Abstract The optimization problem for trajectories of spacecraft flight from the Earth to an asteroid is considered in this paper. The flight is realized in the central Newtonian gravitational field of the Sun with a possibility of gravitational maneuvers near planets. Perturbation maneuvers are taken into account using the method of point area of action with a limitation on the flyby altitude. The spacecraft is controlled by changing the value and direction of the engine thrust. The problem is solved taking into account constraints on the launch time, flight duration, and minimum distance to the Sun.
About one problem of trajectory optimization
Cosmic Research ; 46 , 3 ; 233-237
2008-06-01
5 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
About one problem of trajectory optimization
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