%A DUAN Chuanhui, REN Lixin, CHANG Yajie, BAI Qian, AN Ran, HUANG Yusong
%T All electric propulsion satellite trajectory optimization by homotopic approach
%0 Journal Article
%D 2020
%J Chinese Space Science and Technology
%R 10.16708/j.cnki.1000-758X.2020.0018
%P 42-
%V 40
%N 2
%U {http://zgkj.cast.cn/CN/abstract/article_11178.shtml}
%8 2020-04-25
%X The orbit injection of allelectric propulsion satellite is a typical low thrust multirevolution orbit optimal problem. Due to the small acceleration and the large number of revolutions, it is difficult to solve the optimal theoretical solution. In order to solve this problem, the indirect method model of allelectric propulsion satellite orbit optimization was established by using the optimal control theory, and the problem of the orbital optimization was transformed into the twopoint boundary value problem which can be solved by guessing the initial costate variable. A large thrust problem was solved by combining the evolutionary algorithm and the sequential quadratic programming. With the help of homotopic approach, the small thrust problem was solved by gradually reducing the thrust. The simulation shows that the thrust homotopic method can effectively solve the trajectory optimal of geostationary allelectric propulsion satellites with up to hundreds of revolutions by dozens of thrust reductions.