Optimal trajectories for a multiple rendezvous mission to asteroids

Details Optimal trajectories for a multiple rendezvous mission to asteroids Optimal trajectories for a multiple rendezvous mission to asteroids

Oct 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991mont.iafcw....b&link_type=abstract

IAF, International Astronautical Congress, 42nd, Montreal, Canada, Oct. 5-11, 1991. 13 p.

Statistics

Computation

Asteroid Missions, Interplanetary Trajectories, Ion Propulsion, Trajectory Optimization, Boundary Conditions, Boundary Value Problems, Lunar Gravitation, Spacecraft Maneuvers, Swingby Technique

Scientific paper

Optimal trajectories are designed for an ion-driven spacecraft from earth to the asteroid 8 Flora with an intermediate stop at 4 Vesta under the constraints imposed by a low-cost mission scenario. For each set of boundary conditions and constraints, the problem is transformed into a multipoint boundary value problem which is solved by the multiple shooting method. Complete flight trajectories are fully optimized, including a moon swing-by maneuver (with thrusters in operation) and spiraling down to and up from low asteroid orbits. The swing-by maneuver at the moon reduces the transfer time to the first rendezvous target asteroid 4 Vesta by about 9 months. No simplification or 'splitting up' in the computation of the flight trajectories are made.

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