A flight experiment of a mechanically pumped two-phase ammonia thermal control system, incorporating a number of new component designs, has been assembled and tested in a 1-g environment. Additional micro-gravity tests are planned on the Space Shuttle when Shuttle flights are resumed. The primary purpose of this experiment is to evaluate the operation of a mechanically pumped two-phase ammonia system, with emphasis on determining the performance of an evaporative Two-Phase Mounting Plate. The experiment also evaluates the performance of other specially designed components, such as the two-phase reservoir for temperature control, condensing radiator/heat sink, spiral tube boiler, and pressure drop experiment. The 1-g tests have shown that start-up of the two-phase experiment is easily accomplished with only a partial fill of ammonia. The experiment maintained a constant mounting plate temperature without flow rate controls over a very wide range of heat loads, flow rates, inlet flow conditions and exit qualities. The tests also showed the successful operation of the mounting plate in the heat sharing condensing mode.


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    Title :

    Design and test of a mechanically pumped two-phase thermal control flight experiment


    Additional title:

    Entwicklung und Erprobung eines Flugexperiments mit einem zweiphasigen thermischen Regelsystem mit mechanischer Foerderpumpe


    Contributors:
    Grote, M.G. (author) / Stark, J.A. (author) / Butler, C.D. (author) / McIntosh, R. (author)

    Published in:

    AIAA-Papers ; Jun ; 1-11


    Publication date :

    1987


    Size :

    11 Seiten, 22 Bilder, 3 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English






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