Optimization of Low Thrust Trajectories for Collinear Largrange Point Mission

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概要

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• Two kinds of optimization problems on low thrust transfer trajectories are discussed. One is a transfer from earth parking orbit to Sun-Earth interior libration point L_1.So-called J-minimum trajectories are obtained for this case. It is shown that, in spite of some injection error, spececraft can reach L_1 by optimizing low thrust programs. The other problem treated in this paper pertains to a transfer between collinear Lagrange points, L_1 and L_2,of Sun-Earth system. In this case, two types of low thrust, that is, power-constant and thrust-constant trajectories are studied. In the former case, J-minimum trajectories are obtained, and, in the latter, fuel optimum trajectories with a single coasting arc were sought including optimal steering programs as a function of total mission time. Computational results show that spacecraft can travel between two points within a mission time that stands comparison with high thrust impulsive transfer.

• 宇宙航空研究開発機構の論文

著者

• Nozue Tatsuhiro

  Totsuka Works Hitachi Ltd.

関連論文

• Optimization of Low Thrust Trajectories for Collinear Largrange Point Mission

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