多次行星借力的小推力飞行控制策略研究  

Research on flight control strategy for low-thrust multiple gravity assist trajectories

作　　者：田百义 黄美丽[1] 王大轶[1] 张相宇 冯昊[1] 赵峭[1] TIAN Bai-yi;HUANG Mei-li;WANG Da-yi;ZHANG Xiang-yu;FENG Hao;ZHAO Qiao(Institute of Spacecraft System Engineering,Chinese Academy of Space Technology,Beijing 100094,China)

机构地区：[1]中国空间技术研究院,北京空间飞行器总体设计部,北京100094

出　　处：《控制理论与应用》2019年第12期2013-2018,共6页Control Theory & Applications

基　　金：国家自然科学基金项目(61803027);国家杰出青年科学基金项目(61525301)资助。

摘　　要：针对小推力深空探测器采用多次行星借力的飞行控制策略优化问题,文章提出了一种将推进段作为整体与滑行段进行打靶拼接的方法,最大限度地减少了优化设计时的待优化参数个数.首先,文章给出了小推力飞行轨道的间接优化设计模型和基于B平面理论的行星借力模型.随后,建立了给定开关机时序条件下的小推力借力飞行控制策略优化模型;最后,采用遗传算法和序列二次规划算法循环对该模型进行优化求解,并以地球–金星–地球–木星小推力飞行轨道控制策略优化设计为例进行仿真分析,仿真结果验证了优化模型的正确性和有效性,表明本文的研究方法可对小推力多次行星借力飞行的控制策略进行优化设计.A method of patching between propulsion segment and glide segment is presented in this article, to optimize the flight control strategy of low thrust multiple gravity assist trajectories. Firstly, the optimization model of low thrust control strategy and the model of gravity assist are established based on the indirect optimization algorithm and B-plane theory. Secondly, the optimization model of low thrust multiple gravity assist control strategy is established under the given on-off time sequence. Besides, the genetic algorithm(GA) and sequential quadratic programming(SQP) algorithm are used to solve the optimization problem. Finally, the Earth-Venus-Earth-Jupiter low thrust transfer orbit control strategy is optimized as an example, to verify the correctness and effectiveness of the optimization model. It is shown that, the method presented in this paper can be used to optimize the control strategy of low-thrust multiple gravity assist trajectories.

关 键 词：小推力 多次借力 小推力借力 深空探测 轨道转移 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]