静止卫星小推力多圈转移轨道间接优化  

Indirect Optimization of Low-Thrust Multi-Revolution Orbit Transfers for Geostationary-Orbit Satellites

作　　者：沈红新[1] 李恒年[1] SHEN Hong-xin LI Heng-nian(State Key Laboratory of Astronautic Dynamics, Xi＇an Satellite Control Center, Xi＇an 710043, China)

机构地区：[1]西安卫星测控中心宇航动力学国家重点实验室,西安710043

出　　处：《宇航学报》2017年第10期1041-1047,共7页Journal of Astronautics

基　　金：国家自然科学基金(11702330)

摘　　要：本文研究了电推进平台地球静止(GEO)卫星转移轨道优化问题。在动力学模型中考虑了地球J2项摄动,基于庞特里压金极大值原理(PMP)推导了时间最优变轨控制律及其一阶必要性边界条件,采用推力幅值延拓技术和牛顿下山法对最优控制两点边值问题求解。仿真算例表明本文方法的有效性,相对已有结果性能指标可以提升5%左右。分析了静止卫星小推力多圈时间最优转移轨道要素变化特性,可供工程实际参考。A method for the optimization of geostationary orbit（ GEO） satellite orbit transfer with all-electric propulsion is proposed. The Earth＇s oblateness（ J2） perturbation is included in the dynamic model. The time-optimal control law of the GEO satellites as well as the first order optimality necessary conditions,based on the Pontryagin＇s maximum principle（ PMP）,are deduced. The resulting two-point boundary value problem is solved based on thrust continuation approach and by means of the Newton＇s downhill method. Numerical simulations have demonstrated the effectiveness of the approach proposed,with performance increasing about 5% compared to the existing results. From the numerical results,some characteristics of the time-optimal transfer orbit element changes are drawn,which could provide reference for aerospace engineering.

关 键 词：电推进 地球静止卫星 间接法 两点边值问题 轨道优化 

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]