During the summer of 1975, two Viking spacecraft will be launched toward Mars, each consisting of a lander capsule coupled to an orbiter. About a year later, the orbiters will go into orbit around Mars and then the landers will descend to begin operation on the surface of Mars for 90 day missions. This paper describes the thermal control aspects of the lander capsule design and operation. The paper presents the thermal control requirements, the design philosophy and approach to solving these thermal problems, and then a description of the resulting thermal control subsystem design features. It concludes with a summary of the vehicle thermal performance characteristics as determined from both analysis and system tests under simulated thermal environments.


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    Titel :

    Thermal design of the Viking lander capsule


    Beteiligte:
    Tracey, T. R. (Autor:in) / Morey, T. F. (Autor:in) / Gorman, D. N. (Autor:in)

    Kongress:

    Aerospace Sciences Meeting ; 1974 ; Washington, DC


    Erscheinungsdatum :

    1974-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Thermal design of the Viking lander capsule

    TRACEY, T. / MOREY, T. / GORMAN, D. | AIAA | 1974


    Thermal testing of the Viking lander capsule system

    Tracey, T. / Buna, T. | Tema Archiv | 1974



    Viking lander spacecraft battery

    Newell, D. R. | NTRS | 1976


    Viking Lander Spacecraft Battery

    D. R. Newell | NTIS | 1976