A pumped, two-phase heat-transport system is being developed for possible use for temperature control of scientific instruments on future NASA missions. As compared to a single-phase system, this two-phase system can maintain tighter temperature control with less pumping power. A laboratory model of the system has been built and tested. The measured heat transfer coefficients were approximately the same as in heat pipes, 220 Btu/hr-ft2-F, as compared to 25 Btu/hr-ft2-F for single-phase liquid flow. Heat sharing between experiments has been demonstrated wherein vapor generated in the cold plate of an active experiment was condensed in a cold, unhealed experiment. System stability has been observed. However, additional development is needed. The use of non-azeotropic mixtures of coolants appears especially promising as a simple way to determine exit quality and thus control the flow rates to prevent dryout.


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    Title :

    A Pumped Two-Phase Cooling System for Spacecraft


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    Intersociety Conference on Environmental Systems ; 1983



    Publication date :

    1983-07-11




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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