Application of Semi-Direct Collocation Method for Solving Pursuit-Evasion Problems of Spacecraft

被引：0

作者：

Hao Z.-W. ^{[1
]}

Sun S.-T. ^{[1
]}

Zhang Q.-H. ^{[1
]}

Chen Y. ^{[2
]}

机构：

[1] Department of Astronautical Science and Mechanics, Harbin Institute of Technology, Harbin

[2] Beijing Institute of Control Engineering, Beijing

来源：

Yuhang Xuebao/Journal of Astronautics | 2019年 / 40卷 / 06期

关键词：

Differential game; Optimal strategy; Pursuit-evasion problem of spacecraft; Semi-direct collocation method; Two-point boundary-value problem;

D O I：

10.3873/j.issn.1000-1328.2019.06.003

中图分类号：

学科分类号：

摘要：

The semi-direct collocation method is adopted for solving the pursuit-evasion problem with fixed time-horizon. A new numerical way to solve the optimal control strategies of the pursuit and evasion spacecraft is proposed such that a two-point boundary value problem is not necessary to be solved. Under the assumption of the continuous low-thrust, the procedure solving such a pursuit-evasion problem is given with the payoff of the terminal distance of two spacecraft. In such a numerical method, the differential game is reduced to an optimal control problem according to the semi-transformation. Then, by the Gauss-Lobbato collocation method the optimal control problem is reduced to a nonlinear programming problem which is solved by the sequential quadratic programming method. Such a semi-direct collocation method does not need to solve the necessary condition (a two-point boundary value problem) for the optimal strategies of the differential games, and it is numerically stable. The numerical simulation result shows the optimal control strategies and the associated pursuit-evasion trajectory for a pursuit-evasion problem of spacecraft. © 2019, Editorial Dept. of JA. All right reserved.

引用

页码：628 / 635

页数：7

共 13 条

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