Thermal Protection System (TPS) for Agressive Reentry Trajectories of Space Vehicles

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9453-04-M-0119
Agency Tracking Number: F041-031-2642
Amount: $99,993.00
Phase: Phase I
Program: SBIR
Awards Year: 2004
Solicitation Year: 2004
Solicitation Topic Code: AF04-031
Solicitation Number: 2004.1
Small Business Information
24112 Rockwell drive, Euclid, OH, 44117
DUNS: 175863463
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Andrew Sherman
 Chief Scientist
 (216) 404-0053
 ajsherman@powdermetinc.com
Business Contact
 Larry Walley
Title: CFO
Phone: (216) 404-0053
Email: elwalley@powdermetinc.com
Research Institution
N/A
Abstract
Structural C foam lightweight heat shield sandwich panels for use in a next-generation, high-performance thermal protection systems have been previously tested at NASA Ames Research Center under the pullout and glide portions of a simulated extended-range reentry trajectory. Outstanding performance has been demonstrated, with no ablation of the heated surface to heat fluxes of 150-450 Btu/ft2xsec and durations of 255 seconds using a SiC composite non-ablative coating on a lightweight structure. Unfortunately, pore size and density control of these materials is currently inadequate, and facesheet bonding and water adsorption resulted in reliability issues and areas for improvement. The proposed low-cost, lightweight thermal protection system will utilize a SiC composite coating as the hot side ablation resistant coating, deposited directly on low thermal conductivity carbon and/or glassy silicon carbo-nitride foam, yielding a final areal density of »1.0-1.2 lb/ft2. The innovation to be demonstrated in the proposed program is the integral production of a castable, rigid, microcellular carbo-nitride foam structure having optimizable thermal and mechanical properties which can be coated directly to a SiC composite ablation resistant coating system.

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

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