飞向晕轨道的探测器轨道优化  

The Optimization of Transfer to Halo Orbits

作　　者：胡少春[1,2] 孙承启[1,2] 刘一武[1,2] 

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术国家级重点实验室,北京100190

出　　处：《空间控制技术与应用》2010年第4期1-5,30,共6页Aerospace Control and Application

摘　　要：晕轨道的稳定流形为从地球到晕轨道的转移轨道设计提供了便利.以往都采用在晕轨道上的目标点施加脉冲,这样,稳定流形只是为转移轨道的设计提供一个初始猜想,探测器并没有运行在稳定流形上,因而并未真正利用稳定流形节省燃料的优势.利用基于序优化理论的微分修正法,研究从晕轨道近地点稳定流形上不同点进入稳定流形所需要的燃料消耗,寻找燃耗最少的转移轨道.仿真表明,对于晕轨道近地点入轨,找到的稳定流形射入点机动比以往的晕轨道入轨点机动节省约33%的燃料消耗.此外,还对晕轨道上不同入轨点的入轨代价进行了研究,得到了晕轨道近地点入轨的最小燃耗解.Stable manifolds associated with a Halo orbit can be used to design the transfer trajectory from the Earth to Halo orbit. However, previous studies mainly focused on the optimization of Halo orbit insertion maneuver velocity. So, the stable manifolds only serve as an initial guess for use in a transfer trajectory design scheme. The probe didn＇t travel on the stable manifolds, and couldn＇t make use of the low energy transfer character of manifolds. The differential correction based on Ordinal Optimization theory is used to minimize the stable manifold orbit insertion maneuver velocity in this paper. The numerical simulation results show that the insertion maneuver onto the given stable manifold could save maneuver costs by 33% compared with the Halo perigee insertion maneuver. Moreover, insertion costs for different points in the Halo orbit are analyzed,thus getting the lowest Halo perigee HOI cost transfer trajectory.

关 键 词：平动点 星际高速公路 晕轨道 稳定流形 序优化 微分修正 

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]