NASA SBIR 2020-I Solicitation

Proposal Summary

 20-1- H5.02-5399
 Hot Structure Technology for Aerospace Vehicles
 Rapid Manufacturing of C-C Composites for Thermal Management
SMALL BUSINESS CONCERN (Firm Name, Mail Address, City/State/Zip, Phone)
TDA Research, Inc.
12345 West 52nd Avenue
Wheat Ridge, CO 80033
(303) 422-7819

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

Michael Diener
12345 West 52nd Avenue Wheat Ridge, CO 80033 - 1916
(303) 422-7819

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

Mr. John Wright
12345 West 52nd Avenue Wheat Ridge, CO 80033 - 1916
(303) 940-2300
Estimated Technology Readiness Level (TRL) :
Begin: 2
End: 4
Technical Abstract (Limit 2000 characters, approximately 200 words)

Carbon-carbon composites (C/C) are currently used as hot structures in a variety of extreme environments encountered during hypersonic flight, rocket launch and atmospheric entry, descent and landing. Their use is limited by their expensive and time-consuming manufacturing process. Delivery times of over six months from order placement are common, a result of the long manufacturing process and the limited number of suppliers. With the domestic need for C/C parts increasing, TDA believes that there is a currently an outstanding opportunity to enter the C/C manufacturing market. We have previously developed a process for economical manufacture of a non-graphitizing resin with an exceedingly high char yield. We now propose to use our demonstrated expertise in carbon manufacturing and commercialization to properly formulate and then utilize our resin to make C/C in days to weeks, instead of months. TDA has therefore proposed a process that eliminates multiple densification cycles while arriving at the same density of the finished product, with equivalent mechanical and thermal properties.

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

Our rapid C/C manufacturing process would be used for hot structures for a variety of propulsion systems, including those used for in-space, Lunar/Mars ascent/descent, separation/attitude control, nuclear thermal, and upper stage rocket engines (including the Space Launch System's). Improved hot structures, as enabled by our technology, reduce vehicle weight and/or reusability in many exploration and sample return missions. Our process shortens development and procurement schedules, providing cost savings to all programs utilizing our C/C.

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

The Air Force, Navy, Army, and Missile Defense Agency hypersonics programs would benefit from rapid C/C manufacturing, since C/C hot structures are used as acreage panels and in the combustors. The Air Force would apply the proposed technology to their Evolved Expendable Launch Vehicle (EELV) and ballistic missile programs. C/C parts are also of interest to gas turbine manufacturers.

Duration: 6

Form Generated on 06/29/2020 21:08:16