基于改进多圆锥截线的月地返回轨道快速设计方法  

Fast Moon-to-Earth return orbit design based on improved multi-conic method

作　　者：杨路易 李海阳[1] 张进[1] 周晚萌 陆林 YANG Luyi;LI Haiyang;ZHANG Jin;ZHOU Wanmeng;LU Lin(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院

出　　处：《系统工程与电子技术》2020年第4期896-903,共8页Systems Engineering and Electronics

基　　金：国家自然科学基金（11572345）;载人航天预先研究项目（010201）资助课题

摘　　要：针对返回近地空间站的月地转移轨道优化问题,提出一种基于改进多圆锥截线的高精度轨道设计方法。该类问题与再入大气月地轨道设计不同,需要考虑空间站轨道面约束。首先分析飞行任务过程,基于逆步长积分策略建立优化模型;然后根据地月位置关系,提出近月点窗口和轨道设计参数的初值估计方法;最后对多圆锥截线法进行改进,并与高精度轨道模型相结合,精确快速求解月地转移轨道。仿真算例验证提出的轨道优化策略具有较好的收敛特性和计算效率,并揭示了返回窗口、近月点出发域和速度增量的变化特性和规律。To optimize and design the return orbit from the Moon to the low Earth space station,an accurate and rapid approach based on the improved multi-conic method is proposed.It is different from Moon-toEarth trajectories directly reentering the Earth atmosphere,where the coplanar constraints of the space station should be considered.Firstly,the flight process is analyzed and the optimization model is built with backward integration strategy.Then,based on the orbital geometric relationship in the cislunar space,an estimation method is proposed to determine the initial value of the perilune window and other orbital parameters.The improved multi-conic model is combined with the high-fidelity model and the transfer orbit is optimized rapidly and accurately with a cascade searching strategy.Simulation results show that the proposed solution strategy is effective and has good convergence.The fundamental patterns of the transfer window,perilune window and velocity increment are also revealed.

关 键 词：多圆锥截线 月地返回轨道 地心白道系 近地空间站 出发域 

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]