应用启迪优化方法的地月平动点轨道转移规划设计  

Heuristic optimization for transfer trajectory to cis-lunar liberation point periodic orbit

作　　者：何管维 袁浩 王杰 吴军[1] HE Guanwei;YUAN Hao;WANG Jie;WU Jun(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410007,China)

机构地区：[1]国防科技大学空天科学学院,长沙410007

出　　处：《航天控制》2025年第1期29-38,共10页Aerospace Control

摘　　要：针对地月平动点轨道多目标任务转移策略开展了研究,设计了一种基于双脉冲模式的转移策略,使航天器能够在近直线晕轨道和远距离逆行轨道之间进行转移。首先在质心会合坐标系下建立航天器轨道动力学模型;然后,开展转移策略总体设计并分析涉及的优化变量,确定目标函数和约束条件,将转移策略设计问题转化为轨迹优化问题;进而,验证遗传算法和粒子群优化算法对于该问题的可行性,求解转移轨迹。研究得到了一种应用遗传算法和粒子群优化算法设计平动点轨道转移策略的数值方法,利用该方法设计了近年来重点关注的近直线晕轨道以及远距离逆行轨道之间的转移轨迹。文章提出的优化方法,在无先验信息的情况下能够有效解决轨道转移优化设计问题,并可应用于多类转移方案。The transfer strategies for multi-objective missions around the Earth-Moon Lagrange points are studied and a two-impulse transfer strategy that allows spacecraft to move between near-rectilinear halo orbits and distant retrograde orbits is designed.Firstly,the spacecraft's orbital dynamics model is established in the synodic frame.Then,the overall design of the transfer strategy is implemented,the relevant optimization variables are analyzed,the objective function and constraints are determined,and the transfer strategy design problem is transfered into a trajectory optimization problem.Furthermore,the feasibility of genetic algorithms and particle swarm optimization algorithms for this specific problem is verified for solving the transfer trajectory. A numerical method is presented through this research byapplying genetic and particle swarm optimization algorithms to transfer strategies design of halo orbits,which focuses on recent interest in near-rectilinear halo orbits and distant retrograde orbits. The proposedoptimization method has ability of effectively resolving the orbital transfer design problem without priorinformation and can be applied to various transfer scenarios.

关 键 词：圆型限制性三体问题 轨道转移 遗传算法 粒子群优化算法 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]