A pumped two-phase system for spacecraft thermal control has been developed which makes use of flight-proven heat pipe technology thus minimizing technical risk. Many iteraction of the initial design were conceived and tested in the process of achieving a true pump-assisted heat pipe design, whereby fluid management at heat-transfer surfaces is controlled solely by capillary forces. Development included the construction of a flight prototype small-scale Brassboard unit and a full-scale Engineering Development Unit, both using ammonia as the working fluid. Testing of these units vertified all aspects of the concept, including system and evaporator/condenser performance. Uniform temperatures were maintained with heat-load biasing from 0 to 6 W/cm2, and transport of over 275 kW-M was demonstrated The system is ready for design refinements leading to end-item production.
Development of the lockheed pumped two-phase thermal bus
Entwicklung des gepumpten Zweiphasen Thermal Bus von Lockheed
AIAA-Papers ; Jun ; 1-8
1987
8 Seiten, 19 Bilder, 1 Quelle
Conference paper
English
Development of the Lockheed pumped two-phase thermal bus
AIAA | 1987
|Engineering Index Backfile | 1928
Engineering Index Backfile | 1928
Engineering Index Backfile | 1928
LOCKHEED Constitution DEVELOPMENT STORY
SAE Technical Papers | 1950
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