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.


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    Title :

    Development of the lockheed pumped two-phase thermal bus


    Additional title:

    Entwicklung des gepumpten Zweiphasen Thermal Bus von Lockheed


    Contributors:
    Homes, H.R. (author) / Goepp, J.W. (author) / Hewitt.H.W. (author)

    Published in:

    AIAA-Papers ; Jun ; 1-8


    Publication date :

    1987


    Size :

    8 Seiten, 19 Bilder, 1 Quelle


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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