The Institute of Space and Astronautical Science report. S.P. : Proceedings of the Symposium on Mechanics for Space Flight
巻
1
ページ
87 - 102
発行年
1983-03
抄録（英）
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.
Optimization of Low Thrust Trajectories for Collinear Largrange Point Mission
SA0033407.pdf
(676.02KB)
