NASA SBIR 2022-I Solicitation

Proposal Summary

Proposal Information

Proposal Number:
22-1- H10.01-1879
Subtopic Title:
Advanced Propulsion Systems Ground Test Technology
Proposal Title:
Non-Intrusive Cryogenic Flowmeter for Existing Piping Infrastructure

Small Business Concern

Luna Innovations, Inc.
301 1st Street Southwest, Suite 200, Roanoke, VA 24011
(540) 769-8400                                                                                                                                                                                

Principal Investigator:

Dr. Andrew Boulanger PhD
3155 State Street, VA 24060 - 6604
(540) 557-5889                                                                                                                                                                                

Business Official:

Maggie Hudson
301 1st Street Southwest, Suite 200, VA 24016 - 1921
(434) 483-4254                                                                                                                                                                                

Summary Details:

Estimated Technology Readiness Level (TRL) :                                                                                                                                                          
Begin: 3
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words):

Rocket propulsion test facilities and test articles are highly instrumented to enable a comprehensive analysis of performance and to ensure propulsion system risks are mitigated for spaceflight. NASA desires to advance propulsion ground test technologies to minimize test program time, cost, and risk while meeting safety requirements. To address this challenge, Luna Innovations, in collaboration with National Technical Systems, will develop a non-intrusive cryogenic fluid flow meter for existing piping infrastructure at rocket engine test facilities. The system uses a fiber optic cable attached to a pipe wall to measure the flow induced vibrations distributed along a section of piping. The implementation is non-intrusive and does not contain any electrical components making it inherently safe and robust for rocket engine fuel flows. The system will provide high fidelity flow rate measurements with low initial and operational costs.

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

A cryogenic flow meter will directly support liquid rocket propulsion development. A variety of systems exist that use liquid oxygen to combust with a variety of fuels including liquid hydrogen, kerosene, or liquid methane. In addition, the technology can be used in monitoring flow rates and piping health in space station components. Aero-propulsion applications would benefit from improved engine performance and structural health monitoring while eliminating heavier traditional sensors.

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

The automotive and commercial aircraft industry can use the sensing technology in critical piping to detect the onset of hardware failure. Flow sensing in high pressure and extreme temperature fluid systems in nuclear power, oil and gas, and industrial applications can be used to optimize processes and monitor hardware failure in remote or inaccessible locations.

Duration:     6

Form Generated on 05/25/2022 15:45:05