| PROPOSAL NUMBER: | A1.01-8284 (For NASA Use Only - Chron: 013715 ) |
| PHASE-I CONTRACT: | NAS1-02027 |
| PROPOSAL TITLE: | Intent Inference Algorithm |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this Phase II SBIR effort, Metron designs and develops an intent inference algorithm, an algorithm that infers the intent of the pilot of an aircraft that is being tracked by a surveillance system. Data describing the environment around the aircraft, for instance, the location of nearby aircraft, weather, Navaids, alternate airports, turbulence, and operational data are used to determine plausible routes for travel. Operational data and domain knowledge from pilot and air traffic controller interviews are used to identify how pilots react to these elements in the National Airspace System (NAS). The algorithm imbeds operational data and domain knowledge into human decision-making computer models; these models are then used to predict the future motion of the vehicle and to identify intent. The outputs of the algorithm are an inferred intent, a level of confidence in the intent, and a continuous predicted path.
POTENTIAL COMMERCIAL APPLICATIONS
We are designing our algorithm to be used in real-time applications of systems that track aircraft
en route in the NAS and for future cockpit displays that require the intent of a nearby aircraft to
be inferred. Such a functionality for the cockpit is a required part of a Cockpit Display of Traffic Information,
or CDTI.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Jimmy Krozel, Ph.D.
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA 20170 - 4835
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA 20170 - 4835
| PROPOSAL NUMBER: | A1.02-8103 (For NASA Use Only - Chron: 013896 ) |
| PHASE-I CONTRACT: | NAS3-02001 |
| PROPOSAL TITLE: | Affordable Composite Fan Containment Case with Integral Toughening Elements |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed program will develop and demonstrate an affordable manufacturing approach to fabricate the latest generation of damage tolerant composite fan case designs. These designs embed a grid of stiffener ribs within the composite laminate to limit damage propagation that is initiated during the fan blade containment event. This grid blunts the crack growth and restricts damage within a "safe zone" that permits structural viability of the case after the blade is contained. The proposed work package will demonstrate that advanced braiding concepts can be used to fabricate these composite-toughening elements in a cost-effective manner. This economically viable fabrication method will allow widespread application of the toughened design concept and enable weight efficient, safe containment system designs for high bypass turbofan engines.
POTENTIAL COMMERCIAL APPLICATIONS
This technology can be applied to the design of all jet engine fan containment cases.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Mike Braley
A&P Technology
4595 East Tech Drive
Cincinnati , OH 45245 - 1055
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
A&P Technology
4595 East Tech Drive
Cincinnati , OH 45245 - 1055
| PROPOSAL NUMBER: | A1.02-8674 (For NASA Use Only - Chron: 013325 ) |
| PHASE-I CONTRACT: | NAS3-02002 |
| PROPOSAL TITLE: | Sensitive and Specific Detection of Early Warning Fire Signatures |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An airborne fire is one of the most dreaded emergencies, as all pilots will acknowledge. Isolated at high altitudes, a fire-induced loss of systems can disable the aircraft beyond control. The space shuttles and the International Space Station face an even worse predicament. While an aircraft can land on a short notice, spacecraft are totally vulnerable. Existing fire sensors detect smoke or flame, indicating that the fire is in a relatively advanced stage, but these systems produce false alarms 199 times out of 200. Intelligent Optical Systems (IOS) proposes to develop a fire onset detection system (FODS) that will: (a) detect fire at a very early stage, without false alarm, by performing trend analysis on key chemical markers and temperature, and (b) provide a continuous status update for intelligent decision making by the crew. In Phase I, IOS established the feasibility of FODS by detecting 50 ppm of carbon monoxide. In Phase II, the project team will develop and test a compact FODS prototype. This prototype system will have the capability to react to several fire markers simultaneously with a high level of reliability.
POTENTIAL COMMERCIAL APPLICATIONS
IOS's early-warning fire detection system will improve the aircraft industry's ability to detect in-flight fires. In 1997, the Federal Aviation Administration estimated that the incorporation of fire detectors in Class D cargo holds would result in a savings to the airlines of $458 million in incident and accident reductions over the lifetime of the aircraft that existed at that time. The dramatic reduction in false alarm, and increase in the sensitivity that IOS?s system offers will nearly double these savings. The system will also have applications in manufacturing facilities, buildings, and on ships.
Other possible applications include: a) environmental gas sensing; b) flammable gas detection in the fire hazard areas; and c) evaluation of gas mixtures in the chemical and pharmaceutical industry.
Another potential application includes chemical and biological warfare agent detection by remotely tracing vapors of the explosives and chemicals. The market for chemical and biological warfare agent detectors could reach nearly $400 million in 2002, rising to $490 million by 2007.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Vladimir Rubtsov
Intelligent Optical Systems, Inc.
2520 W. 237th Street
Torrance , CA 90505 - 5217
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Intelligent Optical Systems, Inc.
2520 W. 237th Street
Torrance , CA 90505 - 5217
| PROPOSAL NUMBER: | A1.02-9278 (For NASA Use Only - Chron: 012721 ) |
| PHASE-I CONTRACT: | NAS1-02018 |
| PROPOSAL TITLE: | Improved Crashworthy Aircraft Seat Design |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
NASA is concerned with the prevention of hazardous and accident conditions in transport aircraft and is interested in the mitigation of passenger injuries in accident conditions. Aircraft seats can significantly contribute to the safety of the passengers by restraining them and providing protection in the event of crashes.
An innovative transport aircraft passenger seat concept for superior occupant protection, meeting all structural requirements used in typical seat designs was developed in the Phase I program. This was accomplished with the use of new energy-absorbing structural members and precise control of seat deformation characteristics. Foster-Miller developed an innovative design using the integrated advanced dynamic finite element modeling technique for the seat, occupants, restraints and energy absorbing elements. Results from certification tests on an existing seat design were used to validate the analytical model.
The Phase II program will focus on the optimization and detailed design of this new aircraft seat, including the injury-reduction features. Testing and verification of designs based on the new approach will be conducted. Manufacturing issues and costs will be also addressed. The design will conform to the SAE certification standards for aircraft passenger seats. (P-020417)
POTENTIAL COMMERCIAL APPLICATIONS
This project is directly relevant in the design and manufacturing of high performance aircraft seats. This technology can be adapted in other fields such as automobiles and locomotives to protect passengers and train crew.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Kash Kasturi
Foster-Miller, Inc.
350 Second Ave.
Waltham , MA 02154 - 1196
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Foster-Miller, Inc.
350 Second Ave.
Waltham , MA 02154 - 1196
| PROPOSAL NUMBER: | A1.03-9314 (For NASA Use Only - Chron: 012685 ) |
| PHASE-I CONTRACT: | NAS4-02003 |
| PROPOSAL TITLE: | Hybrid Model Fusion for Gas Turbine Engine Diagnostics and Prognostics |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In Phase I IAC, teamed with Pratt & Whitney and Luppold & Associates, developed and demonstrated a hybrid modeling approach to enhance diagnostics and prognostics performance on F-117 engines. The hybrid model fuses a physics-based model developed by Pratt & Whitney called STORM with an empirical model that uses neural networks to monitor and quantify unmodeled and/or mismodeled engine phenomena that corrupt STORM?s diagnostic outputs. The resulting hybrid model is called the enhanced STORM or eSTORM. In Phase I eSTORM was demonstrated to work extremely well for limited conditions when processing simulated engine data.
In Phase II IAC proposes to develop a standalone system for real time implementation of a full F-117 engine eSTORM. The system will cover the full C-17 flight envelope. The system will include interfaces to accept data from the C-17 aircraft bus and will be capable of on-wing operation. The system will be demonstrated using real F-117 inputs running in a test bench environment. Though developed explicitly for an F-117 application, the hybrid modeling concept developed on this Phase II is generic and can be used for eSTORM development on all Pratt & Whitney military and commercial engines.
POTENTIAL COMMERCIAL APPLICATIONS
IAC worked closely with Pratt & Whitney in development of the initial eSTORM system in Phase I. Pratt & Whitney will support IAC in Phase II to provide engine expertise and proprietary engine models. Though developed explicitly for an F-117 application, the system to be developed on Phase II is generic and can be used for eSTORM development on all Pratt & Whitney military and commercial engines. If Phase II is successful Pratt & Whitney would transition the technologies developed to all their product lines
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Tom Brotherton
Intelligent Automation Corporation
13029 Danielson Street, Suite 200
Poway , CA 92064 - 8811
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Intelligent Automation Corporation
13029 Danielson Street, Suite 200
Poway , CA 92064 - 8811
| PROPOSAL NUMBER: | A1.03-9855 (For NASA Use Only - Chron: 012144 ) |
| PHASE-I CONTRACT: | NAS4-02005 |
| PROPOSAL TITLE: | Object-Oriented, Network-Based, Health Management System |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The safety and efficiency of transportation will be enhanced by revolutionary systems that provide on-line health management of vehicle systems. Creare's Online Health Management (OHM) Toolkit facilitates the assembly of a such a system, through the creation of a distributed network-based data processing structure, which is completely described by semantic metadata. This approach enables the system to intelligently interpret diagnostic and prognostic information and to dynamically generate online reports for a wide range of users.
The object-oriented paradigm employed by Creare's software, provides numerous advantages over current custom written systems, including reduced development time and cost, reduced learning curves, reduced bandwidth requirements through distributed processing, and increased data availability through data buffering and web-based report delivery.
In Phase I we demonstrated the feasibility of this approach by developing and testing prototype software. We accomplished this by building on Creare's previously developed, patented, and award-winning RBNB? middleware software. We augmented this enabling technology with an easy-to-use graphical user interface (GUI) for configuring online health-monitoring systems.
During Phase II of this project, we will complete development of the software to produce a commercial-grade package. We will then test the OHM tools by creating health-management systems for a number of demonstration applications.
POTENTIAL COMMERCIAL APPLICATIONS
Health management systems can enhance the safety and cost effectiveness of a broad range of vehicle, machinery, and processing systems. As a result, our software tools, which enable the creation of online-health management systems, have a broad range of potential applications, in the military, transport, medical, and industrial fields. However, the revolutionary potential of our application is as a next-generation web tool that moves beyond the simple formatting capability of HTML tools, to interpreting and processing capabilities enabled by semantic data descriptions. We envisage explosive growth of this new technology once the the required data management infrastructure is widely implemented and the use of semantic metadata becomes standard. Our software toolkit addresses both of these requirements, through our buffered data management middleware, and our integrated metadata schema.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Anthony Dietz
Creare Inc.
Etna Rd., P.O. Box 71
Hanover , NH 03755 - 0071
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Creare Inc.
Etna Rd., P.O. Box 71
Hanover , NH 03755 - 0071
| PROPOSAL NUMBER: | A1.04-8757 (For NASA Use Only - Chron: 013242 ) |
| PHASE-I CONTRACT: | NAS3-02004 |
| PROPOSAL TITLE: | A Simple, Small, Low Power Instrument to Measure Aircraft Icing Severity |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Aircraft icing severity depends on two key cloud parameters, liquid water content and droplet size. Proposed is a simple instrument using multiple hot wire elements to measure cloud droplet size (median volume diameter) and liquid water content.
The unit utilizes three hot wire sensor elements each of a different geometry, all exposed to the same airflow. By virtue of their different sizes/shapes, the elements have different measurment efficiencies with respect to droplet diameter.
Liquid water content is determined by the total amount of water measured by all three elements. Droplet median volume diameter is determined by the response differences between the three elements. The range of droplet measurement includes super large droplets SLD).
The proposed instrument has no moving parts, no optics and emits no electromagnetic radiation. It is a first principles device capable of complete calibration. Its response time is under one second.
Total frontal area of the instrument is less than four square inches. Less than 500 watts of power are required for operation in continuous icing conditions. The operational airspeed range is compatible with operational jet and turboprop transport aircraft.
Applications include icing research and operational cockpit warning for icing and SLD conditions.
POTENTIAL COMMERCIAL APPLICATIONS
1. GA and Commercial Cockpit Warning Device for Icing Severity, including warning of SLD conditions
2. Frequency of Occurance Survey instrument to conduct gather data from the GA and Commercial fleet in regards to icing certification requirements
3. Transfer standard for intercomparison of Icing Test Facilities
4. Stand alone certification instrument for FAA aircract certification projects.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Lyle Lilie
Science Engineering Associates
114 C Mansfield Hollow Road, Box 605
Mansfield Center , CT 06250 - 0605
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Science Engineering Associates
114 C Mansfield Hollow Road, Box 605
Mansfield Center , CT 06250 - 0605
| PROPOSAL NUMBER: | A1.05-8767 (For NASA Use Only - Chron: 013232 ) |
| PHASE-I CONTRACT: | NAS1-02022 |
| PROPOSAL TITLE: | Shaped Field Giant Magnetoresistive Sensor Arrays for Materials Testing |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Shaped field Giant Magnetoresistive Sensor Arrays offer substantially increased depth of sensitivity and potential to provide 3-dimensional absolute property imaging for conducting and magnetic media. The Phase I demonstrated the capability of Meandering Winding Magnetometer (MWM) drive winding constructs with GMR sensing elements to (1) detect and image 3% material loss in a 0.25 inch thick aluminum plate, (2) detect corrosion damage in a military aircraft component, (3) use a forward model of the sensor interactions with layered media to calibrate in ?air,? without standards, and accurately measure absolute electrical conductivity and layer thickness, (4) measure and monitor temperature variations for an aluminum plate through another 0.25 inch aluminum plate with an additional 0.5 inch air gap between plates, (5) independently measure variations in stress (i.e., through its relationship with magnetic permeability) on a steel plate through a 0.25 inch aluminum plate and variations in an approximately 0.12 inch air gap between plates, and to (6) operate a three channel GMR-MWM sensor array with JENTEK?s commercial impedance instrumentation. These demonstrations completely satisfied the Phase I objectives. The proposed Phase II effort will develop conformable MWM-Arrays with GMR sensing elements and distributed winding designs for imaging hidden damage and geometric features.
POTENTIAL COMMERCIAL APPLICATIONS
There are substantial commercial applications for this capability including replacing X-Ray and UT for inspection of metal structures less than 0.5 inches in thickness for corrosion, fatigue and geometric feature imaging stress measurement for ferrous alloys, and weld inspection (e.g., the friction stir welds on the space shuttle tanks, gun barrel inspection, and even buried unexploded ordnance and landmine detection). The proposed Phase II effort will extend the current capability and substantially broaden JENTEK?s addressable markets. JENTEK plans to provide matching funds for Phase II and III. This match will focus on development of key components for planned commercial versions of GMR-MWM-Array products.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Neil Goldfine
JENTEK Sensors, Inc.
110-1 Clematis Avenue
Waltham , MA 02453 - 7013
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
JENTEK Sensors, Inc.
110-1 Clematis Avenue
Waltham , MA 02453 - 7013
| PROPOSAL NUMBER: | A1.05-9239 (For NASA Use Only - Chron: 012760 ) |
| PHASE-I CONTRACT: | NAS1-02024 |
| PROPOSAL TITLE: | Distributed Optical Fiber Sensor Demodulation System |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This project?s goal is to produce a flight qualifiable tunable laser system specifically for use in optical frequency domain reflectometry (OFDR) based distributed fiber Bragg grating sensing applications. This work represent an enabling technology for NASA's requirement for distributed optical fiber sensing for health monitoring, aviation safety, and aircraft morphing programs. The work is based on the Phase I feasibility studies which generated two approaches for producing OFDR targeted laser systems. These systems have the unique combination of rapid tuning and immunity to mode hops. The proposed designs have reduced alignment tolerances and built in wavelength tracking. These features provide a level of hardening to environmental influences that will make flight qualification of the systems possible as well as cost effective. An integral part to both approaches is the incorporation of a high speed, high resolution, tracking wavemeter. This feature allows for the use of tunable lasers both with and without mode hops.
POTENTIAL COMMERCIAL APPLICATIONS
Distributed optical fiber sensing which is the motivation for this work has applications in many commercial areas. This technology competes directly with conventional strain gage and thermocouple sensors in the industrial sensors market. Applications in air and ground based health monitoring will be dominated by the distributed optical fiber sensing in the coming years due to the need for high sensor density in these applications. The extremely high sensor density is also opening up new markets for routine sensing in industrial processes and products. One of the approaches pursued in this proposal will drastically increase system performance while reducing costs. This will of course remove barriers to entry in all market areas.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Brooks Childers
Luna Innovations Incorporated
2851 Commerce Street
Blacksburg , VA 24060 - 6657
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Luna Innovations Incorporated
2851 Commerce Street
Blacksburg , VA 24060 - 6657
| PROPOSAL NUMBER: | A2.01-8267 (For NASA Use Only - Chron: 013732 ) |
| PHASE-I CONTRACT: | NAS2-02001 |
| PROPOSAL TITLE: | Collaborative Routing Rationing Algorithm |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Collaborative Decision Making (CDM) embodies a new philosophy for managing air traffic. The initial implementation of CDM has been aimed at airport Ground Delay Programs (GDPs). However, it has become increasingly evident that very significant delays and throughput degradations have arisen from en-route airspace problems and limitations, particularly from convective weather activity. This effort focused on the application of CDM technology and concepts to the management of en-route traffic (Collaborative Routing). In this phase II effort, we will implement, demonstrate and evaluate a number of different collaborative routing rationing algorithms (CRRAs) to assign use of en route resources to individual flights. We have found that such algorithms are both feasible and can be made consistent with traffic management goals and with the CDM paradigm. The CRRA algorithms will be implemented in NASA?s System-Wide Evaluation Planning Tool (SWEPT) and a major Human-In-The-Loop simulation experiment will be conducted with participants from the FAA Air Traffic Control System Command Center (ATCSCC), Air Route Traffic Control Centers (ARTCCs) and Airlines Operation Center (AOC) facilities. This simulation will allow the air transportation community to discuss and refine the CRRA concept toward eventual deployment in the National Airspace System (NAS).
POTENTIAL COMMERCIAL APPLICATIONS
The product that is contemplated to result from this phase II effort is an initial implementation of the CRRA algorithms into the SWEPT system. Our intent is to obtain further government contracts from NASA and the FAA to further test, enhance and implement the CRRA concepts, procedures and tools into the operational ATC environment.
The new procedures enabled by these algorithms and concepts allow significant flexibility to the Users of the NAS and other international ATM systems. This flexibility afforded to airlines and other Users creates decisions that need to be made and managed. Thus, as a direct result of the implementation of CDM concepts, a new market has been created to help Users manage the new options that are created by CDM.
Metron Aviation has the necessary experience, organization and track record in such a market to be able to successfully provide services based on the CRRA concepts to airlines. Metron Aviation has developed and now provides as a service the Enhanced Substitution Module (ESM), which is a commercial tool to assist airlines in managing their substitutions during Ground Delay Programs.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Robert Hoffman
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA 20170 - 4835
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Metron, Inc.
131 Elden Street, Suite 200
Herndon , VA 20170 - 4835
| PROPOSAL NUMBER: | A2.01-9158 (For NASA Use Only - Chron: 012841 ) |
| PHASE-I CONTRACT: | NAS2-02003 |
| PROPOSAL TITLE: | Agent-based Simulation of NAS |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In our Phase I effort we demonstrated the feasibility of developing agent-based software for the simulation of NAS that (i) uses of extensions of UML to represent and agents and its interactions/protocols (ii) leverages research in verification of finite state machines to verify the agent protocols and (iii) automatically generates code for execution on IAI?s agent infrastructure, OpenCybele. The approach is based on a software engineering perspective that draws on ideas and recent developments in multi-agent systems, and ongoing work at IAI on multi-agent systems, which includes the development of DIVA, an agent-software verification tool, and Cybele. Having demonstrated feasibility, our Phase II effort will focus on developing a software prototype of the DIVA CASE tool for UML-based design, verification and automatic code generation of multiagent software for agent-based simulations of NAS. Our Phase II tasks include (i) development of a library of NAS agent interaction protocols that are AUML and FIPA ACL compliant (ii) extensions of the Phase I verification approach to protocol verification (iii) integration of the software with Rational Rose and (v) test and validate the case tool with NASA?s agent-based modeling and simulation Software being developed under the ATMSDI effort.
POTENTIAL COMMERCIAL APPLICATIONS
A UML-based CASE tool for software verification and validation of scalable complex multi-agent systems will be developed in this SBIR Phase II effort. To ensure industry wide acceptance, the tool will be developed as an add-on to Rational Rose and will be compliant with OMG and AUML industry standards. To ensure successful technology transfer in our Phase II effort, Rational Software Corporation, the developers of Rational Rose, will team with us as our commercialization partner. Partnering with Rational in our gives us access to a Rational customer base of 52,000 users. In addition, in this growing market of distributed multi-agent micro-simulation applications such as Air Traffic Control Simulation, Ground Transportation, Robotics and supply-chain integration, immediate customers for this tool exist in both the Government and Commercial Sectors. In the government sector our primary customer will be NASA, USDOT and DOD. In the commercial sector customers include spacecraft, air-traffic control, process control and manufacturing companies.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Dr. Leonard Haynes
Intelligent Automation, Inc.
7519 Standish Place, Suite 200
Rockville , MD 20855 - 2785
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Intelligent Automation, Inc.
7519 Standish Place, Suite 200
Rockville , MD 20855 - 2785
| PROPOSAL NUMBER: | A2.02-8202 (For NASA Use Only - Chron: 013797 ) |
| PHASE-I CONTRACT: | NAS2-02006 |
| PROPOSAL TITLE: | Maneuvering Rotorcraft Aeromechanics |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
"The Civil Tiltrotor (CTR) offers a unique opportunity to create a new aircraft market while off-loading a portion of the short-haul traffic." (Ref. NASA?s civil tiltrotor web page). Rotary-wing vehicles proposed for improved system capacity must meet global civil aviation requirements for safety, efficiency, and affordability. Many advances have been made in measuring characteristics of rotary-wing vehicles; however, measurements of dynamic, unsteady, and cross-coupling effects are still challenges posing impediments to rapid design cycles. An innovative method, accurately collecting such measurements, utilizes water as a medium for dynamic testing. This testing technique circumvents many of the problems presented by testing in air and provides better insight into the fluid mechanics, interactions and interferences. The method allows testing in slow motion, separates model and test support frequencies, greatly improves signal-to-noise ratios, and provides unparalleled flow visualization. Water tunnel testing will predict maneuvering aerodynamics and stability parameters early in the design cycle, reducing the development time, risk, and cost of new rotorcraft. The method also applies to high performance aircraft development.
POTENTIAL COMMERCIAL APPLICATIONS
AeroArts is marketing the capability for performing simultaneous flow visualization and force/moment measurement on rotor models, exploiting the special advantages of water as a test medium. There are three main target markets for AeroArts? equipment and expertise, namely commercial aircraft developers, academic institutions, and government research organizations. All manufacturers and developers of runway-independent aircraft are a marketplace for AeroArts? capability. Significant developments within the business sector include the resurging civil aviation market following the lull after September 2001 and the consequent return to concern about the air transportation system capacity. Runway-independent aircraft, and particularly the tiltrotor concept, are one of the brightest hopes for relieving aviation system capacity.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Brooke Smith
AeroArts LLC
PO Box 2909
Palos Verdes Peninsula , CA 90274 - 2909
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
AeroArts LLC
PO Box 2909
Palos Verdes Peninsula , CA 90274 - 2909
| PROPOSAL NUMBER: | A2.02-9586 (For NASA Use Only - Chron: 012413 ) |
| PHASE-I CONTRACT: | NAS2-02007 |
| PROPOSAL TITLE: | Revolutionary Runway Independent Aircraft Flight Simulation Technology |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A potentially key element of meeting NASA?s objective of dramatically increasing aviation system capacity is the utilization of runway independent aircraft (RIAs) to provide feeder service to major airports. Among the challenges in enabling high-volume terminal area RIA operations are identifying potential hazards of this flight regime and developing simulation technology for a complex aeromechanical environment involving the interaction of multiple types of air vehicles (e.g, RIA, fixed-wing,V/STOL). Fast, high-fidelity full-vehicle aeromechanical models and simulation tools are thus needed for RIAs that may be used in such roles. To meet this need, a suite of physics-based tools are being developed that capture challenging problems such as vortex wake encounters, modeling the airwakes of structures/terrain, ?self-interactions? such as vortex ring state, full vehicle gust response, and surface/ground vortex effects. Key technical innovations include novel fast viscous/turbulent wake decay methodologies tailored to RIAs, coupled with state of the art Real Time Free Wake simulation capabilities of CDI?s CHARM full-aircraft analysis. The effort will yield a Multiple Aircraft Simulation Tool (MAST) that will permit both off-line assessment and on-line, real-time flight simulation of RIA and non-RIA vehicles for flight planning, operational training, and evaluation of pilot workload and situational awareness requirements.
POTENTIAL COMMERCIAL APPLICATIONS
This new simulation technology would help government agencies and airport management determine safe trajectories and pilot workload for RIAs in terminal area flight as well as assess the impact of wake vortex interactions on IFR spacing requirements. Industry would use this tool to support design and analysis of new RIA concepts or applications, as well as assist development of next generation control system and flight director aids. Also, this new capability would directly support flight training activities by simulation manufacturers, aircraft operators, and the military services.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Daniel A. Wachspress
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ 08618 - 2302
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ 08618 - 2302
| PROPOSAL NUMBER: | A2.03-8183 (For NASA Use Only - Chron: 013816 ) |
| PHASE-I CONTRACT: | NAS2-02008 |
| PROPOSAL TITLE: | Intelligent Displays for Time-Critical Maneuvering of Multi-Axis Vehicles |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A novel training methodology that takes advantage of automation?s potential as a high-speed decision aid and the strengths of human pattern recognition and conditioning is proposed. The methodology applies optimal control theory to solve for a vehicle?s trajectory and the required control inputs. A preview of the commanded input suite is displayed to the pilot, which will dynamically update as the vehicle state changes in time. Using this and other innovative training displays, the pilot should be able to execute numerous maneuvers previously considered outside the operational envelope, in addition to performing ?standard? emergencies with a high degree of control consistency and accuracy. The preview display?s function can be extended to serve as an on-board pilot cueing aid. This methodology can be incorporated in flight simulators to train pilots across a range of platforms. The initial target application will be for rotorcraft autorotation, a particularly challenging and accident-prone multi-axis maneuver. Phase I demonstrated the concept?s feasibility in the rotorcraft autorotation domain. Phase II will focus on practical application and demonstration of the concept for rotorcraft autorotation training and its expansion to other flight vehicles.
POTENTIAL COMMERCIAL APPLICATIONS
The pilot training software developed under this project can be used to train helicopter pilots to perform safe autorotation maneuvers. The core technology may also be adapted for use in training human operators of other vehicles (flight, ground, and underwater) where multi-axis control in time-critical situations is required.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Bimal Aponso
Systems Technology, Inc.
13766 S. Hawthorne Blvd.
Hawthorne , CA 90250 - 7083
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Systems Technology, Inc.
13766 S. Hawthorne Blvd.
Hawthorne , CA 90250 - 7083
| PROPOSAL NUMBER: | A3.01-9332 (For NASA Use Only - Chron: 012667 ) |
| PHASE-I CONTRACT: | NAS1-02021 |
| PROPOSAL TITLE: | Measurement/Model of Effects of Grazing Flow on Resonator Impedance |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed SBIR Phase II research project is divided into four parts. The principal objective of the first part is to conduct hot-wire measurements to assess the accuracy of Dean?s Two Microphone Impedance Measurement Method. They will also be used to calibrate CAA numerical codes.
The principal objective of the second part is to develop a computationally simple 2-DOF resonator impedance model. The model will include non-linearity of the cavity sound particle velocities pumped into/out-of the inner/outer orifices. The model will be calibrated by Impedance measurements as a function of SPL and grazing flow speed.
The principal objective of the third part is to use hot-wires to measure cavity inflow/outflow sound particle velocities near the orifices of multiple orifice resonators, backed by a common cavity. These measurements should provide fundamental understanding of orifice-to-orifice interaction. They will be used to assess potential resonator bandwidth improvement as a function of orifice spacing in grazing flow applications.
The principal objective of the fourth part is to design and construct a prototype low self-noise probe microphone to measure broadband sound in high-speed flow duct applications. The performance of the prototype probe will be validated in the NASA LaRC 2-in by 2-in wind tunnel.
POTENTIAL COMMERCIAL APPLICATIONS
1. Software/hardware to conduct in-situ impedance measurements of liners installed in engine nacelles, wind tunnels, peak electrical energy turbine exhausts, HVAC ducts.
2. Software code to predict the impedance of 1-DOF and 2-DOF liners exposed to intense sound and high-speed grazing flow.
3. Software code to improve bandwidth performance of resonators based on orifice spacing.
4. Low self-noise probe microphone capable of measuring broadband sound in high-speed flow duct applications.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Alan Hersh
Hersh Acoustical Engineering, Inc.
780 lakefield Road, Unit G
Westlake Village , CA 91361 - 2657
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Hersh Acoustical Engineering, Inc.
780 lakefield Road, Unit G
Westlake Village , CA 91361 - 2657
| PROPOSAL NUMBER: | A3.02-8760 (For NASA Use Only - Chron: 013239 ) |
| PHASE-I CONTRACT: | NAS3-02006 |
| PROPOSAL TITLE: | PIP/MI Matrix SiC/SiC CMCs |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Innovative materials and processing capabilities are needed for the fabrication of ceramic matrix composite (CMC) components for efficient engine systems. NASA has identified CMCs as the only materials that will meet the combination of increased safety, reduced cost, and reduced weight as operational temperatures climb to higher levels (per AeroMat 2000 Annual Conference, June 2000). The current UEET (Ultra Efficient Engine Technology) initiative at NASA is looking at components such as combustor liners and vanes in particular. In light of these needs, this Phase II SBIR proposal addresses lightweight, high temperature, and low cost CMCs for engine and propulsion applications, particularly in the temperature range of 1200-1400C. The work specifically addresses the optimization of a hybrid PIP/MI SiC fiber-reinforced SiC-matrix composite (SiC/SiC). Effort will focus on using SiNC- and SiC-yielding preceramic polymers and a combination of PIP and melt-infiltration processing routes that will reduce the cost and time for producing SiC/SiC composites compared to traditional CVI/MI processing. The intent of this work is to refine and optimize the PIP/MI process developed in Phase I, generate a database of thermal and mechanical properties, and demonstrate fabrication capability of subcomponents. The innovation of this work lies in the ability of PIP processing to protect the fibers and interphase coating in a uniform manner compared to the CVI process, resulting in faster and less expensive processing as well as less variability in material properties.
POTENTIAL COMMERCIAL APPLICATIONS
The results of this program will be immediately applicable to the on-going work of a number of companies for programs such as Integrated High Payoff Rocket Propulsion Technology (IHPRPT) and other initiatives. For example, Boeing-Rocketdyne is interested in evaluating the use of CMCs for transpiration cooled injector faceplates or rocket engine thrust chamber liners for use on the IHPRPT initiative and other advanced engine programs requiring lightweight high temperature CMC materials. Understanding the thermal and mechanical performance of PIP-processed CMC materials will improve the timeline and extent of insertion of CMC materials into a variety of lightweight, high temperature applications. Rockwell Science Center has also expressed interest in C/SiC and SiC/SiC CMCs to use as the exhaust ramp material for the Aerospike Engine concept. General Electric Power Systems and Solar Turbines, Inc., are investigating SiC/SiC CMC materials for turbine engine applications and are very interested in opportunities for reductions in cost and processing time. NASA has identified CMCs as the only materials that will meet the combination of increased safety, reduced cost, and reduced weight as operational temperatures climb to higher levels (per AeroMat 2000 Annual Conference, June 2000). The need for high-temperature CMC materials is evident in applications such as turbomachinery, thrust chambers, seals, bladed-disks (blisks), and various structural panels that may have a requirement for integrated cooling channels. The NASA UEET program in particular has identified applications such as combustor liners and vanes that will require CMC components.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Timothy Easler
COI Ceramics, Inc.
9617 Distribution Ave
San Diego , CA 92121 - 2393
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
COI Ceramics, Inc.
9617 Distribution Ave
San Diego , CA 92121 - 2393
| PROPOSAL NUMBER: | A3.02-9716 (For NASA Use Only - Chron: 012283 ) |
| PHASE-I CONTRACT: | NAS3-02009 |
| PROPOSAL TITLE: | Thermal Spray of UV/Visible Light-Curable Polymide Powders |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The proposed innovative method for spraying UV-curable powders answers a critical NASA need for advanced coatings, and capitalizes on exciting commercial market opportunities. The technology employed combines UV/visible radiation with proprietary thermal spray processing methods yields an effective spray coating system for applying UV-curable powders without the use of solvents.
The spray process and the lay-up aspects of the powder spray technology address a NASA mandate for producing Advanced Materials with Reduced Emissions. The advanced materials processed with this technology have application in gas turbines, rocket and turbine-based combined cycle engines. The technology enables efficient high quality application of these advanced materials to fabricate lightweight jet engine components and other critical NASA and commercial equipment components.
The Phase I technical objectives were fully achieved by demonstrating feasibility of the novel UV/thermal spray technology to coat surfaces using advanced NASA UV-curable polyimide and various commercial UV-curable polymers. This was demonstrated for powder coating conventional materials, heat-sensitive and low-temperature substrates that included metal, glass, natural wood, paper and plastic.
The Phase II technical objective is to develop, fabricate and demonstrate a field portable prototype system. Phase II and Phase III matching resource commitments from the private sector of $680,000 have been obtained.
POTENTIAL COMMERCIAL APPLICATIONS
The proposed technology will meet critical needs in applying a broad-range of commercially available UV-curable thermoplastic and thermoset polymer powder materials as neat materials and as ?designer? composites, nanocomposites and functionally graded materials. Applications include adhesives, scratch resistant coatings, protective coatings, high-elongation coatings, self-extinguishing coatings, circuit board coatings and electrically conductive coatings.
Independent evaluations of several coatings sprayed onto a broad range of substrates in Phase I were made by major UV-curable powder coating manufactures. These evaluations were favorable and resulted in significant commitments by these companies to strategically partner with Montec Research for use of the proposed process for new and expanded applications of their powder coating products.
The entire coatings market was valued at $70.6B in 2000. The UV-curable powder coatings have 4%, or $2.8 of the entire coatings market, and its market share is growing at double-digit rates. The furniture and construction industries alone used a combined 48.4 million pounds of UV-curable coatings in 2001. Automotive and appliance manufacturing use over $21.1B of coatings annually and will increasingly look to UV-curable powder coatings for solutions. The architectural coatings market is $30.7B, and will also benefit from the proposed technology. The technology addresses these industrial requirements and others.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Lawrence Farrar
Montec Research
1901 South Franklin
Butte , MT 59701 - 3005
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Montec Research
1901 South Franklin
Butte , MT 59701 - 3005
| PROPOSAL NUMBER: | A4.01-8115 (For NASA Use Only - Chron: 013884 ) |
| PHASE-I CONTRACT: | NAS1-02009 |
| PROPOSAL TITLE: | Advanced Aircraft Parachute Recovery System |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
SATS is NASA's efficient personal air transportation vision. SATS airplanes must strive for higher levels of safety, speed, and comfort than small airplanes currently offer. BRS proposes to explore the dynamics of parachute inflation for aircraft in this new category and develop a system that will automatically and efficiently manage the parachute deployment sequence throughout their operating envelope. A prototype system for a 5,000 lb aircraft with a speed range from 60 to 300 knots will be developed using an unmanned drop test vehicle and cargo aircraft. BRS will also work concurrently with several light jet manufacturers to define the parachute/aircraft interface requirements. These relationships are critical because it is clear that a practical emergency parachute system for this application must be an integral component of the aircraft and will require contributions from a variety of engineering disciplines. These proposed tasks ideally fit BRS's experience and capabilities.
POTENTIAL COMMERCIAL APPLICATIONS
BRS is strategically positioned to take advantage a new generation of jet aircraft that will break the price and operational barriers of the past. An important key to this new concept is a focus on safety. These new aircraft must be both easier to fly and safer to operate. To date, BRS has signed letters of commitment from three light jet manufacturers to provide cooperative support during and after the Phase II contract period. This support will include engineering support in the areas of airframe structure, parachute installation, and crashworthiness enhancements necessary for the successful parachute deployment and subsequent landing. All of these companies have agreed to work with BRS with the ultimate goal of making their airframes ?BRS ready?. This will allow for the installation of a parachute system once it is available. Continued promotion of Light Jet BRS product will be attained through strategic partnering with other companies that emerge as this market expands and attracts more competitors. These markets can be a significant revenue source for BRS with the average recovery system price ranging from as low as $15,000 and up to $30,000.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Tony Kasher
Ballistic Recovery Systems, Inc.
300 Airport Road
South St. Paul , MN 55075 - 3551
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Ballistic Recovery Systems, Inc.
300 Airport Road
South St. Paul , MN 55075 - 3551
| PROPOSAL NUMBER: | A4.01-8324 (For NASA Use Only - Chron: 013675 ) |
| PHASE-I CONTRACT: | NAS1-02030 |
| PROPOSAL TITLE: | SATS- Lean Technology Design (LTD) |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
TECHNICAL ABSTRACT (LIMIT 200
WORDS)
The Phase I research has positive value for NASA?s SATS mission as
well as for the creation of near-term GA commercial product opportunities
(2005). While researching the Phase I CCT transfer process a modular cabin and
interior design partnership was created with RCO engineering. This automotive
style cabin technology had cost and comfort that was very attractive and Eclipse
Aviation engaged RCO for a prototype development and is negotiating a production
selection. Therefore the successful commercial deployment of a part of the
technology developed in this SBIR is possible during Phase II when Eclipse
reaches production in 2004. Phase III success will be achieved with the
production certification of a complete cabin module that has integrated CCTs.
Munro & Assoc. will partner with appropriate GA OEMs and retrofitters to
self fund a certification effort in parallel with the Phase II R&D. New GA
products will be spawned from the commercial success of the CCT product.
POTENTIAL COMMERCIAL APPLICATIONS
Commercial applications include
full cockpit and cabin installations in new as well as the 100,000 plus travel
active existing small airplanes in the country. Spin offs include software
applications for custom designs.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name,
Organization Name, Mail Address, City/State/Zip)
David Grieco
Munro and Associates
1749 Northwood
Troy , MI 48084 - 1600
NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address,
City/State/Zip)
Munro and Associates
1749 Northwood
Troy , MI
48084 - 1600
| PROPOSAL NUMBER: | A4.01-8541 (For NASA Use Only - Chron: 013458 ) |
| PHASE-I CONTRACT: | NAS1-02016 |
| PROPOSAL TITLE: | General Aviation Aircraft Information Network Server |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
DSI will develop an integrated
backplane/server solution for the SATS cockpit. The GAAINS (General Aviation
Aircraft Information Network Server) solution will provide the foundation for
tomorrows SATS cockpit. DSI believes in the spirit of SATS, and through the
integration of COTS technologies combined with current open architecture
standards, a new enabling platform will be developed which increases cockpit
functionality, while decreasing pilot workload at a fraction of the cost of
today?s systems. DSI?s GAAINS architecture is based on current communication
industry standards for redundancy and fail over scenarios. Ruggedized COTS
hardware coupled with proven smart software suites will provide new heights of
modularity, cost savings, and ease of access, operation and growth. This
backplane/server platform will ultimately increase the chance of success for
NASA?s SATS vision.
POTENTIAL COMMERCIAL APPLICATIONS
Commercial applications include
the GAAINS installations in the existing 100,000 travel active airplanes, as
well as new GA aircraft. This product will also be designed for integration with
the ground and satellite based GA extranet (SATS-Net). Outside of this, there is
almost no limit to expansion and opportunities in terms of providing information
to the GA aircraft. The implications of this are vast. As the Internet has
matured and brought forth a host of viable information services, the potential
for radically improving the availability of information services to the GA
aircraft is enormous. This also has strong potential for the commercial airline
industry. As concepts were borrowed from the automotive industry, the likelihood
that advances in the GA market could be applied back to the automotive industry
are very high.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name,
Organization Name, Mail Address, City/State/Zip)
Gregg Schneider
Dynamic Systems Integration
2649 Production Road
Virginia Beach , VA
23454 - 5228
NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address,
City/State/Zip)
Dynamic Systems Integration
2649 Production Road
Virginia Beach , VA 23454 - 5228
| PROPOSAL NUMBER: | A5.01-8361 (For NASA Use Only - Chron: 013638 ) |
| PHASE-I CONTRACT: | NAS8-01135 |
| PROPOSAL TITLE: | A Hybrid Piezoelectric/Fiber Optic System for Structural Health Monitoring |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Acellent Technologies is developing a Hybrid piezoelectric/fiber optic (HyPFO) structural diagnostic system that can be used to perform quick non-destructive evaluation and long-term health monitoring of aerospace vehicles and structures. The development is based on Acellent's state-of-the-art SMART Layer technology that utilizes a built-in network of piezoelectric sensors and actuators embedded on a thin dielectric carrier film, that can be easily mounted on the surface of existing structures or embedded inside composite structures during manufacturing itself. Due to the popularity of fiber-optic sensors, it is proposed to incorporate fiber-optic sensors into the current SMART Layer product to create a Hybrid piezoelectric/fiber-optic monitoring layer. The specific objectives of the phase I effort were to (1) Develop and fabricate a hybrid piezoelectric/fiber optic layer, (2) Integrate the fabricated prototype onto a demonstration structure and (3) Demonstrate functionality of the structurally integrated HyPFO monitoring layer. Anticipated phase II challenges include completing the design and development of the Hybrid piezoelectric/fiber-optic sensor layer, development of instrumentation for the hybrid layer in collaboration with fiber-optic companies, integration of the fiber-optic instrument and Acellent's current diagnostic instrument, development of diagnostic and application software for the HyPFO and testing and validation of the developed system with industrial partners.
POTENTIAL COMMERCIAL APPLICATIONS
This innovative technology has widespread applications in major industries including aerospace, aeronautical, automotive, and civil infrastructure. The company anticipates that the development and subsequent commercialization of the structural health monitoring system will lead to economic benefits these industries in the form of improved safety, reduced life cycle costs through real-time structural monitoring, improvement in structural reliability, reduction of maintenance cost and improved readiness for service. The proposed development is fully supported by its industrial counterpart - Thiokol Propulsion. These companies have extensive applications of the structural health monitoring system for their products including solid rocket motors, aircrafts structures, and missiles and will test the developed system on their products during the project.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Peter X. Qing
Acellent Technologies, Inc.
562 Weddell Drive, Suite 4
Sunnyvale , CA 94089 - 2108
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Acellent Technologies, Inc.
562 Weddell Drive, Suite 4
Sunnyvale , CA 94089 - 2108
| PROPOSAL NUMBER: | A5.01-9540 (For NASA Use Only - Chron: 012459 ) |
| PHASE-I CONTRACT: | NAS8-01139 |
| PROPOSAL TITLE: | Cavitation Model for Turbopumps in Liquid Rocket Systems |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
An innovative model for simulating cavitation in liquid rocket turbopumps using cryogenic working fluids is proposed. The formulation is based on a compressible gas-liquid framework that accurately models the acoustics in a multi-phase mixture. This methodology was successfully applied, in our Phase I effort, to simulate cavitating inducer performance in water. Our Phase II effort will extend this formulation to cavitation in cryogenic fluids which exhibit, relative to water, far more complex physics; cryogenic pumps operate at temperatures closer to the critical temperature of the working fluid making thermodynamic effects important. The model will account for the variation in the properties of the fluid as a function of the local fluid temperature that may vary due to energy requirements of vaporization/condensation. It will be incorporated within the commercially marketed code CRUNCH CFD that has a multi-element unstructured framework and is ideally suited for complex turbomachine configurations. This framework will be used as a design support tool to analyze inducer designs and in particular determine the suction specific speed at which head breakdown occurs. The limited reliability of current design tools in cavitating flow regimes makes this innovation a useful tool for turbomachine designers.
POTENTIAL COMMERCIAL APPLICATIONS
The software product resulting from our Phase II effort directly addresses core needs of liquid rocket system engineers both in the commercial aerospace industry, as well as NASA. As part of the NASA Space Launch Initiative, there is a current need to design turbomachinery systems that can be throttled over a wide range of off-design conditions. Extensive cavitation under these conditions can detrimentally affect the performance and durability of these systems. Current design procedures largely rely on a combination of one-dimensional analyses and correlations derived from historical design practices. However, these tools have limited reliability in the cavitating flow regime and designers have to be very conservative in defining a safe operational range. Furthermore, commercial CFD tools currently available are not adequate to model the compressibility effects that arise in cryogenic pumping systems. The proposed modeling software CRUNCH CFD addresses these deficiencies and can play a valuable role as a design support tool for refining preliminary designs as well as rectifying problems with existing operational systems. In addition to the liquid rocket industry, this simulation software can also be used in a wide range of the broader commercial market including: 1) Industrial pump market (e.g. boiler feed pumps, nuclear reactor safety pumps, etc). 2) Marine propellers, and 3) Recreational high-speed water crafts such as jet-skis.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Ashvin Hosangadi
Combustion Research and Flow Technology,
174 North Main Street, POB 1150
Dublin , PA 18917 - 2108
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Combustion Research and Flow Technology,
174 North Main Street, POB 1150
Dublin , PA 18917 - 2108
| PROPOSAL NUMBER: | A5.02-8289 (For NASA Use Only - Chron: 013710 ) |
| PHASE-I CONTRACT: | NAS1-02075 |
| PROPOSAL TITLE: | Flight Test Development of the X43A-LS Reusable Launch Vehicle |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Accurate Automation
Corporation proposes a three-pronged effort to build on the Phase I program to
develop technologies in support of the NASA Hyper-X program and the X-43 series
of research vehicles (X-43A, X-43B, and X-43C). The data and technologies
developed under the proposed Phase II program will also support the development
and testing of future hypersonic vehicles and reusable launch vehicles.
The
three major technical objectives of the Phase II program are: 1) Development of
a robust, fully nonlinear parameter identification method and associated tools
for extraction of dynamic models from flight test data, while rigorously
accounting for both process (state) and measurement noise. 2) Development of an
adaptive guidance and navigation control system for the development of optimal
flight trajectories for hypersonic vehicles including reusable launch vehicles.
3) Development of a low-speed flight test database for the X-43 configuration by
conducting envelope expansion flight tests to quantify the performance and
handling qualities of AAC?s X-43A-LS UAV.
POTENTIAL COMMERCIAL APPLICATIONS
Accurate Automation will use the
technologies and data developed during the proposed program to develop an
advanced flight control system that can be used for the X-43 program. This
package will have numerous alternate applications including use for a new decoy
system being developed for the military under the ALVIN Program.
The
telemetry system being developed using technologies being developed in this
program will be a part of our Aircraft Video Program and will transmit cockpit,
cabin and cargo bay imagery to the ground. This product will significantly
improve the current ACARS link used by the commercial carriers. Accurate
Automation is in negotiation with Federal Express to commercialize this
technology. Mr. Jim Phillips of Federal Express has visited AAC twice in the
past 3 weeks on this program to talk about a sizeable investment for adding this
technology to their fleet.
The Phase I of the X-43ALS development program
has successfully resulted in a vehicle configuration which includes a fully
integrated turbojet engine, remote control system, in-flight video, flight data
acquisition system, and ground control station. The X-43ALS vehicle provides a
unique capability as a testbed to support NASA?s development of hypersonic
vehicle technologies and designs.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR (Name,
Organization Name, Mail Address, City/State/Zip)
Christopher S. Gibson
Accurate Automation Corporation
7001 Shallowford Road
Chattanooga ,
TN 37421 - 1716
NAME AND ADDRESS OF OFFEROR (Firm Name, Mail Address,
City/State/Zip)
Accurate Automation Corporation
7001 Shallowford
Road
Chattanooga , TN 37421 - 1716
| PROPOSAL NUMBER: | A5.02-8890 (For NASA Use Only - Chron: 013109 ) |
| PHASE-I CONTRACT: | NAS1-02020 |
| PROPOSAL TITLE: | Magnesium Composites With Corrosion and Wear Resistant Coatings |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The project concerns the development of magnesium composites with advanced anodized coatings for improved corrosion and wear resistance. Coating production and the properties obtained are significant improvements over previous surface treatments for magnesium. In Phase I, over eighty experiments were conducted in the anodization of magnesium alloys and composites. Variables examined through these experiments include: voltage, electrolyte, temperature, magnesium alloy, cathode geometry, and time. Comparison of the coatings was conducted using microscopy, chemical analysis, and corrosion and wear tests. Four magnesium composites were obtained containing two different base alloys and four reinforcement phases (B4C, SiC, Al2O3, and carbon fiber). Anodization of two composites produced excellent coatings. The other two composites were shown to be incompatible with coating methods to resist corrosive environments. These results justify the goals of the project to identify appropriate magnesium composites and make them corrosion and wear resistant and eliminate from contention inappropriate materials. On completion of Phase II, the goals and objectives met will include a database will exist of known and tested anodized magnesium composites. The deliverables include anodized magnesium composite components produced and tested to NASA specifications for use in the reusable launch vehicle program.
POTENTIAL COMMERCIAL APPLICATIONS
Magnesium composites sell to industries who have special weight / wear or weight / strength requirements. Applications for magnesium composites include the automotive, military, aerospace, recreational, and electronic industries. Automotive uses include brake assemblies and pistons. Recreational uses of magnesium composites include tools, boat motors, and bicycle components. Potential government use of magnesium components include aerospace and military applications. Military uses include tank treads, hardware structural components and electronics. Aerospace applications are to be chosen part by part based on weight savings, and desired component physical properties. The P.I. of this project patented a process for anodizing magnesium alloys. The patent was assigned to a joint venture company which has gone on to license the technology in thirteen countries. The P.I. was part of the marketing and sales team that developed the patented process into a commercially viable process. The U.S. licensee of the previous patent is anticipated to be the conduit for further U.S. development and negotiations towards that end are underway.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Thomas Barton
Eltron Research Inc.
4600 Nautilus Court South
Boulder , CO 80301 - 3241
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Eltron Research Inc.
4600 Nautilus Court South
Boulder , CO 80301 - 3241
| PROPOSAL NUMBER: | A5.02-9147 (For NASA Use Only - Chron: 012852 ) |
| PHASE-I CONTRACT: | NAS1-02034 |
| PROPOSAL TITLE: | Field Joining of Ceramic Matrix Composites |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Silicon carbide fiber and carbon fiber reinforced silicon carbide composites are being considered for reusable launch vehicle airframe components. Because the furnaces needed to make components are expensive, and furnaces of the size needed to make airframe components simply do not exist, we need a way to join these composites together to make complex and large shapes. TDA proposes to address this problem by using welding equipment to join C/SiC and SiC/SiC composites. In Phase I, we demonstrated the ability to join these composites by producing a reaction-bonded silicon carbide in joints with commercial Gas Transferred Arc Welders at rates of 5 seconds/inch with strengths greater than the parts to be joined. In Phase II, we will optimize this welding/brazing process to produce prototypes including a 10 inch x 10 inch C/SiC joined composite. We will also produce a 1 inch x 6 inch C/SiC composite joined with a silicon alloy to produce a higher temperature capability joint. In addition to aerospace structures these technology will be commercialized in current markets for monolithic silicon carbide.
POTENTIAL COMMERCIAL APPLICATIONS
This project will develop a method for joining and repairing C/SiC and SiC/SiC composites and monolithic silicon carbide in the manner of advanced metal alloys. This project will allow large and/or complex shapes to be joined to produce reusable launch vehicle airframe components. In addition, it will lower the cost of producing current commercial items such as advanced turbine engines, radiant tube heaters, heat exchangers, armor, erosion and corrosion components.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Mr. Jack D. Sibold
TDA Research, Inc.
12345 W. 52nd Ave.
Wheat Ridge , CO 80033 - 1917
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
TDA Research, Inc.
12345 W. 52nd Ave.
Wheat Ridge , CO 80033 - 1917
| PROPOSAL NUMBER: | A5.03-8392 (For NASA Use Only - Chron: 013607 ) |
| PHASE-I CONTRACT: | NAS8-01141 |
| PROPOSAL TITLE: | Direct Metal Technology for Additive Manufacturing and Rapid Prototyping |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Solidica is proposing a filament based rapid prototyping machine for the production of net shape metal and functional gradient components. Net shape fully dense metallic parts have been the holy grail of rapid prototyping since its inception. Solidica, Inc. has patented an innovative ultrasonic approach for rapid prototyping of net shape metallic parts using a ribbon feedstock. By combining the use of ultrasonics for layer-by-layer material build up of metallic ribbons with a simple machining head Solidica achieves net shape fully dense metallic components in a fraction of the time and at a lower cost than traditional machining or casting. Extending this proprietary technology to use filament based feedstock rather than ribbon, will enable a complexity of geometry that is currently only achievable for fully dense metal components through investment casting. This innovation has enormous cost saving advantages for production of both complex metallic and bimetallic functional gradient test hardware. There is currently no technology that is readily capable of forming functionally gradient structures for complex geometric shapes.
POTENTIAL COMMERCIAL APPLICATIONS
The Phase II filament based RP machine proposed here is essentially an alpha version of a next generation product for Solidica, and described in our business plan. The rapid prototyping machine market is about $300M per year, and up to 50% of all applications for these machines have metal end items, meaning that some 50% of all purchasers are potential buyers of this product. Solidica's goal is to commercialize this Phase II system by 2003, and bring it to market in 2004. We have developed an launched a larger scale tooling oriented RP/RT product, and this is a technically feasible evolution with an important market potential.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Dawn White
Solidica
3941 Research Park Drive, Suite C
Ann Arbor , MI 48108 - 2219
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Solidica
3941 Research Park Drive, Suite C
Ann Arbor , MI 48108 - 2219
| PROPOSAL NUMBER: | A5.03-8601 (For NASA Use Only - Chron: 013398 ) |
| PHASE-I CONTRACT: | NAS8-01142 |
| PROPOSAL TITLE: | Economical Fabrication of Thick-Section Ceramic Matrix Composites, Phase II |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
No timely and cost-effective methods now exist for fabrication of thick-section (>=2"), continuous fiber-reinforced ceramic matrix composites (CMCs). Application of such CMCs can enhance the efficiency and performance, reduce the weight, improve the durability, and lower the cost of aerospace propulsion systems, particularly those used in high temperature, high-stress environments. Achieving these benefits requires development of matrix infiltration techniques capable of efficiently producing thick parts. The quality of such parts will also depend on implementation of improved fiber/matrix interfaces and interface deposition techniques. Carbon fibers are of particular interest as CMC reinforcements because they are relatively inexpensive, have higher strength and stiffness and lower density than oxide or non-oxide ceramic fibers, and retain their mechanical properties at very high temperatures. The main drawback of carbon fibers is their low oxidation resistance, which has prevented their extensive use in high temperature oxidizing environments. Oxide interfaces can potentially impart sufficient protection, as well as provide other essential interface functions related to load transfer between fibers. In Phase I, Ultramet demonstrated a unique and innovative process for depositing oxide interfaces, specifically ultraviolet-enhanced chemical vapor deposition (UVCVD), throughout thick fiber preforms. Ultramet also successfully achieved rapid infiltration of carbide matrices into thick-section (1") fiber preforms, up to 98% dense, using an innovative melt infiltration process and obtained initial mechanical properties and oxidation performance of the resultant composites. In Phase II, Ultramet will optimize material selection and processing parameters to produce low-porosity carbon/silicon carbide (C/SiC) thick-section CMCs having optimal strength, stiffness, and oxidation performance, and scale up the processing to fabricate components up to 14" diameter x 2.5" thick.
POTENTIAL COMMERCIAL APPLICATIONS
Cost-effective, rapid fabrication of thick-section ceramic matrix composites will potentially benefit a number of component applications. Within this project, aerospace applications are of particular interest. A broad range of aerospace components would benefit from an economical thick-section C/SiC composite offering a long lifetime in a high temperature oxidizing environment while under load. Specific applications include high temperature engine panels (e.g. those needed for hypersonic propulsion hot gas flow paths), combustors, inlet nozzles (stators), turbine disks, process industry parts requiring high temperature capability and corrosive environment resistance for extended periods (e.g. hot gas and liquid handling equipment), furnace structures, and high temperature filter elements. Successful generic demonstration and database development of the proposed technology could support any of these applications.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Jason R. Babcock, Ph.D.
Ultramet
12173 Montague Street
Pacoima , CA 91331 - 2210
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Ultramet
12173 Montague Street
Pacoima , CA 91331 - 2210
| PROPOSAL NUMBER: | A5.03-9756 (For NASA Use Only - Chron: 012243 ) |
| PHASE-I CONTRACT: | NAS8-01146 |
| PROPOSAL TITLE: | Better Pressure Vessel Impact Resistance Utilizing Filament Wound Hybrid Fibers. |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
HyPerComp Engineering, Inc. proposes to develop filament wound composite pressure vessels with superior low and high velocity impact resistance as well as improved high temperature (fire) survivability.
The current generation of high performance filament wound composite pressure vessels as utilized in solid propellant propulsion, space craft energy storage systems, launch tubes, self contained breathing apparatus, and other demanding applications utilize carbon fibers in order to obtain a high performance to weight ratio. While the impressively high tensile strength of these fibers provides for light weight pressure vessels, the resulting thin wall thickness combined with carbon fiber?s sensitivity to ?bruising? can result in significant risk of impact damage. Even relatively light and difficult to detect impacts can potentially degrade the capability of these pressure vessels.
HyPerComp Engineering has recently completed a Phase I SBIR through NASA, MSFC demonstrating significant improvement in impact resistance in high performance pressure vessels (NAS8?01146). The effort proposed herein builds upon that knowledge, expands it into higher energy levels, and incorporates heat resistant materials currently under evaluation at NASA, MSFC to develop a ?next generation? filament wound pressure vessel with significant improvements in both high and low velocity impact capability as well as improved fire resistance
POTENTIAL COMMERCIAL APPLICATIONS
Both military and aerospace pressure vessel applications where high performance and mission reliability are required are natural targets for the technology proposed for development herein. Similarly the commercial pressure vessel industry, while not requiring quite as high of performance, is always keenly aware of any technology that might make the product safer. These seemingly separate but demanding industries are always searching for improvements in performance and safety with regard to pressure vessels. The demonstrated technology has the potential of taking both attributes to a new level.
In the aerospace market composite pressure vessels are relied upon for both performance (low weight) and reliability. The thin walled nature of these high performance pressure vessels make them susceptible to impact damage, often undetectable impact damage. An improvement in damage tolerance with little to no performance sacrifice is of significant worth and should be readily marketable either through the sale of specific hardware or the licensing of specific technology.
Likewise there are many commercial applications where pressure vessels are used in demanding applications. An improved, significantly lighter yet extremely rugged SCBA cylinder would be viewed as a significant improvement in safety and would find a significant market niche for demanding applications.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
James Patterson
HyPerComp Engineering, Inc.
1080 North Main Suite #2
Brigham City , UT 84302 - 1470
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
HyPerComp Engineering, Inc.
1080 North Main Suite #2
Brigham City , UT 84302 - 1470
| PROPOSAL NUMBER: | A5.04-9065 (For NASA Use Only - Chron: 012934 ) |
| PHASE-I CONTRACT: | NAS13-02002 |
| PROPOSAL TITLE: | Multi-disciplinary Multiphase Flow Analyzer |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Simulation methodologies which describe complex, Multiphase, flow phenomena including cavitation, cryogenic fluid management, coolant spray and impinging jets will be developed. Accurately described real fluid properties will be employed in an integrated simulation tool, that involves thermodynamics and fluid dynamics models, to describe local vaporization phenomena in liquid rocket engine propellant delivery systems, propellant tanks and the test facilities. Bubbly flows will be simulated with a homogeneous or heterogeneous mixture model, which emphasizes the computational efficiency and modeling effectiveness. Cavitating venturi meter and pump flows, cryogenic propellant tank filling processes and evaporating cooling jets can be analyzed with this methodology. More accurate propellant metering, oscillatory inlet flow characterization and accurate description of the thermodynamics environment of cryogenic fluid systems will be the result of this project. Other complex flows in propellant delivery systems or coolant flows in test facilities will also be amenable to analysis with the produced methodology.
POTENTIAL COMMERCIAL APPLICATIONS
Advanced propulsion systems of the reusable launch vehicle designs require heavy testing in the liquid propellant supply systems. Cryogenic propellants are usually stored near the saturation conditions. This means that system optimization would involve a lot of analyses trying to identify the possible onset of cavitation anywhere in the supply systems. Also, analysis to predict the phase change due to thermal flushing is also important in cryogenic fluid management. This requirement is shared across the Government agencies and the private industry, which organizations are involved in aerospace research and development.
Cross industry application may also include marine propulsion designs for cavitation diagnostics, water pumps design, valve operation design in industrial liquid flow circuits and artificial heart design, etc. The fundamental multiphase flow physics involved in these applications are similar to what are proposed in this research. There may be some application specific variations in fluid properties that required further tailoring to have good representation of the type of flow under investigation. With these resolved in the Phase II and Phase III research, the present multiphase flow analyzer will become widely accepted in the industry.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Yen-Sen Chen
Engineering Sciences, Inc.
1900 Golf Road, Suite D
Huntsville , AL 35802 - 4319
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Engineering Sciences, Inc.
1900 Golf Road, Suite D
Huntsville , AL 35802 - 4319
| PROPOSAL NUMBER: | A5.04-9367 (For NASA Use Only - Chron: 012632 ) |
| PHASE-I CONTRACT: | NAS13-02004 |
| PROPOSAL TITLE: | Intelligent Wireless Sensor Communication for Health Monitoring |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The key innovation of this proposal is the design of a low-cost high data rate wireless sensor network for rocket engine test facilities. Time Modulated Ultra-wideband (TM-UWB) technology is the key to implementing this wireless sensor network. To the best of our knowledge, no other wireless technology can achieve the high data rate and high channel capacity required for rocket engine testing. During Phase I, we have demonstrated the feasibility of our concept. In Phase II, we will further develop the complete architecture and develop a prototype wireless sensor network to evaluate the system performance and fields demonstrate its capability. The proposed wireless sensor network consists of a network controller and many smart sensor nodes. Each smart sensor node is equipped with a TM-UWB transmitter, a narrow band receiver, and a multiplexed data acquisition system. The UWB transmitter is used to transmit the digitized sensor data to the network controller at a data rate of at least 1.25Mbps. The narrow band receiver is used to receive control and configuration commands from the network controller, which will be very infrequent and can be very low data rate. We believe this is the most cost effective architecture for Phase II.
POTENTIAL COMMERCIAL APPLICATIONS
For current rocket engine testing, a long wire needs to be connected from each sensor on the test stand to the signal-conditioning center. Furthermore, the sensor configurations always need to be changed for testing different rocket engines. These wiring and configuration changes represent significant cost and time for the test. With the proposed TM-UWB wireless sensor networks, this cost and the preparation time can be greatly reduced. This cost and time saving will attract government agencies, including NASA and US Air Force, to use this wireless sensor network for their engine testing facilities. None of the existing wireless technologies can provide high data rate and high channel capacity required in rocket test facilities, which often involves hundreds of sensors. TM-UWB also offers other advantages over other wireless technologies, such as spectral efficiency, coexistence with other RF devices without causing interference, and multipath Immunity. Beyond engine testing, this wireless sensor network can be for any equipment health monitoring and Supervisory Control and Data Acquisition, especially for large manufacturing facilities. The fact that TDC raised $100 million of private funds for this development proves that there are many investors who believe this concept will yield valuable products.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Chujen Lin
Intelligent Automation, Inc.
7519 Standish Place, Suite 200
Rockville , MD 20855 - 2785
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Intelligent Automation, Inc.
7519 Standish Place, Suite 200
Rockville , MD 20855 - 2785
| PROPOSAL NUMBER: | A6.01-8259 (For NASA Use Only - Chron: 013740 ) |
| PHASE-I CONTRACT: | NAS5-01206 |
| PROPOSAL TITLE: | Composite Grids for Ion Thruster |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The grid stack used on ion engines is a critical component influencing engine performance and weight. The grids currently used on ion thrusters and in laboratory ion sources use costly machined pyrocarbon grids with thick ceramic mounting posts and they require assembly of several parts.
This project investigates novel carbon grid materials and sandwich construction using insulating core materials that resist shorting caused by sputtered contaminates. The benefits of this grid concept are: precision shape, vibration resistance, light weight, fewer grid components required, scalability to small and large grid diameters (including high power ion engines for nuclear electric propulsion), and low cost.
Phase 1 demonstrated feasibility of fabricating small sandwich grids with suitable precision and voltage standoff. Phase 2 shall futher develop materials and processing, and fabricate full-scale sandwich grids for use in NASA Ion Engines.
POTENTIAL COMMERCIAL APPLICATIONS
Low cost carbon grids have commerical application in Ion Sources and Ion Engines. The sandwich grids architecture offers special benefits to Ion Thrusters for in space propulsion, including high power nuclear electric propulsion. The methods developed may be useful for other electron sources in microwave tubes, lasers, accelerators, and electronics display technology.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Y Robert Yamaki
Energy Science Laboratories, Inc.
6888 Nancy Ridge Dr.
San Diego , CA 92121 - 2232
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Energy Science Laboratories, Inc.
6888 Nancy Ridge Dr.
San Diego , CA 92121 - 2232
| PROPOSAL NUMBER: | A6.01-8910 (For NASA Use Only - Chron: 013089 ) |
| PHASE-I CONTRACT: | NAS8-01181 |
| PROPOSAL TITLE: | FLIGHT WEIGHT MAGNETS USING CARBON NANOTUBES |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The motivation for the Phase I effort to use carbon nanotubes for application to magnets in space was based on published reports that their current carrying capacity was 10,000 times that of other superconductors and that their mechanical strength was 100 times that of steel on a mass basis. In phase I, we investigated the properties of this amazing new material and concluded the original premise was substantially correct, although some details remain to be investigated and a whole new suite of tools and machinery are required. In Phase II, we are proposing to advance this technology to the point of winding a nanotube magnet coil, testing it and delivering it to NASA/MSFC. The main thrusts of the program include some more definitive measurements of superconducting properties as a function of temperature, magnetic field and mechanical strain. In parallel efforts, tools will be developed to wind the carbon nanotube coils, attach electrical leads to them and test their performance. We will update the conceptual design for a NASA magnet for an MHD disk generator using carbon nanotube conductors and perform sufficient economic analyses to determine the economic feasibility of this application of carbon nanotubes.
POTENTIAL COMMERCIAL APPLICATIONS
The most immediate commercial applications of this technology are for magnets that are deployed on space vehicles and aircraft for power and propulsion. A dramatic reduction in weight is possible as a result of the high current density. This potential, factored into a power or propulsion system weight that is mostly from the magnet with existing technology, has the result of dramatic increases in performance per unit system weight. In addition there are potential fruitful applications to magnetic nozzles, both the generator and accelerator in the AJAX type propulsion system, flow modification systems for hypersonic aircraft and magnetic confinement of fusion reactions. These applications, particularly in space can justify a premium price because of the cost of launching mass into space. If the technology is developed at a price competitive with other superconductors, there is a huge market in earth based electrical equipment such as large electric motors and generators, transformers, power transmission lines, ground fault isolators, magnetic field gradient particle separators, magnets for MRI machines and all the other markets identified for high temperature superconductors identified in the U. S. DOE market penetration studies.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
James N. Chapman
LYTEC LLC
1940 ELK RIVER DAM ROAD, P.O. BOX 1581
TULLAHOMA , TN 37388 - 1581
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
LYTEC LLC
1940 ELK RIVER DAM ROAD, P.O. BOX 1581
TULLAHOMA , TN 37388 - 1581
| PROPOSAL NUMBER: | A6.01-8948 (For NASA Use Only - Chron: 013051 ) |
| PHASE-I CONTRACT: | NAS8-01148 |
| PROPOSAL TITLE: | Ultrahigh Energy Propulsion By Pulsed Magnetic Field Compression of Fissile Plas |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
A new fission powered space power and propulsion system based on using a non-moving fissile gas is proposed. The main innovation in the proposed fission based propulsion system is the use of well-established fusion plasma confinement and compression methods to achieve a supercritical condition in a highly subcritical fissile gas. In particular, electromagnetic induced shock wave compaction and gas dynamic trap techniques are merged to bring a relatively small volume (~ 1 m3) of a fissile (235U, 233U, or 239Pu) compound gas (such as UF4) to prompt supercriticality condition, thereby, releasing an intense pulse of fission power. A magnetic field compaction scheme is designed to directly convert the fission energy to electricity. The specific energy of the proposed nuclear electric system for megawatt level power operation is well above 1 kWe/kg. An alternative direct propulsion system is designed based on using a merger between Magnetized Target Fusion (MTF) and hydrodynamic confinement techniques to achieve long duration (~ 100 to 1000 ms) criticality and ultrahigh burnup in a fissile gas. The MTF technique induces a large pressure ratio (~ 10) adiabatic compaction of fissile gas by rapid collapsing of a cylindrical layer of a low neutron absorbing metal (Al or Zr). Hydrodynamic confinement in a leaky reversed mirror configuration is used to contain and direct the fission plasma through a nozzle, thereby, generating intense thrust (~ 100s of klb) at specific impulse levels in excess of 2000 seconds.
POTENTIAL COMMERCIAL APPLICATIONS
A shock wave driven fission power system utilizes fissile materials in highly subcritical configuration. The low nuclear material inventory combined with the active nature of the criticality inducing process is a unique feature of the proposed space nuclear power and propulsion system. The exceptional simplicity and safety of the proposed concept provides an unlimited potential for a wide range of space power and propulsion applications. Furthermore, the success of the proposed project will potentially lead to terrestrial applications including commercial nuclear power generation at a very competitive cost with improved safety features.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Angelo Ferrari
New Era Technology Inc.
2435 NW 36 Terrace
Gainesville , FL 32605 - 2633
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
New Era Technology Inc.
2435 NW 36 Terrace
Gainesville , FL 32605 - 2633
| PROPOSAL NUMBER: | A6.02-9259 (For NASA Use Only - Chron: 012740 ) |
| PHASE-I CONTRACT: | NAS8-01152 |
| PROPOSAL TITLE: | Time-stepped & discrete-event simulations of electromagnetic propulsion systems |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The existing plasma codes are ill suited for modeling of mixed resolution problems, such as the plasma sail, where the system under study comprises subsystems with diverse modeling paradigms (e.g., fluid, kinetic) at differing levels of temporal and spatial resolution. Such complex systems are not unique to propulsion studies, but are commonly encountered in wide variety of fields. In Phase I, we were able to develop and successfully test the core technology for multi-resolution modeling within two distinct computational paradigms. By introducing a temporal mesh, we successfully overcame a major obstacle in the use of time-stepped simulations for multi-resolution problems. However, even more significant is our finding that discrete event simulation methodology works quite well for many-body systems such as plasmas with several orders of magnitude performance advantage over equivalent time-stepped simulations. The importance of this result cannot be overstated as it will have immediate repercussions in all fields where time-stepped modeling are currently used. Using these early versions of our code, we were able to address a number of outstanding issues in regards to the feasibility of plasma sails. Our objectives for Phase II are (i) to fully develop the codes, (ii) address the issues regarding the feasibility of plasma sails such as expansion of the magnetic bubble by the plasma source and the resulting drop-off of the magnetic field strength with radial distance, and (iii) prepare plans for marketing our technology in Phase III.
POTENTIAL COMMERCIAL APPLICATIONS
The successful completion of the proposed R&D will bring into existence a new generation of simulation codes that would position SciberNet as the premier provider of plasma simulation services to customers in the Federal Government and the private sector such as the aerospace and electronics industries. The discrete event simulation code (DES) presents a break through technology and will be applicable to most fields that are currently using time-stepped simulations. To this end, we plan to design our 3D DES code based on a general architecture so that it can be readily adapted to other applications such as gravitational or fluid simulations, among others. One of our objectives in Phase II is to conduct market analysis to identify the most suitable market nitche beyond propulsion and plasma simulations that we can pursue in Phase III. The development of the DES code has also led us to a new concept in interactive simulation and visualization with high commercial potential. Although a significant fraction of our revenue is projected to be from a service model, we have already had discussions with several vendors (e.g., Analytical Graphics) about the possibility of developing modules, based on simplified versions of our codes that can be integrated into existing commercial software.
In that regard, our business model will be similar to a number of companies that offer specialized commercial modeling tools such as OPNET, SES, and WorkBench.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Homa Karimabadi
SciberNet, Inc.
13270 Russett Leaf Lane
San Diego , CA 92129 - 2369
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
SciberNet, Inc.
13270 Russett Leaf Lane
San Diego , CA 92129 - 2369
| PROPOSAL NUMBER: | A6.02-9453 (For NASA Use Only - Chron: 012546 ) |
| PHASE-I CONTRACT: | NAS8-01153 |
| PROPOSAL TITLE: | A Solid Expellant Plasma Source/Contactor for Electrodynamic Tethers |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The Solid Expellant Plasma Source/Contactor (SOLEX) is a new technological development that considerably simplifies the plasma generation and electron emission process. Under the Phase-1 effort, the preliminary work to demonstrate the feasibility of the SOLEX concept was accomplished. The intent of the proposed Phase-II effort is to develop a flight-level design for a SOLEX plasma generator, for electrodynamic tether systems, and fabricate an Engineering Unit test device that is appropriate for flight validation. The SOLEX will operate directly off of the tether-generated high-voltage (requiring no conditioned power or control electronics) and will eliminate the need for high-pressure gas containers, pressure regulators, plumbing and valves?required by present state-of-the-art Hollow Cathode devices. These are significant improvements over current state-of-the-art contactors that impinge heavily on spacecraft resources. Based on available flight data and Phase-I tests, current capacity can range from a few milli-amps to several amps. By nature of its design, the SOLEX should not be sensitive to contamination and should have essentially unlimited restart capability?both are issues with state-of-the-art contactors. Moreover, the simplicity of the design concept suggests that flight devices will be relatively inexpensive.
POTENTIAL COMMERCIAL APPLICATIONS
The SOLEX should be an attractive alternative to present plasma generation devices because of its simplicity, robustness, efficiency, and predicted low-cost. Potential space technology applications include (1) plasma contactors for electrodynamic space tethers, (2) plasma sources for plasma sails, and (3) electrical neutralization of high-altitude (e.g., synchronous orbit) spacecraft. A low-mass device, such as the SOLEX, is required to enable the practical application of electrodynamic tether propulsion devices to the end-of-life deorbit of satellites where system mass, simplicity and robustness are critical concerns. As space debris becomes a growing concern to NASA and the DOD, this application will become increasingly important. Potential ground-based applications include plasma sources for sputter deposition systems used in the semiconductor industry.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Dr. Nobie H. Stone
SRS Technologies
500 Discovery Drive
Huntsville , AL 35806 - 9999
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
SRS Technologies
500 Discovery Drive
Huntsville , AL 35806 - 9999
| PROPOSAL NUMBER: | A7.01-9688 (For NASA Use Only - Chron: 012311 ) |
| PHASE-I CONTRACT: | NAS1-02013 |
| PROPOSAL TITLE: | Flow Driven Oscillating Vortex Generators for Control of Boundary Layer Dynamics |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Active boundary layer control is effective in controlling boundary layer dynamics, but imposes a penalty because of the power and hardware required. In Phase I a family of self-excited Flow Driven Oscillating Vortex Generators (FDOVGs), which oscillate at frequencies where the induced vortical flows have length scales that are of the order of the scale of the aerodynamic surface, and therefore are useful to control boundary layer dyamics, have been demonstrated. The FDOVGs receive power from the mean flow to operate and generate large amplitude oscillations. Deployment can be achieved with no external power by using a flow change to activate the FDOVG, or with external power by changing the geometry or stiffness of the FDOVG.
The Phase II effort will provide the aerodynamicist with a new flow control actuator that can be integrated into aerodynamic components. Micro- as well as macro-scale devices with applications on micro air vehicles, unmanned vehicles, jetliners, and over the road vehicles such as tractor-trailer trucks can be developed. The FDOVG is a simple, inexpensive, reliable, and potentially single-part solution to providing effective flow control without significant penalty for a large variety of difficult applications.
POTENTIAL COMMERCIAL APPLICATIONS
The FDOVG system represents an innovative family of flow control devices
that could yield revolutionary increases in performance of air and sea
vehicles. For example, FDOVGs have the potential to reduce landing speeds
on general aviation aircraft, thereby enhancing safety and utility.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Alan J. Bilanin
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ 08618 - 2302
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Continuum Dynamics, Inc.
34 Lexington Avenue
Ewing , NJ 08618 - 2302
| PROPOSAL NUMBER: | A7.02-9869 (For NASA Use Only - Chron: 012130 ) |
| PHASE-I CONTRACT: | NAS4-02007 |
| PROPOSAL TITLE: | Solution based 3-D Mesh adaptation for Heat and Mass predictions |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
In this proposal, a solution-based three-dimensional mesh adaptation procedure is described. The algorithm utilized in our code can very effectively refine the mesh in regions of interest by moving nodes in regions of unchanging flow field for accurate prediction of steady and unsteady pressure and thermal load distributions. Our flow solver interacts with most popular commercial CAD packages through the CGNS interface and currently interfaces with OPTIMESH/MOM3D through a user friendly GUI provided with ICEM CFD mesh generator package.
Benchmarks have been performed; among them is the moving-lid (lid-driven) cavity problem. This problem is a well-known standard to test CFD codes. The results of these benchmarks have been excellent.
Further correlation and more stringent benchmarking will continue as part of the Phase II efforts. Enhancement of the code is required to accept additional mesh element types, for unsteady flows, inclusion of species, reaction and other scalar functions.
Our objective for Phase II is to develop a product involving both the CFD solver and the grid adaptation module within a single package.
POTENTIAL COMMERCIAL APPLICATIONS
The commercial applications of this package are varied and many since the adaptation procedure may practically be applied to almost any field or industry such as structures, acoustics, earthquake simulation, magnetic fields and so on. This is because the code accepts any parameter as a vector or scalar quantity and performs adaptation based on the error estimates obtained from the initial solution and variation of these variables.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Bahman Hadi
Cascade Engineering Services, Inc.
2515 140th Ave N.E, Suite E100,
Bellevue , WA 98005 - 1885
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Cascade Engineering Services, Inc.
2515 140th Ave N.E, Suite E100,
Bellevue , WA 98005 - 1885
| PROPOSAL NUMBER: | A7.02-9910 (For NASA Use Only - Chron: 012089 ) |
| PHASE-I CONTRACT: | NAS4-02008 |
| PROPOSAL TITLE: | Adjoint-Based Design Software Using Adaptive Finite Element Methods |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
ResearchSouth has developed a powerful design optimization algorithm using an adjoint-based methodology for advanced aerospace vehicles including the airframe aerodynamic shape and the integrated propulsion system. The significance is that this algorithm separates the geometric entities from the optimization process allowing an independent linkage with many CAD packages and at much lower cost. All objectives have been met for the Phase I project. A computer software package, termed SAMdesign, now has the capability to solve the three-dimensional Euler equations, solve the adjoint of the Euler equations, and change the vehicle shape subject to constraints. All of these solutions are performed on unstructured tetrahedral meshes using a Finite Element based numerical algorithm. Four test cases have been successfully computed including a generic aerospace vehicle. Phase II will include multi-disciplinary effects, coupled physics for aerodynamics / propulsion / structures, fast finite element meshing methods, and will develop the software into a production package. Extensive verification and validation will be done on NASA configurations. The product will be documented, delivered and installed at NASA with a user-training course given. This will provide NASA with a powerful software tool to perform very efficient and rapid design assessment of evolving next generation space vehicles.
POTENTIAL COMMERCIAL APPLICATIONS
The following are some of the many commercial applications for the adjoint-based finite element design software. (1) design of automobile airbags (2) design of viscous mixing processes for chemical manufacturing companies, (3) design of more efficient internal combustion engines, (4) commercial airplane design for improved fuel economy (5) analysis and design of waste disposal systems, (7) design of air conditioning systems for large buildings, (8) housing design to withstand tornadoes, (9) biomedical application for design of cardiovascular devices, and (10) office building design for protection from terrorists activities.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Lawrence W. Spradley
ResearchSouth, Inc.
555 Sparkman Dr. Suite 1612
Huntsville , AL 35816 - 0000
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
ResearchSouth, Inc.
555 Sparkman Dr. Suite 1612
Huntsville , AL 35816 - 0000
| PROPOSAL NUMBER: | A7.03-8825 (For NASA Use Only - Chron: 013174 ) |
| PHASE-I CONTRACT: | NAS4-02010 |
| PROPOSAL TITLE: | A Non-Intrusive Radar Sensor for Engine Vibration Monitoring |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Radatec has demonstrated that a radar/microwave sensor can be used to measure the dynamics of turbine fan blades. The sensor was designed for function in harsh environments (+2500 F) of the combustor section. An alpha prototype was built and data were collected on a turbine simulator. The proposed Phase II project seeks to take this technology to the next step- a commercial product running on actual turbine engines providing new and useful information to turbine operators.
In Phase II, technical goals are to optimize the sensor antenna, construct a 35.0 GHz radar subsystem, and built an antenna fitting that will mount the sensor to a turbine engine through existing holes in gas turbines. Finally, a hardened beta prototype sensor will be built and tested on a General Electric F404 turbofan engine. The end result of Phase II will be a tested beta prototype that Radatec will market to industrial and government users.
POTENTIAL COMMERCIAL APPLICATIONS
There is a strong unsatisfied need in the marketplace for robust, high bandwidth sensors that can gather data directly from the combustor section of a turbine engine. Existing engine health monitoring systems do not provide useful measurements of engine health, because they cannot pinpoint causes of damage- and often provide warnings of damage late. This technology offers a compelling value proposition to operators by allowing them to safely increase there scheduled maintenance interval, thereby reducing cost and downtime.
Land-based power producing gas turbine engines and aircraft engines are both being targeted as the first markets for the sensor. The market for land-based turbines is estimated at $56-100 million per year with the aircraft market estimated at an addition $75-$150 million per year. Land-based turbines will be the point of entry into the market due to their lower reliability, and more immediate impact on an electric utility?s bottom line. As active blade tip clearance aircraft engines become more prevalent, the Radatec sensor has the potential to improve cruising fuel efficiency by 1-2%.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Scott Billington
Radatec, LLC
430 10th Street, Suite N-104C
Atlanta , GA 30318 - 5798
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Radatec, LLC
430 10th St. NW, Suite N-104C
Atlanta , GA 30318 - 5798
| PROPOSAL NUMBER: | A7.03-8908 (For NASA Use Only - Chron: 013091 ) |
| PHASE-I CONTRACT: | NAS4-02011 |
| PROPOSAL TITLE: | Rayleigh/Mie Lidar for Non-intrusive Measurement of Aircraft Air Data Parameters |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
We propose to develop an Optical Air Data System (OADS) to measure air vehicle airspeed, Mach number, atmospheric pressure, atmospheric temperature, angles of attack and sideslip, and air density using a non-intrusive technique termed Rayleigh/Mie lidar. Currently, these parameters are measured using numerous sensors that cannot perform adequately for high-performance/high-speed aircraft. Recent research into OADS has focused on coherent Mie (aerosol) lidar, which fail in many flight regimes due to insufficient aerosol scattering. Moreover, Mie lidar cannot measure temperature or pressure. Rayleigh (molecular) lidar overcomes these shortcomings by scattering from the air itself to provide velocity, temperature and pressure. Rayleigh/Mie lidar has the additional benefit of providing improved velocity measurements when sufficient aerosols exist. Thus, OPHIR's Rayleigh/Mie OADS offers performance, weight and cost savings advantages not provided by any other commercially available or developing technology.
The Phase I research effort has been very successful. All objectives were met and all tasks successfully completed. This research has proven the feasibility of a Rayleigh/Mie lidar OADS.
Phase II will include the development of a flyable prototype. The Boeing Company will provide flight-testing, and Goodrich Aerospace will perform wind tunnel testing, at no cost to the Phase II effort.
POTENTIAL COMMERCIAL APPLICATIONS
This technology offers significant commercial potential for flight test operations, military aircraft and commercial aircraft. As an indication of this commercial potential, we have been very successful in gaining support from major airframe and air data system manufacturers. OPHIR's Rayleigh/Mie approach has gained the support of The Boeing Company Flight Test Group (providing flight testing at no cost to the Phase II effort), Goodrich Aerospace (providing testing and evaluation support at no cost to the Phase II effort) and the European Aeronautic Defense and Space Company- EADS(Airbus).
Thus, the world's two largest airframe manufacturers, Boeing and EADS(Airbus) and one of the largest manufacturers of air data systems, have all expressed interest and support for this research. The Phase II research will include cooperative demonstrations of this critical technology to these Industry leaders. This is a significant step toward Phase III commercialization.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Dr. Loren D. Nelson
OPHIR Corporation
10184 West Belleview Avenue, Suite 200
Littleton , CO 80127 - 1762
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
OPHIR Corporation
10184 West Belleview Avenue, Suite 200
Littleton , CO 80127 - 1762
| PROPOSAL NUMBER: | A8.01-8418 (For NASA Use Only - Chron: 013581 ) |
| PHASE-I CONTRACT: | NAS1-02002 |
| PROPOSAL TITLE: | BOUNDARY LAYER PUMPED PROPULSION |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
Advanced Propulsion Inc. proposes a Revolutionary Concept (RevCon) integrated aircraft and propulsion system that provides aircraft drag reduction and propulsion system efficiency increase, thereby improving aircraft fuel efficiency by as much as a factor of two. The key feature is the ducting of a high fraction of the aircraft total boundary layer from distributed airframe inlets to turbofan engine(s) in the rear of the fuselage. This fully integrated, boundary layer pumping engine(s) will provide the sole propulsive thrust for the aircraft. API?s intent is twofold: First, to design the wing and fuselage configurations and boundary layer ingestion features for a very high fraction of laminar flow and greatly reduced parasitic drag. Second, to match the mass flow of the ingested boundary layer, the turbofan engine(s) and the aircraft cruise thrust requirement at the cruise design point to yield an extremely high level of propulsive efficiency.
With reduced fuel loads, aircraft can be smaller, and less costly. With less drag and greater efficiency, aircraft can have higher performance. This integrated aircraft/propulsion technology is applicable to all types and sizes of subsonic airplanes.
POTENTIAL COMMERCIAL APPLICATIONS
7. POTENTIAL COMMERCIAL APPLICATIONS (LIMIT 200 WORDS):
API envisions a global general aviation and transport category airplane market for its revolutionary airplane design. Special sector airplanes are also feasible because the new economy era demands long-range personal transport that can fly an un-refuelled mission range of 8,000 nautical miles with reserves allows global coverage from the United States. The world air cargo market is also expanding at a greater rate than the passenger market and represents and has needs for long range capability that offers time savings.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Gerald Merrill
Advanced Propulsion Inc.
254 West Baseline Road, Suite 104
Tempe , AZ 85282 - 1263
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Advanced Propulsion Inc.
254 West Baseline Road, Suite 104
Tempe , AZ 85282 - 1263
| PROPOSAL NUMBER: | A8.02-8450 (For NASA Use Only - Chron: 013549 ) |
| PHASE-I CONTRACT: | NAS3-02013 |
| PROPOSAL TITLE: | A High Turn-Down Ratio, Low Emissions Combustor for Gas Turbine Engines |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
This proposal describes an innovative, high-efficiency, compact
combustor for lean-premixed, low-emissions gas turbine systems and
responds directly to NASA's request for "Innovative technologies
relating to combustion processes, including fuel injectors, piloting,
flameholding techniques for increased and performance and decreased
emissions" under SBIR topic A8.02. The concept is based on previously
demonstrated means for creating high mixing rate regions using multiple
discrete axial vortices in the flow. This injector-mixer-flameholder
shows promise for emissions reduction by ensuring rapid and complete,
well controlled mixing. Another goal is an axial-vorticity fuel
injection, mixing, and flame stabilization design that passively
controls combustion instability and flashback by making the combustion
region insensitive to axial flow oscillations. During previous work APRI
has demonstrated the ability to stabilize flames in a geometry designed
to provide open three-dimensional separations. In the Phase I effort the
ability to control mixing rates in geometry directly suitable to gas
turbine combustors was demonstrated. Conceptual designs for combustors
based on this technology are presented. The Phase II effort will take
advantage of the axial vorticity mixers and flame stabilizers to
complete the design and test of a lean-premixed
fuel-injector/flame-holder for gas turbine systems.
POTENTIAL COMMERCIAL APPLICATIONS
The axial-vorticity fuel-injector/flame-holder system described in this
proposal is applicable to a wide variety of combustion systems. Aircraft
gas turbines, industrial gas turbines, gaseous waste incinerators, and
other industrial burners can benefit from the high mixing rate and flame
stability characteristics of this design.
NAME AND ADDRESS OF PRINCIPAL INVESTIGATOR
(Name, Organization Name, Mail Address, City/State/Zip)
Thomas H. Sobota, Ph.D.
Advanced Projects Research, Inc.
1925 McKinley Avenue, Suite B
La Verne , CA 91750 - 5800
NAME AND ADDRESS OF OFFEROR
(Firm Name, Mail Address, City/State/Zip)
Advanced Projects Research, Inc.
1925 McKinley Avenue, Suite B
La Verne , CA 91750 - 5800
| PROPOSAL NUMBER: | A8.02-8881 (For NASA Use Only - Chron: 013118 ) |
| PHASE-I CONTRACT: | NAS3-02015 |
| PROPOSAL TITLE: | Integrated Ejector Pump Flow Control for Low-Pressure Turbine |
TECHNICAL ABSTRACT (LIMIT 200 WORDS)
The operation of the low-pressure turbine at cruise conditions produces a Reynolds number significantly below takeoff conditions leading to laminar separation over the blades; consequently, the efficiency of the LP turbine at cruise is significantly below that at takeoff for both military and commercial engines. In the Phase I SBIR Techsburg demonstrated the capability of an innovative flow control technique designed to improve the LP turbine performance leading to a reduction in costs. Flow control was achieved with ejector pumps machined into the blade surface to provide a simple and efficient way of producing blowing and suction. High-pressure supply air from the compressor is injected into the flow as a high momentum jet providing a boundary layer that is resistant to separation, while low momentum fluid in the boundary layer is removed with suction upstream and combined with the supply air to enhan