NASA SBIR 2018-I Solicitation

Proposal Summary

 18-1- Z7.01-7382
 Entry Descent & Landing Sensors for Environment Characterization, Vehicle Performance, and Guidance, Navigation and Control
 Distributed Fiber Optic Sensing System
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
RC Integrated Systems, LLC
24234 Madison Street
Torrance , CA 90505-6627
(760) 383-1218

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Naibing Ma
24234 Madison St Torrance, CA 90505 - 6627
(760) 383-1218

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Naibing Ma
24234 Madison St Torrance, CA 90505 - 6627
(760) 383-1218
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract

To meet the NASA need for high accuracy, light weight, low power fiber optic sensing system for Entry, Descent, and Landing (EDL) instrumentation systems, RC Integrated Systems LLC (RISL) proposes to develop a novel Distributed Fiber Optic Sensing (DFOS) System providing accurate in situ measurement of multiple thermal protection system (TPS) structural, aerothermal, and aerodynamic response parameters including temperature, pressure/strain, and heat flux. The DFOS is based on use of novel materials for high-temperature operation and uniquely designed fiber optic sensors. The DFOS system is capable of simultaneously measuring multiple TPS response parameters (e.g., pressure, strain, temperature, and heat flux) from thousands of sensing locations by emplacing a single optical fiber onto the TPS structure. DFOS will tolerate operating temperatures up to1800 degrees C and achieve measurement errors within +/- 5 degrees C for temperature sensors and +/-1% for pressure sensors. In Phase I RISL will demonstrate the feasibility of DFOS for in-situ measurement of DFOS feasibility by fabricating and testing a technology readiness level (TRL)-4 prototype, with the goal of achieving TRL-6 by the end of Phase II.

Potential NASA Applications

The proposed technology will provide for NASA a distributed and embedded in situ system for measurement of thermal protection system (TPS) temperature, strain, heat flux, and surface pressure with high accuracy and high spatial resolution. The proposed system will provide better traceability from the modeling and design tools to actual performance, because the resultant sensor data can lead to higher-fidelity design tools, improved risk quantification, decreased heat shield mass, and increase in direct payload. The proposed system can be applied to different types TPS materials for planetary aerocapture and entry as well as return to Earth. The proposed technology will directly support future NASA missions.

Potential Non-NASA Applications

The military will benefit from this technology by incorporating the proposed system into the aircraft structural components to monitor, in situ and in real time, potential component failure, to reduce the amount of inspection and testing required, and increase reliability and mission availability. Commercial applications include health monitoring of commercial aircraft structural components. The sensors can also be used for damage detection of oil and gas pipelines. Harsh environment applications of the system include monitoring coal-fired power plants, natural-gas-based power plants, geothermal plants, as well as other power-generation facilities.

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