Two Viking spacecraft, each consisting of a lander capsule coupled to an orbiter, will be launched toward Mars during the summer of 1975. About a year later, the orbiters will go into orbit around Mars and the landers will descend to the surface for 90-day landed missions. The lander must withstand a wide variety of environmental and operational conditions during all phases of the mission, including prelaunch sterilization. On the surface of Mars, the lander internal temperatures must be controlled under widely varying thermal environments and atmospheric conditions. The lander thermal design is based on the maximum use of passive techniques and is integrated into the overall vehicle design and operation. The solutions to the unusual combinations of design problems and a summary of the results of full scale model testing under simulated mission conditions are presented.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Development of the Viking Mars lander thermal control subsystem design


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

    Kongress:

    Thermophysics and Heat Transfer Conference ; 1974 ; Boston, MA


    Erscheinungsdatum :

    1974-07-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Development of the Viking Mars Lander Thermal Control Subsystem Design

    Theodore F. Morey / David N. Gorman | AIAA | 1976


    Mars Viking surface sampler subsystem

    Crouch, D.S. | Tema Archiv | 1977