MOST SPACECRAFT, PARTICULARLY MANNED VEHICLES, HAVE DIVERSIFIED POWER REQUIREMENTS NECESSITATING A VARIETY OF THERMAL-CONTROL CAPABILITEIS FOR BOTH PRIMARY SYSTEMS AND CONTINGENCY OPERATIONS.

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: N/A
Agency Tracking Number: 2783
Amount: $49,854.00
Phase: Phase I
Program: SBIR
Awards Year: 1985
Solicitation Year: N/A
Solicitation Topic Code: N/A
Solicitation Number: N/A
Small Business Information
21119 Superior St, Chatsworth, CA, 91311
DUNS: N/A
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 TIMOTHY A LOFTIN
 PRINCIPAL INVESTIGATOR
 () -
Business Contact
Phone: () -
Research Institution
N/A
Abstract
MOST SPACECRAFT, PARTICULARLY MANNED VEHICLES, HAVE DIVERSIFIED POWER REQUIREMENTS NECESSITATING A VARIETY OF THERMAL-CONTROL CAPABILITEIS FOR BOTH PRIMARY SYSTEMS AND CONTINGENCY OPERATIONS. TO ACCOMPLISH THESE REQUIREMENTS, HEAT DISSIPATION IN THE SPACE ENVIRONMENT (AND CONTROL IN MOVING THE HEAT LOADS) FROM THE SOURCES TO RADIATIVE OR WASTE-HEAT AREAS MUST BE ACCOMPLISHED RELIABLY AND SIMPLY, WHILE MAINTAINING STRUCTURAL EFFICIENCY. THIS TASK WILL BE DEMONSTRATED BY USING COMPOSITE MATERIALS AND PROCEDURES WITH HIGH-CONDUCTIVITY PITCH-GRAPHITE TOW REINFORCEMENT IN EITHER COPPER-OR ALUMINUM-MATRIX MATERIAL FOR SIMPLE RADIATOR AND HEAT-PIPE APPLICATIONS. THESE COMPOSITE MATERIALS WILL ALSO HAVE LOWER DENSITY AND HIGHER STIFFNESS AND STRENGTH THAN THE UNREINFORCED METALS, AND WILL HAVE SHOWEN "HEAT-PIPING" POTENTIAL.

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

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