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

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.