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, unheated 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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    Titel :

    A pumped two-phase cooling system for spacecraft


    Weitere Titelangaben:

    Ein pumpendes Zweiphasenkuehlsystem fuer Raumschiffe


    Beteiligte:
    Ollendorf, S. (Autor:in) / Costello, F.A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1983


    Format / Umfang :

    7 Seiten, 6 Bilder, 4 Tabellen, 3 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    A Pumped Two-Phase Cooling System for Spacecraft

    Costello, F. A. / Ollendorf, S. | SAE Technical Papers | 1983


    A SINDA Modeling Technique for Pumped Two-Phase Spacecraft Cooling Systems

    Costello, F. A. / Ollendorf, S. | SAE Technical Papers | 1984



    Mechanical Pumped Cooling Loop for Spacecraft Thermal Control

    Birur, Gajanana C. / Gram, Marsh B. / Bhandari, Pradeep | SAE Technical Papers | 1996


    Micro/nano spacecraft thermal control using a MEMS-based pumped liquid cooling system

    Birur, G.C. / Waniewski Sur, T. / Paris, A.D. et al. | Tema Archiv | 2001