The thermal design strategy is discussed as it relates to the production of up to 34 identical small satellites in a relatively short period of time. Tight production and launch schedules and the need to design for low mass, risk, and cost presented a design challenge for all disciplines. A specific arrangement of passive thermal control features, including ITO-coated AgTef covered structure radiators, MLI, and software controlled heaters established a robust design. Thermal modeling of the bus and unique antenna are presented including a comparison between the predicted and required component temperature ranges. Also described are the primary mission objective, the spacecraft configuration, requirements and design drivers, mission environments, and design parameters.


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    Titel :

    Thermal Design of the ORBCOMM Constellation Spacecraft


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    DeMauro, Frank (Autor:in) / Ducas, William (Autor:in)

    Kongress:

    International Conference On Environmental Systems ; 1996



    Erscheinungsdatum :

    01.07.1996




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




    Thermal Design of the ORBCOMM Constellation Spacecraft

    DeMauro, F. / Ducas, W. / SAE | British Library Conference Proceedings | 1996


    Mission Design of the ORBCOMM Constellation

    Evans, M. J. / Maclay, T. J. / International Astronautical Federation | British Library Conference Proceedings | 1998


    Debris Considerations for the Orbcomm Constellation

    Maclay, T. D. / Evans, M. / American Astronautical Society | British Library Conference Proceedings | 1997


    The ORBCOMM System

    Deckett, M. / Centre National d'Etudes Spatiales / European Space Agency | British Library Conference Proceedings | 1993


    ORBCOMM Global Data And Messaging

    Kelly, R. W. / Radio Technical Commission for Maritime Services | British Library Conference Proceedings | 1998