The work carried out on a phase A study of an out-of-ecliptic mission using the Ariane launch vehicle is reported. It comprises a single spacecraft with a model experiment payload similar to payload A of the earlier phase A studies, and uses a Delta Vega orbit to provide an adequate spacecraft mass for injection into the transfer orbit to Jupiter. This feature increases the complexity of the spacecraft by the addition of a 400 N bi-propellant rocket motor and increases the overall mission duration from launch to recrossing the ecliptic plane after solar passage to nearly 6 years. Using May 1983 launch opportunity, it is concluded that a useful payload could be carried which achieves a maximum heliographic latitude of about 70 deg, for a phase C/D industrial development program cost of about 38 MAU at mid 1975 rates.


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    Title :

    Out-of-Ecliptic Using Ariane Launch Vehicle. Volume 1: Executive Summary


    Contributors:
    J. Simpson (author) / J. Howard (author) / P. Braund (author) / B. Pugh (author) / R. Slade (author)

    Publication date :

    1977


    Size :

    59 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English