嫦娥五号月球轨道交会导引策略设计  

Lunar orbit rendezvous phasing design for Chang’e-5 Mission

作　　者：孟占峰[1] 高珊[1] 盛瑞卿[1] Zhanfeng MENG;Shan GAO;Ruiqing SHENG(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航空学报》2023年第5期237-252,共16页Acta Aeronautica et Astronautica Sinica

基　　金：国家中长期科技发展规划重大专项。

摘　　要：嫦娥五号任务实现了国际首次月球无人轨道交会对接,本文详细介绍了其最终飞控实施所采用的交会导引策略的设计模型、方法和工程实现考虑。讨论了嫦娥五号月球轨道交会任务的工程设计约束和关键参数的确定,提出了一种月球轨道交会的交班点确定方法。提出了一种新的四脉冲交会策略,通过引入径向变轨控制量,固定各次变轨点位置,解决了在月球背面测控遮挡约束下确保各次变轨全过程测控可见的工程难题。针对新四脉冲方案,采用近圆轨道偏差方程提出了一种新的初值求解方法,构造了基于微分修正的精确数值求解算法,并推导了求解所需的状态转移矩阵的解析表达形式。建立了测控约束下的交会导引约束优化模型,获得了测控约束下的最优能量解,并揭示了问题的全局特性规律。给出了所提出方法在嫦娥五号实际任务中的应用,验证了此方法的正确性。To achieve the mission of Chang’e-5 lunar orbit rendezvous,a new 4-impulsive rendezvous phasing scheme is proposed.By using the radial control variable,the argument of latitude of each impulse is constrained,so as to satisfy the constraint of tracking condition.For the new 4-impulse scheme,a new initial guess method is proposed by using the near-circular orbit deviation equation.A high-fidelity numerical solution is constructed using the differential correction algorithm,and the corresponding analytical state transition matrix is derived.The design consideration and results of the key parameters of Chang’e-5 lunar orbit rendezvous mission are discussed.The optimization design model of rendezvous guidance constraint with the constraint of tracking condition is established.The optimal argument of latitude in each impulse is obtained by solving the optimization problem.The global characteristics of constrained optimization problems are also revealed.The operation results of Chang’e-5 show that the proposed strategy can guarantee the constraint of tracking condition,satisfying the flight mission requirements.

关 键 词：嫦娥五号 月球轨道 交会 状态转移矩阵 约束优化 

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]