NASA SBIR 2018-I Solicitation

Proposal Summary


PROPOSAL NUMBER:
 18-1- H10.01-7402
SUBTOPIC TITLE:
 Advanced Propulsion Systems Ground Test Technology
PROPOSAL TITLE:
 Additive Manufacturing of Integrated Sensor 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
nma.risl.llc@gmail.com
24234 Madison St Torrance, CA 90505 - 6627
(760) 383-1218

Business Official (Name, E-mail, Mail Address, City/State/Zip, Phone)
Mr. Naibing Ma
risl.llc@gmail.com
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 measurement of pressure, temperature, strain and radiation in a high temperature and/or harsh environment to support rocket ground test, RC Integrated Systems LLC (RISL) proposes to develop a novel Additive Manufacturing of Integrated Sensor (AMIS) System, providing accurate simultaneous measurement of multiple parameters including pressure, temperature, and strain in high temperature and/or radiation environment. The AMIS is based on use of novel materials for high-temperature operation and uniquely designed fiber optic sensors. The AMIS sensors can tolerate operating temperatures up to 1800 degrees C and achieve measurement errors within 0.5% for temperature sensors and 0.2% for pressure and strain sensors. In mass production, each additive-manufactured microelectromechanical systems (MEMS) sensor will cost about $10. In Phase I RISL will demonstrate the feasibility of AMIS for in-situ measurement of temperature and strain 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 AMIS will provide for NASA an in situ sensor suite capable of measuring temperature, pressure, and strain in high temperature (up to 1800°C) and/or high radiation environment to enhance proven, state-of-the-art propulsion test facilities. It can be incorporated into Stennis Space Center (SSC) rocket ground test facility to enhance Chemical and Advanced Propulsion technology development and certification. The AMIS system can also be incorporated into SSC’s Nuclear Thermal Propulsion Ground Test Exhaust Capture System for measurement of engine exhaust gas temperature and pressure. This development will support multiple NASA missions including human mission to Mars.

Potential Non-NASA Applications

The AMIS can be used to replace thermocouples that are currently used for turbine engine exhaust gas temperature and pressure measurement.  It can be incorporated into the nuclear power plant for temperature, pressure, and strain monitoring of nuclear reactors to ensure safe operation. It can also be used for monitoring temperature and pressure in coal-fired power plants, natural-gas-based power plants, geothermal plants, as well as other power-generation facilities throughout the nation.


Form Generated on 05/25/2018 11:32:25