Thermal Protection Systems for Space Applications

Award Information
Agency: Department of Defense
Branch: Missile Defense Agency
Contract: F29601-03-C-0076
Agency Tracking Number: 02-0102T
Amount: $1,176,430.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: N/A
Solicitation Number: N/A
Solicitation Year: N/A
Award Year: 2003
Award Start Date (Proposal Award Date): N/A
Award End Date (Contract End Date): N/A
Small Business Information
The Millennium Centre, R.R. 1, Box 100B, Triadelphia, WV, 26059
DUNS: 101582922
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Rick Lucas
 Program Manager
 (304) 547-5800
Business Contact
 Brian Joseph
Title: President
Phone: (304) 547-5800
Research Institution
 210 Fluor Daniel Building, Box 340921
Clemson, SC, 29634
 (864) 656-5628
 Nonprofit college or university
The Missile Defense Agency's (MDA) ballistic missile defense system is made up of a variety of components including land- and sea-based missiles, satellites, and space-based laser, all part of the Theater and National Missiles Defense Systems. Reusablehypersonic and reentry vehicles are being designed to meet Defense Department requirements. Two specific programs, the MDA's Space Based Laser (SBL) and the Space Maneuver Vehicle (SMV) program have requirements for innovative Thermal Protection Systems(TPS). Touchstone Research Laboratory has developed two novel materials. One can be used as a stand alone TPS, Carbon Foam (CFOAM[R]) for environments between 1000 and 3000 degrees F. When combined with the second material, Brazed Aluminum MatrixComposite (BAMC), it provides a sandwich structure combining a structural thermal insulator, carbon foam (with compressive strength of up to 4000 psi) with a high-specific strength metal matrix composite (BAMC), which maintains its strength even above 750degrees F. The innovative lightweight Carbon Foam (CFOAM) and Brazed Aluminum Matrix Composite (BAMC) research will provide a new generation, lightweight, thermally efficient and affordable Thermal Protection System (TPS). It will protect sensitive spacecraftoptical and structural components enabling the thermal subsystems to minimize power consumption. A new TPS system can potentially increase payload fraction as well as provide additional mass margin by increasing propellant mass fraction. Such a systemwould open design space and reduce the risk of future mass growth. The technology will be directly applicable to NASA's on-going and future launch vehicle and space platform programs. It will be of great benefit to the commercial satellite industry.

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

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