基于微分对策的卫星弹道拦截混合优化方法

W. Wu, J. Chen, J. Liu
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引用次数: 0

摘要

本研究针对目标航天器能够使用连续量级受限推力进行机动的卫星拦截情况进行轨道设计和优化。为了设计一种远程连续推力拦截轨道,构造了具有J2摄动的两颗卫星的轨道运动方程。该问题被认为是微分博弈论中典型的追逃问题;利用边界约束条件和包含时间和燃料消耗的性能指标函数,导出了双侧最优对应的鞍点解,并将该追逃问题转化为两点边值问题。提出了一种采用遗传算法和序列二次规划的混合优化方法来获得最优控制策略。仿真结果表明,所提出的模型和算法是可行的。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
A hybrid optimisation method for intercepting satellite trajectory based on differential game
This study addresses orbit design and optimisation for the situation of satellite interception in which the target spacecraft is capable of manoeuvring using continuous magnitude restricted thrust. For the purpose of designing a long-range continuous thrust interception orbit, the orbit motion equations of two satellites with J2 perturbation are constructed. This problem is assumed to be a typical pursuit-evasion problem in differential game theory; using boundary constraint conditions and a performance index function that includes time and fuel consumption, the saddle point solution corresponding to the bilateral optimal is derived, and then this pursuit-evasion problem is transformed into a two-point boundary value problem. A hybrid optimisation method using a genetic algorithm (GA) and sequential quadratic programming (SQP) is derived to obtain the optimal control strategy. The proposed model and algorithm are proved to be feasible for the given simulation cases.
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