Trajectory design for an ion drive asteroids rendezvous mission launched into an Ariane geostationary transfer orbit

Details Trajectory design for an ion drive asteroids rendezvous mission launched into an Ariane geostationary transfer orbit Trajectory design for an ion drive asteroids rendezvous mission launched into an Ariane geostationary transfer orbit

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984asdy.confr....p&link_type=abstract

American Institute of Aeronautics and Astronautics and American Astronautical Society, Astrodynamics Conference, Seattle, WA, Au

Astronomy and Astrophysics

Astronomy

Asteroid Missions, Ion Propulsion, Rendezvous Trajectories, Space Rendezvous, Trajectory Optimization, Transfer Orbits, Ariane Launch Vehicle, Feasibility Analysis, Flyby Missions, Space Exploration

Scientific paper

AMSAT has conceived an asteroid rendezvous mission which would consist of an Ariane-launched, 3-axis-stabilized, 350-kg spacecraft utilizing both mercury and solar electric ion propulsion. The spacecraft is to be equipped with a science instrument platform with a mass of approximately 30 to 50 kg. Practically uninterrupted earth departure opportunities are found for targets such as 4 Vesta, 8 Flora, and 19 Fortuna from 1986 through 1988. The 7 to 8 year mission would allow for a second rendezvous of 4 Vesta, and marginal additional fuel would make close flybys of targets feasible. Through the use of parameter optimization techniques, trajectories can be generated and the inclusion of constraints due to spacecraft techology, tour design, and navigation can be facilitated.

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