Review of thermal design of ISIS `A' satellite (International Satellites for Ionospheric Studies); design conditions dictated by details of structure, orbit mission and `on board' temperature limits and payload power dissipation are considered which showed that `passive' thermal control of spacecraft was feasible; computer programmed multi-node heat balance analysis have been developed and used to predict spacecraft flight temperatures and evaluate design parameters; scope of thermal vacuum test program required to establish design integrity is outlined.


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    Titel :

    Thermal design of ISIS `A' spacecraft


    Weitere Titelangaben:

    Can Aeronatuics Space J


    Beteiligte:
    Gray, G.G. (Autor:in) / Jurewicz, L.S. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Thermal design of the ISIS ''A'' spacecraft.

    Gray, G. G. / Jurewicz, L. S. | NTRS | 1966


    Isis-a Spacecraft Magnetic Tests

    J. C. Boyle | NTIS | 1969


    Isis-B Spacecraft Magnetic Tests

    J. C. Boyle | NTIS | 1972


    ISIS-B spacecraft magnetic tests

    Boyle, J. C. | NTRS | 1972


    ISIS-A spacecraft magnetic tests

    Boyle, J. C. | NTRS | 1969