NASA SBIR 2020-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 20-1- A2.01-4786
SUBTOPIC TITLE:
 Flight Test and Measurement Technologies
PROPOSAL TITLE:
 Distributed Optical Sensing System
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
RC Integrated Systems, LLC
20100 South Western Avenue, Suite A5
Torrance, CA 90501
(760) 383-1218

Principal Investigator (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Mr. Naibing Ma
E-mail:
nma.risl.llc@gmail.com
Address:
20100 South Western Ave, STE A5 Torrance, CA 90501 - 1307
Phone:
(760) 383-1218

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)

Name:
Naibing Ma
E-mail:
nma@rcintegrated.com
Address:
20100 South Western Ave., STE A5 Torrance, CA 90501 - 1307
Phone:
(760) 383-1218
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

To meet the NASA need for fast response, low volume, and minimal intrusion sensing system to enhance the monitoring of test aircraft safety and atmospheric conditions during flight testing, RC Integrated Systems LLC (RISL) proposes to develop a novel Distributed Optical Sensing System (DOSS), capable of providing in situ high resolution measurement of temperature, surface pressure, and strain of aerospace vehicle outer structure during flight test. These data will be used to provide information necessary to safely expand the flight and test envelopes of aerospace vehicles and components. The DOSS is based on use of novel materials for high-temperature operation and uniquely designed fiber optic sensors, capable of simultaneously measuring multiple aerothermal, aerodynamic, and structural response parameters of aerospace vehicles. DOSS sensors can withstand temperatures up to1500 degrees C and achieve measurement resolution of 0.1 degree C for temperature over 1500 degrees C range, one microstrain for strain over 10000 microstrains range, and less than 1 psi for pressure over 3000 psi range. In Phase I RISL will demonstrate the feasibility of DOSS 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 (Limit 1500 characters, approximately 150 words)

The proposed DOSS system will support a variety of flight regimes and vehicle types ranging from low speed, sub-sonic applications and electric propulsion, through transonic and high-speed flight regimes. DOSS can be integration into NASA Aeronautics Research Mission Directorate (ARMD) Integrated Aviation Systems Program (IASP), the Electrified Powertrain Flight Demonstration (EPFD) and Flight Demonstrations and Capabilities (FDC) projects for relevant flight testing. 

Potential Non-NASA Applications (Limit 1500 characters, approximately 150 words)

DOSS can be used for turbine engine exhaust gas temperature and pressure measurement. The military can incorporate DOSS into aircraft engines to monitor component failure, thus to reduce the amount of inspection and testing required, and increase reliability and mission availability. DOE can incorporate DOSS into the nuclear power plant for monitoring of nuclear reactors to ensure safe operation. 

Duration: 6

Form Generated on 06/29/2020 21:06:40