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
Amount:
$49,854.00
Award Year:
1985
Program:
SBIR
Phase:
Phase I
Contract:
n/a
Award Id:
2783
Agency Tracking Number:
2783
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
21119 Superior St, Chatsworth, CA, 91311
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
n/a
Principal Investigator:
TIMOTHY A LOFTIN
PRINCIPAL INVESTIGATOR
() -
Business Contact:
() -
Research Institute:
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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