Galileo 1989 VEEGA trajectory design

Details Galileo 1989 VEEGA trajectory design Galileo 1989 VEEGA trajectory design

Sep 1989

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1989jansc..37..281d&link_type=abstract

Journal of the Astronautical Sciences (ISSN 0021-9142), vol. 37, July-Sept. 1989, p. 281-306.

Computer Science

Performance

1

Astrodynamics, Earth-Venus Trajectories, Flyby Missions, Galileo Project, Interplanetary Trajectories, Trajectory Analysis, Ballistic Trajectories, Escape Velocity, Launch Windows, Mission Planning, Spacecraft Maneuvers, Trajectory Optimization

Scientific paper

The new baseline for the Galileo Mission is a 1989 Venus-earth-earth gravity-assist (VEEGA) trajectory, which utilizes three gravity-assist planetary flybys in order to reduce launch energy requirements significantly compared to other earth-Jupiter transfer modes. The launch period occurs during October-November 1989. The total flight time is about 6 years, with November 1995 as the most likely choice for arrival at Jupiter. Optimal 1989 VEEGA trajectories have been generated for a wide range of earth launch dates and Jupiter arrival dates. Launch/arrival space contour plots are presented for various trajectory parameters, including propellant margin, which is used to measure mission performance. The accessible region of the launch/arrival space is defined by propellant margin and launch energy constraints; the available launch period is approximately 1.5 months long.

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