基于脉冲初值的小推力转移轨道优化研究  

Study on Low-Thrust Transfer Trajectory Optimization Based on Impulse Initial Value

作　　者：王旭生 施伟璜[1,2] 王伟 彭玉明[1,2] WANG Xusheng;SHI Weihuang;WANG Wei;PENG Yuming(Shanghai Institute of Satellite Engineering, Shanghai 201109, China;Shanghai Key Laboratory of Deep Space Exploration Technology, Shanghai 201109, China)

机构地区：[1]上海卫星工程研究所,上海201109 [2]上海市深空探测技术重点实验室,上海201109

出　　处：《上海航天》2019年第1期53-58,共6页Aerospace Shanghai

基　　金：上海市科委科研计划项目(16DZ1120300)

摘　　要：针对小推力转移轨道优化过程往往忽略初值多样性的现状,研究了基于不同脉冲初值的小推力转移轨道优化问题。基于直接法的离散思想建立了小推力转移轨道优化模型,提出了基于粒子群和序列二次规划的组合优化算法,以地球1∶1共振近地小行星2016HO3交会任务为例,将3种典型的脉冲轨道作为初值设计了燃料最优小推力转移轨道。仿真结果表明:3种初值轨道优化得到了2个小推力转移发射窗口,两者燃料消耗差距不超过6%。不同的初值对小推力轨道的整体性能指标影响较小,但开关机时刻和推力方向的变化会产生较大差异,从而得到不同的最优控制曲线。Considering the fact that the diversity of initial values is often neglected in the optimization process of the low-thrust transfer trajectory, the low-thrust transfer trajectory optimization with different initial impulse values is studied in this paper. Firstly, a low-thrust transfer trajectory optimization model based on the direct method is established. Then, a combinatorial optimization algorithm based on particle swarm optimization and sequential quadratic programming is proposed. Finally, the asteroid 2016 HO3 rendezvous mission is selected as a simulation example, and the optimization results of the low-thrust transfer orbit are analyzed with single-revolution double-pulse, triple-pulse and multi-revolution double-pulse as initial values. The results show that two launch windows are obtained from three initial values, with the fuel consumption gap of less than 6%. Different initial value inputs will cause large differences in switch time and the change of thrust direction, but only a subtle distinction in overall performance indexes, thus different optimal control curves can be obtained.

关 键 词：小行星探测 小推力轨道优化 燃料最优 脉冲初值 粒子群优化 序列二次规划算法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]