (For NASA Use Only - Chron: 022728 ) |
| SUBTOPIC TITLE: | Airframe Systems Noise Prediction and Reduction |
| PROPOSAL TITLE: | Development of High Frequency Excitation Devices for Noise Reduction |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
INNOVATIVE TECHNOLOGY APPLICATIONS CO.
P.O. Box 6971
Chesterfield , MO 63006 - 6971
(314 ) 576 - 1639
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Alan Cain
ITACabc@aol.com
P.O. Box 6971
Chesterfield , MO 63006 - 6971
(314 ) 576 - 1639
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The noise level of new and existing aircraft need to be reduced to meet the increasingly stringent US and international airport standards. High frequency excitation (wavelengths much shorter that amplified instabilities) of jet flows is a new technology that has the potential to reduce acoustic levels significantly in addition to lowering turbulence levels. In application, forcing is applied at frequencies that are much higher than ones associated with the large-scale, two-dimensional structures associated with the jet, but much lower than the Kolmogorov scale. The development of the jet is substantially altered through two mechanisms. First, the high-frequency forcing increases the turbulent dissipation rate. Second, it reduces the turbulent production. These two mechanisms together lead to a significant decrease in the energy in the large-scale two-dimensional motion and subsequently lowering turbulent and noise levels. One benefit of the control is that the forcing needs only to possess frequencies that are above a certain range. This single frequency requirement encompasses a wide array of potentially suitable devices.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The engine retrofitting and new engine development market for meeting stage IV requirements for commercial aircraft is in the order of billions of dollars for the next 10 and 20 years. Phase II flight tests will guide the implementation of such systems on commercial jet engines. The experiments will be combined with scaling analysis to develop guidance for optimal system hardware designs that can be patented. These designs are of great values to aircraft and engine manufacturers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed technology development could open the door to further understanding and breakthroughs (beyond the proposed SBIR program) by NASA researchers. These breakthroughs in noise reduction may advance the national interest in a quieter air travel industry.
| PROPOSAL NUMBER: | 02- A3.01-8246 (For NASA Use Only - Chron: 023753 ) |
| SUBTOPIC TITLE: | Small Aircraft Transportation System Technologies |
| PROPOSAL TITLE: | SATS Virtual Market Place Facilitating Traffic Flow Management |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metron Inc
11911 Freedom Drive
Reston , VA 20190 - 2835
(703 ) 234 - 0782
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Chris Brinton
brinton@metsci.com
131 Elden Street
Herndon , VA 20170 - 2835
(703 ) 787 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Small Aircraft Transportation System (SATS) concept envisions a dramatic change in demand on National Airspace System (NAS) resources: a significantly increased number of flights operating as needed on Point-to-Point (PTP) routes with smaller aircraft. In addition to the increased demand on the NAS, the dynamic, ?on-demand?, nature of the SATS concept will present even greater challenges to the country?s Traffic Flow Management (TFM) system. The NAS regulates the flow of aircraft through TFM initiatives. However, the current TFM system does not perform well under uncertain demand patterns. The innovation proposed herein creates a website marketplace for providers and consumers of SATS services. More importantly, our innovation links the information from this SATS website to the Nation?s TFM system. Critical information regarding projected demand can be provided to the TFM system to allow the necessary management of the NAS. Advanced portions of this concept include interactivity between the SATS website and the TFM system to notify consumers of small aircraft transportation services regarding projected delays due to congestion along their requested route of flight at their requested flight time.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Significant potential exists for commercial applications of the Small Aircraft Transportation System Virtual Marketplace (SATS-VMP) innovation proposed herein. The SATS-VMP web-site leverages the existing technology of the Internet and World Wide Web to create a marketplace for transactions between buyers and sellers of SATS aviation services. The development, hosting and management of the SATS-VMP web-site is an excellent commercial opportunity for this innovation. Metron Aviation has the infrastructure, expertise, staff and financial resources to host the SATS-VMP web-site. This provides commercial opportunities using multiple revenue models associated with Internet websites, including advertising and commission on sales. Metron Aviation has demonstrated the financial ability to develop and successfully market commercial aviation applications by producing the Enhanced Substitution Module (ESM), which is a commercial tool used operationally by numerous airlines to interact with the Traffic Flow Management System of the National Airspace System.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The Small Aircraft Transportation System (SATS) concept envisions a dramatic change in demand on National Airspace System (NAS) resources: a significantly increased number of flights operating as needed on Point-to-Point (PTP) routes with smaller aircraft. In addition to the increased demand on the NAS, the dynamic, ?on-demand?, nature of the SATS concept will present even greater challenges to the country?s Traffic Flow Management (TFM) system. In order to achieve NASA?s goals for the SATS concept, modern TFM decision support systems will be necessary to enable the SATS concept by handling the increased volume as efficiently as possible. Metron Aviation has led the research and development of numerous systems that interface directly to the TFM system. Many of these systems that improve the efficiency and flexibility of the TFM system have been developed through NASA funding.
| PROPOSAL NUMBER: | 02- A3.01-8431 (For NASA Use Only - Chron: 023568 ) |
| SUBTOPIC TITLE: | Small Aircraft Transportation System Technologies |
| PROPOSAL TITLE: | Gyroplane Development and Demonstration using a Unique Bearingless Rotor System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Global Technology Connection Inc
2839 Paces Ferry Rd. #1160
Marietta , GA 30339 - 5770
(770 ) 803 - 3001
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Ash Thakker
athakker@globaltechinc.com
2839 Paces Ferry Rd. #1160
Marietta , GA 30339 - 0000
(770 ) 803 - 3001
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
It is well known that an outstanding way to achieve a reduction in landing and takeoff speeds is with a hybrid rotary wing and fixed wing aircraft, such as a gyroplane. However, while there are two U.S. companies pursuing development of gyroplanes, Groen Brothers and Carter Copter, neither has included a rotor system that is easy to fly or can adequately control rotor blade flapping during the critical flight conditions.
A far superior rotor for gyroplanes is the Hanson Elastic Articulated (EA) bearingless rotor that grew out of Lockheed California in the early 1960s for light commercial helicopters. It was later further developed on an autogyro by Mr. Tom Hanson.Georgia Tech ASDL has been working with him in evaluating and analyzing the EA bearingless rotor. The inherent features of the EA Rotor look just as promising today, and can provide the missing link in making gyroplanes true PAVs.
This proposal seeks to fulfill the promise of the gyroplane as a personal air vehicle. In Phase I the scientific, technical, and feasibility of the proposed innovation will be demonstrated. It will include a sound business plan outline for production, with a technical plan providing for compatibility with the emerging National Airspace System architecture and a certification plan. This will be accomplished with the assistance of two other organizations in addition to ASD, LLC. These are the Georgia Tech ASDL and Eagle Aviation Technologies Inc.Based on the demonstrated technical feasibility demonstrated in Phase I, the Phase II program will be used to demonstrate through flight testing the innovative gyroplane concept. This will include testing that can be used in conjunction with the certification and business plan developed in Phase I.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Many commercial uses of Personal Air Vehicles can be envisioned in the commercial world. Personal transport, medical transport, emergency personnel, security personnel and recreational uses.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Under the Small Aircraft Transportation System (SATS) Technologies, NASA is seeking Personal Air Vehicle (PAV) advanced concepts that reduce the landing speed for FAR Part 23 aircraft under 6,000 pounds. Advanced concepts for roadable aircraft are also desired. This category must include a sound business plan outline for production, with a technical plan providing for compatibility with the emerging National Airspace System architecture and a certification plan to meet FARS: Part 103 (Ultra-lite vehicle, Part 21.12 (Primary Category Aircraft), Part 23 (Certified Aircraft) or Part 27 (Rotorcraft), or Part 21.191 Advisory Circular AC No: 20-27 series (Experimental Homebuilt Aircraft)
| PROPOSAL NUMBER: | 02- A3.01-9714 (For NASA Use Only - Chron: 022285 ) |
| SUBTOPIC TITLE: | Small Aircraft Transportation System Technologies |
| PROPOSAL TITLE: | Avionics Based Runway Incursion Prevention |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Rannoch Corporation
1800 Diagonal Rd. Suite 430
Alexandria , VA 22314 - 2840
(703 ) 838 - 9780
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Rick Cassell
rcassell@rannoch.com
1800 Diagonal Rd. Suite 430
Alexandria , VA 22314 - 2840
(703 ) 838 - 9780
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes the adaptation of an aircraft based runway incursion advisory and alerting system for general aviation applications. PathProx is a runway incursion advisory and alerting system developed by Rannoch Corporation for air carrier operations. The work proposed under Phase I of this SBIR includes the definition of the developmental needs for adapting the PathProx conflict detection and alerting collision avoidance algorithms to General Aviation (GA) operations. Systems currently being deployed by the FAA are based on a ground infrastructure where runway incursion conflict alerts generated by the system are provided to ATC. Under this operational scenario the pilot is not provided with conflict alert information in the cockpit, leaving the aircraft dependent on the ground ATC infrastructure and human response. A General Aviation runway incursion advisory and alerting system will provide the following safety benefits:
? Reduction in the likelihood of near collisions resulting from runway incursions.
? Improved pilot response in taking evasive actions following incursions.
? Provision of runway incursion alerting at airports not equipped with surface surveillance systems
? Provision of runway incursion alerting at uncontrolled (non-towered) airports
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The result of the Phase I research proposal here would be the definition of the approach to adapting the Rannoch PathProx runway incursion alerting algorithms to General Aviation operations. During Phase II the development would proceed, which would result in the system being available commercially. The intended market is all General Aviation aircraft that are equipped with the Global Positioning System and a minimal map display.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The availability of PathProx runway incursion alerting algorithms for General Aviation would enhance the development of Small Aircraft Transportation Systems (SATS). Specifically, it would enhance pilot situational awareness and provide improved aircraft safety in a cost-effective manner.
| PROPOSAL NUMBER: | 02- A3.02-8048 (For NASA Use Only - Chron: 023951 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Optical switches for secure quantum encryption data transmission network |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
SiWave, Inc.
400 E. Live Oak Avenue
Arcadia , CA 91006 - 5619
(626 ) 821 - 0570
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Cathleen Jones
c.jones@siwaveinc.com
400 E. Live Oak Avenue
Arcadia , CA 91006 - 5619
(626 ) 821 - 0570
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The communication network of the Air Traffic Management system requires highly reliable and secure transmission to protect the secrecy and authenticity of the information being transferred. Systems must meet that criteria and be capable of recognizing and withstanding tempering, spying and physical attacks. These requirements cannot be relaxed without diminishing severely the capability of the communication network, and the consequences of loss of security could be disastrous in the extreme. The only undecipherable encryption method is quantum cryptography in which the encryption key is encoded in a quantum property of the carrier, and detecting a quantum property destroys the quantum coherence, altering its value. This concept implementation requires that the transmission network consisting entirely of optical paths in which random polarization is not destroyed or revealed.
SiWave proposes to develop and test a low loss and hardened 32-port all-optical path switch designed for extreme environmental conditions (thermal, vibration, shock) and suitable for quantum encryption applications in this Phase 1 SBIR. During Phase II, SiWave will fabricate and test the optimized switch designed in Phase I. We will demonstrate the performance of the device for quantum encrypted data transmission applications, and propose modifications to extend its capabilities for better performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
For a medium port count switch such as the 32x32 switch that we propose in this Phase I SBIR, the best known application is to telecommunications, where optical crossconnects and optical add/drop multiplexers have a large market. The projected market size for optical switches in 2006 is $6B and up to $10B by 2010. Another application is to sensors where the sensor connects to the measurement device by fiber optic cable, and to distributed sensor networks where an array of sensors can be interconnected with each other and with multiple measurement systems. These switches can also be implemented in classical computers that use fiber optics. Finally, the application to secure data networks for handling financial, business and information transaction represents a potential market worth billions of dollars per year.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed optical switch from SiWave will enable NASA to create an ultra-secure and reliable quantum encryption communication network for its Air Traffic Management system. The proposed switch will be reliable and low loss and be capable of withstanding severe environmental conditions and physical attacks. In addition, such switch would be compact and low power to reduce the back-up power requirements for operation in severe conditions. SiWave's optical switch can also function as the central crossconnect or router in a high bandwidth optical network, routing multiple high data rate optical signals to different destinations. Such application would increase greatly the data communication capability of NASA, allowing scientists to share and to analyze large volume of data.
| PROPOSAL NUMBER: | 02- A3.02-8938 (For NASA Use Only - Chron: 023061 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | NAS-Wide Environmental Modeling of Alternative Airspace Concepts |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metron Inc
11911 Freedom Drive
Reston , VA 20190 - 2835
(703 ) 234 - 0789
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Terry Thompson
thompson@metsci.com
131 Elden Street
Herndon , VA 20170 - 2835
(703 ) 787 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Leveraging extensive experience from major airspace re-design projects, Metron develops a software system to model the NAS-wide environmental consequences of new airspace concepts. The NAS Environmental Impact Model (NASEIM) is innovative in the following ways:
(1) It solves the NAS-wide data-integration problem;
(2) It solves the data-transformation problem for new airspace concepts involving new procedures, aircraft, emissions characteristics, and airspace usage; and
(3) It solves the computational-burden and scenario-comparison problems inherent in large-scale environmental modeling of new airspace concepts.
This enables NASA to determine, early in concept development, which concepts may have either adverse or beneficial effects on the environment, particularly with regard to aircraft noise. This also enables NASA to determine which elements of the new airspace concepts are causing significant environmental impacts, and to modify the concepts to ameliorate the associated environmental impacts. Key features of the Metron approach include NAS-wide modeling of impacts (not just around airports), automated adherence to concept-specific flight profiles, and the ability to model proposed concept-specific changes in operational procedures, aircraft types, and levels of noise emission. This approach also provides integrated comparison of different scenarios, quantification and localization of impacts, and analysis of the causes of differences in impact across scenarios.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The Phase I and Phase II commercial potential for embedding NASEIM in VAMS is significant in two areas:
? Commercial firms of all types (airlines, aerospace companies, consultants, etc.) need access to a full-scale simulation environment for gauging the operational utility and feasibility of new airspace and ATM concepts; and
? The same firms will need to gauge the environmental impacts of proposed new concepts in order to show both operational and environmental feasibility. Without the latter, no new concepts will be able to survive the environmental assessment process mandated by the National Environmental Protection Act (NEPA).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Phases I and II embed NASEIM into VAMS and lead to NASA capabilities critical to airspace modernization
? Enables NASA to determine, early in concept development, which concepts may have either adverse or beneficial effects on the environment, particularly with regard to aircraft noise;
? Enables NASA to compare the environmental and operational benefits within a unified simulation environment that uses the same flight and trajectory data;
? Enables NASA to determine which elements of the new airspace concepts are causing the most significant environmental impacts, and, where appropriate, to modify the concepts to ameliorate the associated environmental impacts.
| PROPOSAL NUMBER: | 02- A3.02-9526 (For NASA Use Only - Chron: 022473 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | A Tool for the Evaluation of Proposed TFM Initiatives |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Metron Inc
11911 Freedom Drive
Reston , VA 20190 - 2835
(703 ) 234 - 0753
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jesse Clayton
clayton@metsci.com
131 Elden Street
Herndon , VA 20170 - 2835
(703 ) 787 - 8700
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Metron Aviation, Inc. builds a tool for Traffic Flow Management (TFM) that integrates existing and emerging technologies in the areas of modeling and operations analysis to enable the evaluation of proposed TFM initiatives (Figure 1). The key innovation of this effort is the integration of the Post Operations Evaluation Tool (POET) and the Future ATC Concepts Evaluation Tool (FACET) in order to accomplish new tasks that neither of these tools can do alone. This development leverages the following key features: FACET?s trajectory prediction and modeling capabilities, and POET?s mature database management system and operations analysis tools. By integrating the tools we provide a system that allows Traffic Flow Managers to investigate future TFM initiatives in real-time. These users then exploit the tool?s analysis capabilities to observe and compare the benefits and impacts of several proposed initiatives prior to implementing them operationally.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The integrated tool researched in the Phase I and II efforts has FAA and Airline Operations Control (AOC) commercial potential. The tool is designed primarily for Traffic Flow Managers to allow them to model proposed initiatives prior to implementation. These individuals are already familiar with Metron?s operational POET tool. Leveraging POET analysis techniques and displays, we will be providing a TFM Decision Support Tool that is both familiar and well integrated.
Under the CDM program, AOCs use airline-specific versions of strategic planning tools such as FSM to collaborate on control decisions and allocate resources. As the propsed tool leverages models for equitable delay distributions in proposed initiatives, AOCs would benefit from the ability to provide input to such actions. Furthermore, airlines may be particularly interested in monitoring their relative performance using the equity metrics we have proposed. This tool could be marketed to airlines under the CDM program.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA currently uses FACET for, as the name describes, the evaluation of future ATC concepts. Integrating POET and FACET provides NASA with rich analysis and data visualization capabilities for such evaluations. Furthermore, as the number of data sources used by FACET grow, a robust database management system, such as the one proposed in the effort, will be helpful for organizing and managing it. Though not treated explicitly in the proposal, a significant side effect of the proposed effort is that the integration of FACET with the POET database provides quick access to months of historical ETMS data currently archived by Metron.
| PROPOSAL NUMBER: | 02- A3.02-9528 (For NASA Use Only - Chron: 022471 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Efficient Air Traffic Scenario Generation |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Seagull Technology, Inc.
1700 Dell Avenue
Campbell , CA 95008 - 6902
(408 ) 364 - 8200
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. David B. Signor
dsignor@seagull.com
1700 Dell Avenue
Campbell , CA 95008 - 6902
(408 ) 364 - 8200
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose an innovative scenario generation application that significantly decreases the time and cost to develop complex air traffic scenarios. Our application addresses functionality including the user interface, real time displays, data processing (input/output), and compatibility with other similar applications. Unique innovations are focused on flexible user interface and simulation processing options combined with open-architecture, object-oriented software to enable rapid scenario construction and evaluation. These capabilities are lacking in current scenario generation tools and will provide significant savings to users performing analysis on new airspace operational concepts or modifications to the National Airspace System. In addition, such an application will support a number of other applications including military, firefighting, and aviation security planning, operational simulations, evaluations, and training, The proposed initial research analyzes the requirements for such an application and designs and implements an initial prototype.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial airlines can use this application to support technology investment decision making, new procedure design, operational concept robustness analysis, operations analysis, and training. The FAA may use our product with their Target Generation Facility (TGF) to provide quick-turnaround, human factors analysis of future operations concepts. There is a growing market for aerospace operation simulation worldwide to support; a) communication, navigation, and surveillance, and weather sensing equipment loading and placement analysis, b) UAV and commercial space launch scheduling and design, c) defense force strike planning and procedure development, d) firefighting mission planning and training, and e) aviation security threat analysis.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Within NASA, our scenario generation application can be used to advance research efforts including human performance evaluation in advanced airspace concepts, advanced airspace system concept evaluation and visualization, and the study of revolutionary vehicle concept airspace integration issues. Our application is primarily aimed at providing a scenario generation and analysis tool for investigating many advanced airspace concept issues including conflict detection and resolution, airspace and airport design, en route replanning and traffic flow management decisionmaking, and environmental impact. In general, NASA simulation capabilities exist for these areas but the capability for efficient generation of new scenarios is lacking.
| PROPOSAL NUMBER: | 02- A3.02-9684 (For NASA Use Only - Chron: 022315 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Virtual National Airspace with Human Pilots and Controllers |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
AerospaceComputing, Inc.
465 Fairchild Drive, Ste. 224
Mountain View , CA 94043 - 2251
(650 ) 988 - 0388
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Hiro Kumagai
hkumagai@aerospacecomputing.com
465 Fairchild Drive, Ste. 224
Mountain View , CA 94043 - 2251
(650 ) 988 - 0388
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The behavior of the National Airspace System is the result of the real-time decisions of individual pilots and air traffic controllers. Successes or failures of the system are often due to how they react to the rapidly changing situation and information load that confronts them. A Virtual National Airspace System is proposed that utilizes live pilots and controllers. To maintain their instrument flight skills, pilots routinely use Personal Computer Aviation Training Devices (PCATD?s) that are owned and operated by flight schools, Fixed-Base Operators (FBO?s), and other private parties. Each pilot represents a potential participant in NASA air traffic simulation studies. The proposed Virtual National Airspace System incorporates the state vectors of multiple aircraft and the problems of shared frequency radio communication. Key architectural concerns for the simulation include: state vector and protocol design, simulation server and network operating in real-time with pilots and controllers, and multi-frequency voice communication. A user / pilot database can track pilots for various ratings and, thereby, provide air traffic studies with pilots screened for particular purposes, including maintaining the overall quality of the simulation.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
PCATD?s operated by flight schools and FBO?s can have more realistic simulation since the system simulates surrounding traffic and the shared frequency radio communication with air traffic controllers and other pilots. Large flight simulation facilities other than those used by NASA can benefit by ?purchasing? the miscellaneous traffic and air traffic controller services. The FAA and its contractors can use the system to train air traffic controllers in an environment with rated pilots. The simulation server can be commercially operated in a fashion similar to an Internet Service Provider.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Once the system development is complete, it can provide realistic air traffic to flight simulations and air traffic studies on demand, at any time, at no charge. This makes NASA?s airspace simulations more complete, with miscellaneous surrounding traffic, without increasing the cost of simulation sessions. Investigations into the impact of air traffic management improvements can be done in a setting that incorporates human participants with their changing workloads. The system can also be integrated with more automated approaches so that narrower aspects of air traffic management can be studied.
| PROPOSAL NUMBER: | 02- A3.02-9734 (For NASA Use Only - Chron: 022265 ) |
| SUBTOPIC TITLE: | 21st Century Air-Traffic Management |
| PROPOSAL TITLE: | Integration of Unmanned Air Vehicles with the National Airspace System |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Applied Systems Intelligence, Inc.
11660 Alpharetta Highway
Roswell , GA 30076 - 4916
(770 ) 518 - 4228
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Wendy Elmore
welmore@asinc.com
11660 Alpharetta Highway
Roswell , GA 30076 - 4916
(770 ) 518 - 4228
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This research refines existing associate decision aiding technology and applies it to a new, larger air traffic management (ATM) domain. We have shown in other NASA projects how our associate systems can provide Distributed Air-Ground (DAG) decision aiding to pilots, air traffic controllers, and airline dispatchers within the ATM system of a UAV free NAS. Our existing C2IT software provides decision aiding to UAV operators in combat environments in such a manner that the UAV looks much like a normal aircraft to external observers. We propose to refine our existing UAV decision aiding system so that UAV operators can collaborate effectively with the actors of the ATM system of the NAS. In particular, we shall identify the new ATM message signals and data objects required, synthesize new collaboration diagrams, and refine the finite state machine (FSM) of a UAV associate system. The associate will further the UAV?s similarities to a piloted aircraft in order to accommodate the existing decision support systems of air traffic controllers and pilots.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Future UAV systems will be able to operate on a routine basis with other aircraft in the NAS. This capability will allow them to be used everyday without special clearances or airspace being set aside for their operation. This will make UAV?s commercially viable for missions such as atmospheric radiation measurement, pipeline monitoring, homeland security, search & rescue, intelligence gathering, surveillance, fire fighting, agricultural and environmental monitoring, aerial photography and mapping, law enforcement, and telecommunication relay to name a few.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The results of this project will enable UAVs to smoothly interact with the NAS ATM system when they need to. They will enable the ATM system to maintain a high level of performance even during UAV operations. NASA will be able to take advantage of this capability during their UAV research and testing operations, which will make them far easier to execute than UAV operations today.
| PROPOSAL NUMBER: | 02- A4.01-7626 (For NASA Use Only - Chron: 024373 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | Advanced Crew Escape System Simulation Tool for Future Launch Vehicles |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
CFD Research Corp
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Peter Liever
jls@cfdrc.com
215 Wynn Dr.
Huntsville , AL 35805 - 1944
(256 ) 726 - 4800
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A computational technique that utilizes an innovative tightly coupled combination of CFD, 6-DoF and blast wave simulation methods is proposed for the analysis of crew escape systems for future launch vehicles. An existing high-fidelity simulation program, well validated for military crew escape systems, will be leveraged to meet the challenges of simulating escape system operation for launch abort across the flight envelope, from pre-launch to the hypersonic regime.
In Phase I, computationally efficient blast wave effect models will be integrated to simulate launch vehicle propellant explosion effects. Analytical models and available explosion test data will be combined into reduced mechanism blast wave models simulating the explosion event. The value of the improved coupled simulation capability will be demonstrated through sample computations, with and without blast wave effects, for individual and simultaneous crew member ejection, and for the escape separation of a crew vehicle.
The newly developed physical and dynamic simulation models will be further refined and validated in Phase II. In particular, the speed and accuracy of staging and escape simulations using the new blast wave models will be improved. Recent CFDRC experience in complex urban blast wave flow field modeling will be leveraged to implement a solution adaptive overset Chimera grid approach.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Additional application areas include analysis of store release and missile launch from future hypersonic transcontinental military aircraft and crew escape systems for such vehicles, and multi-stage kinetic projectile boost and staging. Other potential new markets for the coupled CFD/6-DoF/blast wave modeling include analysis of missile proximity warhead effectiveness, explosive warhead application against chemical/biological agents, and armored vehicle protection designed to deflect incoming warheads through the initiation of blast waves in the warhead path.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
The proposed simulation technology will find direct and immediate applications with NASA and contractors in the development of NASA's Second and Third Generation Reusable Launch Vehicles. The software provides accurate and cost effective escape system simulation technology not available to NASA today. It provides significant capability advances in crucial areas of launch vehicle development: 1) definition and screening of escape strategies in the concept phase, 2) verification of escape system functionality across the flight envelope, and 3) blast wave impact on escape system functionality and safety margin. It offers risk mitigation of crew safety and survivability not available from ground or flight tests. The technology is cross-cutting for all potential architectures, and for all crew escape systems ranging from individual ejection seats to crew vehicles.
| PROPOSAL NUMBER: | 02- A4.01-8696 (For NASA Use Only - Chron: 023303 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | MicroSAFE (Stress Analysis and Forecasted Endurance) |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Invocon, Inc.
19221 I-45 South, Suite 530
Conroe , TX 77385 - 8703
(281 ) 292 - 9903
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Joe Hermann
jhermann@invocon.com
19221 I-45 South, Suite 530
Conroe , TX 77385 - 8703
(281 ) 292 - 9903
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The NASA SLI is to determine design approaches to a new space launch vehicle that can reduce the costs and minimize risks. Significant amounts of the cost associated with operation of the current Shuttle involves manual inspections. The challenge is to determine a means of more cost effective inspections. Proposed herein is a means for reducing the need for manual inspections while improving the quality of ?flight readiness status? information. The proposed approach also insures that this reduction in operations costs could be achieved for a minimum cost. A miniature device is proposed that can measure and compile the exact stress life in mechanical parts on a constant basis and report this information to a gathering facility via wireless radio communications. The device would be so small that one or more of them could be included on every critical life limited part designed for a particular application. The inclusion of the device on the critical part would make the part a ?smart part? that would continually measure its own health relative to stress life and would report that information when commanded. Thus maintenance personnel would only need to watch for data processing alarms to determine the replacement time.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Commercial air service organizations all deal with life limited parts. Parts must be replaced within a specific number of operational hours. The number of hours are estimates by the builder and the controlling government safety authority. A technique that could total the exact number of stress cycles and their magnitude could allow life limited parts to be changed out only when service life has been reached. Example: PA 38 Piper aircraft. The wings have a service life of 11,000 hours. This assumes that the plane was used to the limits of the Utility Category (more stressful than Normal Category). These aircraft are being scrapped every year due to this limitation in spite of the fact that many have not even come close to their service life. Commercial operations can save money precise measurements and lives could be saved as exemplified by the recent Slurry Tanker crashes if total service life was easily available.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
This device is applicable to both retrofit and new system NASA applications. Specifically, IVC has raw data collection hardware flying on the Shuttle for purposes of measuring the exact strain loads imparted on the engine steering arms. IVC has pushed size and cost reduction of this device to the limits of conventional components. In this form, the device has a large potential market and can contribute to the optimization of replacement schedules for many ?life limited? parts. This effort has resulted in a device that measures 2.5 cm by 2.5 cm by 1.5 cm. The proposed device (measuring 5 mm by 5 mm by 2 mm ) would bond to the part or structure. Properly packaged, the device could be imbedded into composite construction to detect changes in the statistical stress life that would signal structural failure.
| PROPOSAL NUMBER: | 02- A4.01-8700 (For NASA Use Only - Chron: 023299 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | A New Methodology for Calculating Launch Vehicle Ascent Loads |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Dynamic Concepts Inc
P.O. Box 97
Madison , AL 35758 - 0097
(256 ) 461 - 8006
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Dr. Thomas G. Howsman
thowsman@dynamic-concepts.com
P.O. Box 97
Madison , AL 35758 - 0097
(256 ) 461 - 8006
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Determining an effective structural design of a launch vehicle is critical to both mission success and crew safety. In order to evaluate the adequacy of a launch vehicle?s structural design, the ascent loads experienced by the vehicle must be determined. Computation of the ascent loads is a complex, multi-disciplined undertaking that involves an assessment of both natural and induced environments. Currently, ascent loads are calculated primarily using a somewhat restrictive constant Mach number squatcheloid approach. A method to compute the ascent loads of a launch vehicle through a direct coupling of the six-degree-of-freedom trajectory simulation with a time correlated flexible body simulation of the structure is proposed. Load dispersions due to the statistical uncertainties associated with both environmental effects (e.g., winds) as well as vehicle uncertainties (e.g., thrust misalignment) may be assessed directly from a set of Monte Carlo runs of the synchronized trajectory and loads simulations. The Phase I research is directed at developing the necessary algorithms and providing a proof-of-concept simulation. During Phase II, a complete modular computational framework will be developed that will integrate the 6DOF trajectory tools with the loads prediction software, allowing for a more accurate and unified loads analysis of the vehicle.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The most obvious non-NASA application for this technology is the commercial satellite launch industry. Proposed commercial reusable launch vehicles have the potential to dramatically lower payload-to-orbit costs. This proposed analytical process could enhance such vehicles by producing more optimal structural designs and reducing the potential for launch failure. The proposed technology could also be adapted to augment existing simulations of various mobile military assets such as a planes, tanks, or guided missiles, thus increasing the fidelity of the computed loads for these systems as well.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
If the proposed computational approach for ascent loads is fully developed, NASA will gain an important tool for the accurate prediction of launch vehicle loads. Clearly, NASA?s 2nd Generation RLV design must be structurally efficient in order to meet program goals. This will require accurate knowledge of vehicle loads in order to eliminate excess conservatism without jeopardizing safety. Similarly, if the Shuttle is to continue flying for many years into the future, more precise knowledge of the dynamic loads which occur during ascent may be required for future fracture and reliability analyses of the vehicle.
| PROPOSAL NUMBER: | 02- A4.01-8734 (For NASA Use Only - Chron: 023265 ) |
| SUBTOPIC TITLE: | Space Transportation Architecture Definition |
| PROPOSAL TITLE: | Dynamic Transfer Function Measurements for Cavitating Pumps |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Concepts ETI, Inc.
217 Billings Farm Road
White River Jct , VT 05001 - 9486
(802 ) 296 - 2321
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Daniel O. Baun
dob@conceptsnrec.com
217 Billings Farm Road
White River Jct , VT 05001 - 9486
(802 ) 296 - 2321
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
There are no analytical tools or experimental facilities in the world today that can quantify the dynamic transfer function for a cavitating inducer. The goal of this research is to fill this void. An innovative experimental technique is proposed where by a cavitating inducer's dynamic transfer function is quantified by mapping the flow and pressure fluctuations at the inducer exit as a function of harmonic perturbations at the inlet. A cavitating inducer can be a source of instability in a rocket engine. Due to cavitation dynamics, inlet flow perturbations maybe amplified by the inducer resulting in very large flow and pressure fluctuations in the fuel system. The resulting dynamic couplings can lead to vehicle instability (POGO) as well as generate intense dynamic loadings on the turbopump. The feasibility of implementing the technique on the Concepts NREC water flow test rig will be demonstrated in Phase I of the project. Implementation of the technique and inducer transfer function identification will occur in Phase II. The proposed dynamic transfer function characterization methodology is applicable to any high energy density turbomachine subject to impeller induced flow instabilities, such as boiler feed pumps or re-injection pumps and compressors.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
High energy density turbomachines such as gas re-injection pumps and compressors, and high-energy industrial pumps, are a source of instability. Accurate dynamic characterizations of these machines are required to ensure safe and reliable operation of the systems into which they are installed. In addition to understanding the dynamic attributes of these machines under cavitation or stalled conditions, the dynamic transfer function under normal operating conditions are also required. The methodology proposed to measure the dynamic transfer function of a cavitating inducer is transferable. The proposer is well-positioned to commercialize the technology to both aerospace and industrial customers.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
As mission requirements lead to higher power density turbopumps with lower specific weights and higher suction specific speed requirements the potential for flow-induced dynamic instabilities, both at the turbopump level and at the system level, increase. Rocket vehicle dynamic models require an accurate dynamic characterization for the inducer. The proposed experimentally measured dynamic transfer functions will provide accurate and reliable pump dynamic attributes which are necessary to assess the probability of destructive flow instabilities, such as cavitation surge and rotating cavitation, and their effect on engine component or integrated vehicle system instability.
| PROPOSAL NUMBER: | 02- A4.02-7464 (For NASA Use Only - Chron: 024535 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Aluminum/Alumina Based Metal Matrix Composites from Nanometer Powder |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Technanogy, LLC
2146 Michelson Dr., Suite B
Irvine , CA 92612 - 1304
(949 ) 261 - 1420
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Debbie Shelton
dshelton@technanogy.net
2146 Michelson Dr., Suite B
Irvine , CA 92612 - 1304
(949 ) 261 - 1420
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Technanogy Air and Space and Rockwell Scientific propose a novel approach to manufacturing a low density high-performance aluminum based metal matrix composite (MMC) by consolidating nano-aluminum powder. Depending on the application, Technanogy?s nano-aluminum powder can be tailor made in terms of size and oxide shell thickness. For the current project, powders having ceramic weight contents of 15, 25, 35, 45, 55 and 65 percent will be provided to Rockwell Scientific for consolidation. During the consolidation process Rockwell will determine the ideal processing parameters for each ceramic concentration so that the process can be further developed to produce large quantities of bulk nanocrystalline Al/Al2O3 metal matrix composite material. It is expected that the consolidated Al/Al2O3 composite will have nearly theoretical density and a submicron- sized distribution of ceramic and metallic grains, and that this ultra-fine microstructure will produce a high specific strength and specific stiffness at all temperatures and excellent compatibility in hydrogen environments. The specific goal is to produce aluminum based MMCs with specific strength superior to 414MPa at 260?C. Improvement in the high temperature properties of aluminum MMCs will allow their use in many applications where they have not been used previously in NASA or commercial applications.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Technanogy Air & Space and Rockwell Scientific are collaborating to produce Al/Al2O3 composite materials by combining Rockwell?s consolidation expertise with Technanogy?s nanoparticulate composite. The projected improvements in high temperature strength and lower CTE would impact the following NASA applications: ducting and duct flanges for carrying warm gases, wave guides, struts for airplanes or satellite structures, airplane fins, and thermal management supports.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Technanogy Air & Space and Rockwell Scientific are collaborating to produce Al/Al2O3 composite materials by combining Rockwell?s consolidation expertise with Technanogy?s nanoparticulate composite. The projected improvements in high temperature strength and lower CTE would impact the following commercial applications: connecting rods in combustion engines, cylinder liners, engine blocks, driveshafts, alloy wheels, baseball bats, golf clubs, and bicycle frames.
| PROPOSAL NUMBER: | 02- A4.02-7982 (For NASA Use Only - Chron: 024017 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Production of Single-Walled Carbon Nanotubes by Catalytic Disproportionation ... |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Southwest Nanotechnologies, Inc.
2516 Warwick Drive
Oklahoma City , OK 73116 - 4324
(405 ) 325 - 4940
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Leandro Balzano
lbalzano@ou.edu
2516 Warwick Drive
Oklahoma City , OK 73116 - 4324
(405 ) 206 - 5979
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The unmatched properties of single-wall nanotubes make them a unique product that will represent a billion-dollar market in applications that range from space to consumer products. At the University of Oklahoma, the catalytic production of SWNT has been optimized in a novel process (CoMoCAT) based on a specific catalyst formulation that yields SWNT with high selectivity. A fluidized bed reactor is particularly suitable to achieve optimal synthesis conditions and make the process continuous. A good-quality SWNT product has been consistently obtained. The present proposal will focus on the gradual improvement of the current CoMoCAT technology to make it able to operate in a continuous, larger-scale mode that will result in low SWNT costs. The anticipated results of the phase I include the development and testing of the continuous, large-scale reactor and the scale up of the purification process. Phase II is visualized as a direct application of the optimized process at an even larger scale that will incorporate the participation of strategic partners for the development of SWNT-based materials. The carbon nanotube is 100x stronger than steel, yet 1/5th the weight. SouthWest NanoTechnologies will commercialize nanotubes for their structural properties, meeting a direct need for NASA, and providing the next generation of lightweight composites for industries worldwide.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
A4.02 - Space Structures, Materials, & Mfg.
The estimated market value of carbon nanotubes is $400MM USD in FY2004. SouthWest NanoTechnologies, Inc. will focus on the near-term structural ?killer applications? in Single-Walled Carbon Nanotubes. Compiled from a variety of sources, these include composite materials, electromagnetic shielding material, and thermal materials. The aforementioned products will create the demand of the future, and result in demonstrable near-term revenue. This focus is decidedly unique, as the company has a formal relationship with a Fortune 100 company, and is currently negotiating a joint development agreement.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
With all due respect to the ongoing Contour program, we tread cautiously along what appears to be a crucial need for high-end structural technologies. As of 8/20/02, the mission is still active, though early reports indicate the spacecraft may have broken in two. NASA spokesman Don Savage was quoted in a CNN story, ?The failures hurt but they do happen.? Thus, an approval of this proposal demonstrate tangible and decisive steps toward correcting the problem at its source. Based on NASA's specific needs, this material could be formed into ultra lightweight discontinuous fiber composites for several targeted aerospace applications.
| PROPOSAL NUMBER: | 02- A4.02-8771 (For NASA Use Only - Chron: 023228 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Ultrasonic Tape Laminated Cryogenic Tank Structures Processed Outside Autoclave |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Foster-Miller Inc
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 622 - 5502
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
John Player
jplayer@foster-miller.com
350 Second Ave
Waltham , MA 02154 - 1196
(781 ) 684 - 4242
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Recent designs for large aerospace structures especially cryotank structures for the second and third Generation Reusable Launch Vehicle (RLV) are driving the aerospace community to develop out-of-autoclave composite manufacturing processes to save enormous autoclave capital equipment costs. In this proposed Phase I effort, Foster-Miller will demonstrate that autoclave equivalent mechanical properties can be obtained using its Ultrasonic Tape Lamination technology coupled with its novel out-of-autoclave processing approach, solid state curing. Preliminary data from work with Northrop Grumman on the second generation RLV cryotank manufacturing program already shows that this process is feasible by achieving 90 percent of the autoclave processed properties.
Foster-Miller will utilize in house analytical equipment to perform the resin characterization essential for refining the UTL/solid state curing approach. Critical mechanical property testing will be performed to demonstrate autoclave property equity in the Phase I. Northrop Grumman will supply Foster-Miller with key logistical and tooling information to assess the cost saving potential of the refined UTL/solid state cure approach. The Air Force has shown significant interest in this technology and will be kept informed as UTL/solid state curing is developed in Phases I and II. (P-020642)
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
Foster-Miller?s Ultrasonic Tape Lamination (UTL) technology coupled with its novel out-of-autoclave processing approach, solid state curing has the potential to dramatically change the cost structure for fabricating a wide range of commercial aircraft composite components. Many of the large nacelle and flight control structures on Boeing and Airbus aircraft require multiple autoclave cycles for their manufacture, incurring substantial costs in cycle time and associated labor. Foster-Miller?s UTL/solid state bag-less cure would eliminate the need for the autoclave and perhaps more importantly, would eliminate the labor costs associated with vacuum bagging, usually performed several times during a component?s fabrication. UTL/solid state bag-less curing can also be applied to the manufacture of a wide range of other large composite structures that need high quality at low cost such as thick tubulars for offshore oil drilling, military fighter structures (JSF, F-18E/F, and V22) and military space plane structures (Air Force SOV cryotanks).
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Foster-Miller?s UTL/solid state bag-less cure can be utilized during the manufacture of many of NASA?s large aerospace structures. The most prominent are the cryogenic fuel tanks for the next generations of reusable launch vehicle. Although the cryotanks provide the largest immediate cost savings primarily due to the elimination of autoclave capital investment, the opportunity to save manufacturing costs with this novel out-of-autoclave processing approach exists for other large space vehicle structures such as RLV wing skins, payload bay and landing gear doors. Other launch vehicles such as Delta IV rocket and its composite payload fairings also provide an excellent cost saving opportunity for the UTL/solid state bag-less technology.
| PROPOSAL NUMBER: | 02- A4.02-8845 (For NASA Use Only - Chron: 023154 ) |
| SUBTOPIC TITLE: | Space Structures, Materials, and Manufacturing |
| PROPOSAL TITLE: | Innovative Tungsten Alloys for Advanced Propulsion Systems |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Plasma Processes, Inc.
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Robert Hickman
robert@plasmapros.com
4914 Moores Mill Rd
Huntsville , AL 35811 - 1558
(256 ) 851 - 7653
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Non-conventional technologies are needed to revolutionize space propulsion. Development of materials with improved properties is essential to increase performance and reduce cost. Advancements are needed for components in high powered electrical, beamed energy, and nuclear propulsion systems. Innovative Vacuum Plasma Spray (VPS) processes for fabricating net shape, tungsten-rhenium-hafnium carbide alloy components are proposed. Tungsten is being used for its high melting temperature and chemical stability. However, conventional tungsten materials have to be forged to get adequate properties. Forging tungsten into complex shapes is difficult and has limited its application. Tungsten alloys yield improved properties as compared to conventional unalloyed tungsten. It is well documented that small additions of rhenium improve the ductility of tungsten without significantly decreasing the melting point. Also, dispersion hardening by additions of HfC increases the high temperature strength by pinning grain boundaries. In Phase I, W-Re-HfC powders and process parameters will be developed to fabricate samples for characterization and hoop tensile testing. After optimization, nozzles will be fabricated and hot fire tested at ATK-Thiokol. Development of these materials will allow the production of components with unique properties and reduce the size, weight, and cost of propulsion systems.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The results of the Phase I effort will clearly demonstrate the ability to fabricate improved tungsten alloy components. Development of these advanced materials will produce robust components with unique properties and reduce the size, weight, and cost. Potential clients for these components are NASA, DOD, Thiokol, and Aerojet. Letters from Thiokol and Aerojet for Plasma Processes ongoing R&D efforts are attached to this proposal. PPI will develop and transfer the SBIR technology to other commercial applications such as: Ballistic and tactical missiles, gun barrel liners, Arc-jet thrusters, Heat exchangers, Welding electrodes, Plasma facing components for nuclear reactors, gas turbines, automobile engines, incinerators, thermal control coatings, oxidation protective coatings, coatings for composite parts and structures, thermal barrier coatings, structural jackets on tubular combustors and nozzles, crucibles, tubes, valves, and storage vessels.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
NASA applications that net shape tungsten alloy components can be used for are high powered electrical, beamed energy, and nuclear propulsion systems. Tungsten alloys can also be used for microgravity crucibles, heat pipes, fuel cells, and components for solar themal propulsion, liquid/solid rocket motors, and other high temperature applications.
| PROPOSAL NUMBER: | 02- A5.01-7863 (For NASA Use Only - Chron: 024136 ) |
| SUBTOPIC TITLE: | Lightweight Engine Components |
| PROPOSAL TITLE: | Multilayer Fiber Interfaces for Improved Environmental Resistance and Slip |
SMALL BUSINESS CONCERN
(Firm Name, Mail Address, City/State/Zip, Phone)
Ultramet
12173 Montague St
Pacoima , CA 91331 - 2210
(818 ) 899 - 0236
PRINCIPAL INVESTIGATOR/PROJECT MANAGER
(Name, E-mail, Mail Address, City/State/Zip, Phone)
Jason R. Babcock, Ph.D.
jason.babcock@ultramet.com
12173 Montague St
Pacoima , CA 91331 - 2210
(818 ) 899 - 0236
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Application of ceramic matrix composites (CMC) reinforced with carbon fibers can potentially enhance the efficiency and performance, reduce the weight, improve the durability, and lower the cost of rocket engine combustion devices and turbomachinery components used in high temperature, high-stress environments. Meeting these objectives requires improvements in fiber-reinforced CMC materials and fabrication processes, particularly improved fiber/matrix interfaces, interface deposition processes, and oxidation protection. Although carbon fibers are most desirable as CMC reinforcements, their low oxidation resistance has prevented their use in high temperature oxidizing environments. In previous work, Ultramet developed a unique and innovative process, ultraviolet-enhanced chemical vapor deposition (UVCVD), which allows deposition of dense, strain-tolerant oxides at room temperature, thus avoiding heat-induced material degradation and providing excellent material performance, including enhanced oxidation protection. However, identifying a single phase that best performs the two key functions of the interface coating, oxidation protection and interface slip, simultaneously has thus far proven elusive. In this project, the UVCVD process will be developed specifically for deposition of multilayered interface coatings in which separate components will perform these two functions, resulting in optimum composite performance.
POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 150 WORDS)
The composite materials to be developed in this project using innovative interfaces and novel UVCVD processing will have broad commercial applicability to a range of products, including fuel-rich turbomachinery components, aircraft engine components, recuperators, ducts, and other hot gas path components, process industry components requiring high temperature capability and corrosive environment resistance (e.g. hot gas and liquid handling equipment), furnace structures, and high temperature filter elements.
POTENTIAL NASA APPLICATIONS (LIMIT 150 WORDS)
Ceramic matrix composite materials are projected to significantly increase safety and reduce costs simultaneously, while decreasing weight for space transportation propulsion. Innovative material and process technology advancements are required to enable long life, reliable, and environmentally durable materials. Specific