The spin-stabilized INTELSAT VI spacecraft bus is described, including overall design requirements and individual subsystems. The satellite weighs approximately 4500 kg at launch, has a beginning-of-life mass of 2570 kg, and an end-of-life dry mass of 1905 kg. It is composed of spun and despun sections connected by a bearing and power transfer assembly. The despun section structure supports the communications payload (repeater and antennas) and provides the command and telemetry and thermal control functions. The spun section includes the attitude control, power, propulsion, and thermal subsystems. Deployable appendages, including antennas and a telescoping solar panel, are implemented by multiple mechanisms.


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    Titel :

    INTELSAT VI spacecraft bus design


    Weitere Titelangaben:

    Design des Intelsat VI Raumfahrtbusses


    Beteiligte:
    Dest, L.R. (Autor:in) / Bouchez, J.P. (Autor:in) / Serafini, V.R. (Autor:in) / Schavietello, M. (Autor:in) / Volkert, K.J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1991


    Format / Umfang :

    51 Seiten, 6 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch




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    HOEBER, C. F. / BARBERIS, N. J. | AIAA | 1983


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    Parker, R.D. / Hayden, J.H. / Neel, W.O. et al. | Tema Archiv | 1984


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