Flight data from a 15.8 mm OD, 760 mm long, axial-groove, methane cryogenic heat pipe verified successful priming and operation during six min of zero-g time. The nominal power applied to the evaporator was 60-w for the first 60 sec of zero-g time, 14 w for the next 270 sec, and 25 w for the last 20 sec of flight. The heat pipe condenser was mounted into an aluminum heat sink which was cooled to 103 K at launch and increased in temperature to 128 K by the end of the flight. Ground test data obtained for the flight heat pipe, together with theoretical predictions, indicate a zero-g heat transport capability of 3500 to 4000 w-cm in the 100-125 K temperature range.


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    Titel :

    Cryogenic heat pipe experiment - Flight performance onboard a sounding rocket


    Beteiligte:
    Harwell, W. (Autor:in) / Quadrini, J. (Autor:in) / Sherman, A. (Autor:in) / Mcintosh, R. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Thermophysics Conference ; 1975 ; Denver, CO


    Erscheinungsdatum :

    01.05.1975


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




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