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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Thermal design of ISIS `A' spacecraft


    Additional title:

    Can Aeronatuics Space J


    Contributors:
    Gray, G.G. (author) / Jurewicz, L.S. (author)

    Published in:

    Publication date :

    1966


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    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-A spacecraft magnetic tests

    Boyle, J. C. | NTRS | 1969


    ISIS-B spacecraft magnetic tests

    Boyle, J. C. | NTRS | 1972