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.
Interplanetary trajectory design for the Galileo mission
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1983 ; Reno, NV
1983-01-01
Conference paper
No indication
English
Interplanetary trajectory design for the Galileo mission
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