SBIR/STTR
High Temperature "Smart" P3 Sensors and Electronics for Distributed Engine Control, Phase I
Project Introduction
Current engine control architectures impose limitations on the insertion of new control capabilities due to weight penalties and reliability issues related to complex wiring harnesses. NASA in collaboration with Air Force Research Lab (AFRL) has been conducting research in developing technologies to enable Distributed Engine Control (DEC) architectures. Realization of such future intelligent engines depends on the development of both hardware and software, including high temperature electronics and sensors to make smart components. NASA is particularly interested in the design and development of these applications for assessing the benefit they bring to the engine system. Compressor discharge pressure measurement has long been a key aspect of turbine engine control to manage stall margin. Given that, there is a need for a high-temperature, smart P3 sensor as a key building block for distributed engine controls. Given the current limitations of high temperature electronics, the business case for smart control elements (sensors and actuators) can be made in the fan/compressor section of the engine. The long-term objective of the proposed effort is to advance high-temperature P3 sensor technology for DEC applications through working with OEM partners and industry working groups to: (1) to iterate the current technology toward DEC formats/functions, (2) advance the digital electronics design/firmware and high temperature electronics, and (3) (through demonstration and stakeholder collaboration) present the viability (technical and business case) of the proposed sensor.
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Anticipated Benefits
Potential NASA Commercial Applications: The proposed sensor directly supports NASA Aeronautics Research Mission Directorate (ARMD) research thrusts including vehicle safety, efficiency and carbon emission reduction. The sensor is also directly applicable to a planetary exploration mission to Venus since a high temperature sensor that does not require cooling will significantly reduce payload weight, volume, and complexity. Space propulsion systems, including chemical rockets, nuclear thermal propulsion, launch and station keeping, all exhibit high temperatures and would benefit from the proposed technology. Energy generation systems such as Stirling engines and fuel cells also have high operational temperatures that could be monitored by the proposed sensor. In situ resource utilization systems utilize high temperatures and pressures and would benefit from the proposed technology. Derivative sensor technology could potentially be applied for sensing conditions in thermal protection systems for alloy and ceramic matrix composite structural components.
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Primary U.S. Work Locations and Key Partners
| Organizations Performing Work | Role | Type | Location |
|---|---|---|---|
Glenn Research Center
(GRC)
|
Lead Organization | NASA Center | Cleveland, OH |
| Sporian Microsystems, Inc. | Supporting Organization | Industry | Lafayette, CO |
Primary U.S. Work Locations
-
Colorado
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Organizational Responsibility
Responsible Mission Directorate:
- Space Technology Mission Directorate (STMD)
Lead Center / Facility:
- Glenn Research Center (GRC)
Responsible Program:
- SBIR/STTR
Project Management
Program Director:
Program Manager:
Principal Investigator:
- Kevin Harsh
Project Duration
Start: Jun 2015
End: Dec 2015
Technology Maturity (TRL)
| Start: | 3 |
| Current: | 4 |
| Estimated End: | 4 |
Applied Research
Development
Demo & Test
Technology Areas
Primary:
- TA 15 Aeronautics
- TA 15.6 Enable Assured Machine Autonomy for Aviation
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