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Nanostructured Ablative Thermal Protection System

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-14-C-0227
Agency Tracking Number: N141-080-0686
Amount: $80,000.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: N141-080
Solicitation Number: 2014.1
Timeline
Solicitation Year: 2014
Award Year: 2014
Award Start Date (Proposal Award Date): 2014-05-23
Award End Date (Contract End Date): 2014-11-24
Small Business Information
12345 W. 52nd Ave.
Wheat Ridge, CO 80033-1916
United States
DUNS: 181947730
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Michael Diener
 Senior Chemist
 (303) 940-2314
 mikee@tda.com
Business Contact
 John Wright
Title: Chief Technology Officer
Phone: (303) 940-2300
Email: jdwright@tda.com
Research Institution
 Stub
Abstract

Ablative thermal protection system (TPS) materials are widely used in spacecraft and missiles that re-enter the atmosphere. Since they constitute a significant portion of the re-entry body"s mass, improving their performance could greatly reduce mission cost or increase payload. The ablative TPS in the Trident reentry vehicle is based on a char-forming composite of woven carbon fibers and phenolic resin. However, recent advances in carbon materials allow for innovative structures that make better use of the ablator"s weight and volume. We are proposing to develop an altered carbon structure for phenolic-impregnated ablators that takes advantage of modern carbon materials, thereby delivering performance increases with minimal technical risk. The newer carbons will increase the mechanical stability of the ablator without increasing its density or thermal conductivity. Our proposed manufacturing process will also enable three-dimensional control over the ablator"s structure, realizing additional performance benefits.

* Information listed above is at the time of submission. *

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