The technical aspects of the GEOS 3 which is to be launched on Ariane in tandem with another spacecraft by 1983 are discussed. Four distinct mission options are investigated and the feasibility of each option is discussed. The options are: a near polar lunar orbiter; a lunar orbiter with a transfer trajectory similar to that of option one; an operational orbit with the apogee lying about a lunar distance in the opposite direction to the sun; and the exploration of the far reaches of the magnetotail by orbiting the L2 point of the Earth-Sun system. Proposed configurations are described, as well as the sensor options for all missions. The rate of scientific return and other parameters used to compare mission effectiveness are discussed.


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    Title :

    GEOS 3. Volume 1: Executive Summary


    Contributors:
    T. Kilvington (author) / P. D. Matthews (author) / P. Vangasse (author) / P. Braund (author) / T. Morley (author)

    Publication date :

    1979


    Size :

    181 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English