About one problem of trajectory optimization

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 a...

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Bibliographic Details
Published in:Cosmic research 2008-06, Vol.46 (3), p.233-237
Main Authors: Grigoriev, I. S., Zapletin, M. P.
Format: Article
Language:English
Subjects:
Astronomy
Astrophysics and Astroparticles
Astrophysics and Cosmology
Physics
Physics and Astronomy
Space Exploration and Astronautics
Space Sciences (including Extraterrestrial Physics
Studies
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Summary: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.
ISSN:0010-9525
1608-3075
DOI:10.1134/S0010952508030064