The Galileo mission has been reprogrammed to use a direct earth-Jupiter trajectory with a May 1986 launch date and with arrival at Jupiter occurring in mid-1988. Within the constraints of Shuttle/Centaur launch vehicle capability and total spacecraft mass and performance, optimal broken-plane trajectories are generated, and the region of positive propellant margin in the launch/arrival space is determined. Mission constraints are used to define a launch/arrival strategy. It is also shown that a close flyby of any one of several asteroids or a comet is possible on the interplanetary transfer with minimal impact on mission performance.


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    Title :

    Interplanetary trajectory design for the Galileo mission


    Contributors:

    Conference:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1983 ; Reno, NV


    Publication date :

    1983-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Interplanetary trajectory design for the Galileo mission

    DAMARIO, L. / BYRNES, D. | AIAA | 1983




    Interplanetary Trajectory Optimization with Application to Galileo

    Louis A. DAmario / Dennis V. Byrnes / Richard H. Stanford | AIAA | 1982


    INTERPLANETARY MISSION DESIGN

    American Astronautical Society | British Library Conference Proceedings | 2000