基于改进遗传算法的有限推力远程导引变轨策略  

Finite Thrust Remote Guided Orbital Strategy Based on Improved Genetic Algorithm

作　　者：刘俊尧 贾建芳 李文强[2] 宋锦武 LIU Jun-yao;JIA Jian-fang;LI Wen-qiang;SONG Jin-wu(School of Electrical and Control Engineering,North University of China,Taiyuan 030051,China;School of Information and Communication,North University of China,Taiyuan 030051,China;Guangzhou GRG Metrology&Test Co.Ltd.,Guangzhou 510656,China)

机构地区：[1]中北大学电气与控制工程学院,山西太原030051 [2]中北大学信息与通信工程学院,山西太原030051 [3]广州广电计量检测股份有限公司,广东广州510656

出　　处：《中北大学学报（自然科学版）》2020年第3期220-225,共6页Journal of North University of China(Natural Science Edition)

基　　金：国家自然科学基金资助项目(61573250);山西省青年自然科学基金资助项目(201801D221208);山西省青年自然科学基金资助项目(201801D121159)。

摘　　要：航天器在轨道转移过程中存在推力弧段,与脉冲轨道转移相比,有限推力轨道转移能够反映航天器在真实环境中的工作状态.本文采用改进遗传算法求解远程轨道能量最优的多脉冲变轨方案,在脉冲点处将脉冲量转换为推力弧段上的有限推力,实现了多脉冲机动远程导引向有限推力下远程导引变轨的转换,并对有限推力变轨方案速度增量方向进行修正,修正后变轨方案精度显著提高,与目标轨道相对位置误差大幅减小.The spacecraft has a thrust arc during the orbital transfer process. Compared with pulsed orbital transfer, the limited thrust orbital transfer can reflect the working state of the spacecraft in the real environment. An improved genetic algorithm is used to solve the multi-pulse trajectory optimization solution with optimal long-range orbit energy. The pulse amount is converted to the limited thrust on the thrust arc at the pulse point, and then orbital conversion from multi-pulse motorized remote guide to finite thrust remote guide is realized. Orbit conversion, and the direction of speed increase of the limited thrust orbiting scheme is modified. After the correction, the accuracy of the orbiting scheme is significantly improved, and the relative position error with the target track is greatly reduced.

关 键 词：变轨方案 有限推力 遗传算法 轨道修正 燃料最优 

分 类 号：V448[航空宇航科学与技术—飞行器设计]