约束条件下的Halo轨道转移轨道设计  

Transfer Trajectory Design for Halo Orbit with Multiple Constraints

作　　者：李明涛[1,2] 郑建华[1] 于锡峥[1] 高东[1] 

机构地区：[1]中国科学院空间科学与应用研究中心,北京100080 [2]中国科学院研究生院,北京100049

出　　处：《宇航学报》2009年第2期437-441,509,共6页Journal of Astronautics

摘　　要：平动点任务的转移轨道往往存在约束条件,以往的研究集中于无约束条件下的Halo轨道转移轨道设计,研究约束条件下的Halo轨道的转移轨道设计问题。首先分析了平动点任务转移轨道的约束条件,然后给出了一种约束条件下Halo轨道转移轨道设计的一般方法,重点推导了考虑轨道高度、航迹角、轨道倾角、升交点约束的微分修正公式。然后以日地L1点附近的Halo轨道为目标轨道,在约束条件下设计了其转移轨道,仿真结果验证了本文方法的有效性。There always exist constraints on transfer trajectory of libration point missions; however, previous studies mainly focused on transfer trajectory design strategy without constraints. This paper studied transfer trajectory design strategy for halo orbit with multiple constraints. Firstly, Constraints on transfer trajectory of libration point missions were ana lyzed. Then a general method of transfer trajectory design with multiple constraints was proposed, emphasis was on the conclusion of differential corrections equations with the altitude ,flight path angle, inclination and ascending node constraints. Finally, a halo orbit around the libration point L1 of the Earth-Sun System was taken as the objective orbit, transfer trajectory with multiple constraints was designed with the proposed method; simulation results validate the effectiveness of the proposed method.

关 键 词：HALO轨道 转移轨道 约束条件 微分修正 

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] P13[天文地球—天体力学]