The configuration of the Viking 75 Spacecraft, which was used in two missions related to the exploration of the planet Mars, is examined and a description of the orbiter propulsion subsystem is provided. The propellants utilized were nitrogen tetroxide and monomethylhydrazine. Gaseous helium was used for pressurization. Orbiter maneuver durations ranged from the 39.4 minute Mars orbit insertion on VO-2, the longest engine firing in space to date, to the 1.7-second station keeping trim on VO-1. Total engine operating time was 2748.2 seconds for VO-1 and 2814.5 seconds for VO-2.


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    Titel :

    In-flight performance of the Viking 75 Orbiter propulsion system


    Beteiligte:
    Schmit, D. D. (Autor:in) / Leeds, M. W. (Autor:in) / Vote, F. C. (Autor:in)

    Kongress:

    Propulsion Conference ; 1977 ; Orlando, FL, US


    Erscheinungsdatum :

    1977-07-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    In-flight performance of the Viking 75 Orbiter propulsion system

    SCHMIT, D. / LEEDS, M. / VOTE, F. | AIAA | 1977


    Long-Life Bipropellant System Demonstration, Viking Orbiter Propulsion System

    D. D. Schmit / J. W. Anderson / F. C. Vote | AIAA | 1981




    Viking Orbiter Stereo Imaging Catalog

    K. R. Blasius / A. V. Vertrone / B. H. Lewis et al. | NTIS | 1982