地月L1点低能转移轨道设计与优化  

Design and optimization of Earth-Moon L1 low-energy transfer orbit

作　　者：乔琛远 杨乐平[1] QIAO Chenyuan;YANG Leping(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,湖南长沙410073

出　　处：《系统工程与电子技术》2024年第10期3519-3527,共9页Systems Engineering and Electronics

基　　金：高轨智能轨道设计理论与操控技术研究基金(22-ZZCX-083)资助课题。

摘　　要：针对地月空间平动点周期轨道与近地轨道之间的低能转移问题,提出一种地月L1(Earth-Moon L1,EML1)点Halo轨道到地球静止轨道(geostationary Earth orbit,GEO)的四脉冲低能转移轨道的设计方法。所提方法在扰动流形和Lambert弧段拼接的三脉冲转移轨道设计基础上,从分析轨道雅可比常数变化与速度增量关系的角度出发设计四脉冲低能转移轨道。数值仿真结果表明,四脉冲优化模型比三脉冲模型效率更高,可以得到更优的转移方案,有效解决了优化过程中由于搜索空间大、极值数量多而导致的优化结果不佳的问题。所提设计方法可以用于EML1其他周期轨道族与各类近地轨道的相互转移问题研究。Aiming at the low-energy transfer problem between the periodic orbit of the cislunar space libration point and near-Earth orbit,a design method of 4-impulses low-energy transfer orbit from Earth-Moon L1(EML1)point Halo orbit to geostationary Earth orbit(GEO)is proposed.Based on the design of 3-impulses transfer orbit which applies disturbed manifold and Lambert arc,the 4-impulses low-energy transfer orbit is designed by analyzing the relationship between the change of Jacobi constant and the velocity increment.Numerical simulation results show that the 4-impulse optimization model is more efficient than 3-impulse model and a better transfer scheme can be obtained,which effectively solves the problem of obtaining poor optimization results due to large search space and numerous extreme values in the optimization process.The proposed design method can be used to study the transfer between other periodic orbit families of EML1 and various near-Earth orbits as well.

关 键 词：地月空间 平动点 周期轨道 不变流形 低能转移轨道 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]