Thermal control of the MUSES-B spacecraft is achieved by a combination of passive and active techniques. The thermal control subsystem is designed so that it can maintain spacecraft temperature for a wide range of sun angles, during long eclipse, and with a wide variation of internal heat dissipation. A smooth tent-shaped thermal shield is provided for the exposed RCS to avoid multi-reflection and to reduce uncertainty in analysis. Thermal design and its verification has been conducted separately for the main structure, the RCS and the deployable antenna. The adequacy of the thermal mathematical models was verified in a series of thermal model tests. The thermal analysis using the refined mathematical models shows satisfactory performance in orbit.


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    Title :

    Thermal control desiring for the MUSES-B spacecraft


    Additional title:

    Das thermische Konstruktionskonzept des Satelliten MUSES-B


    Contributors:
    Okamoto, A. (author) / Suzuki, H. (author) / Nagashima, K. (author) / Ohnishi, A. (author) / Hirosawa, H. (author)

    Published in:

    Publication date :

    1996


    Size :

    9 Seiten, 12 Bilder, 5 Tabellen, 2 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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