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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    Title :

    Cryogenic heat pipe experiment - Flight performance onboard a sounding rocket


    Contributors:
    Harwell, W. (author) / Quadrini, J. (author) / Sherman, A. (author) / Mcintosh, R. (author)

    Conference:

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


    Publication date :

    1975-05-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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