基于准流形方法日地系L3点转移轨道设计  

Transfer Trajectories to L3 Libration Point of Sun-Earth System

作　　者：潘迅[1] 泮斌峰[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《中国空间科学技术》2015年第1期51-57,共7页Chinese Space Science and Technology

摘　　要：针对深空探测中轨道转移时间长且能量消耗较大的问题,提出基于准流形实现从地球停泊轨道到日地系L3点转移轨道的设计方法。在日地限制性三体问题模型下,在L1点或L2点Halo轨道上施加扰动推力,构造准流形,利用其非线性三体动力学特性,通过霍曼转移轨道与近地轨道进行拼接,使航天器进入准流形后能够无动力滑行到L3点附近区域。在准流形与L3点周期轨道交点,施加速度脉冲,使航天器进入相应周期轨道,从而完成轨道转移。仿真结果表明,利用该方法所得结果与基于不变流形的转移轨道相比,能将速度增量从4 398m/s减少为4 014m/s,并将转移时间从9年以上缩短到7.3年以内,有效地提高了航天器的工作效率。A method was presented for designing the transfer trajectories to the Sun-Earth L3 periodic orbits based on the pseudo manifolds in the circular restricted three body problem. The dynamics of the pseudo manifolds, constructed by giving a large perturbation to L1 or L2 orbits, were used to construct the transfers. Three deterministic maneuvers were required to complete the orbit transfer： first, leave the low Earth orbit; second, transfer into the pseudo manifold; third, inject to the L3 orbit. Numerical simulation results show that, compared with the transfers based on invariant manifolds, this method reduces the transformational energy consumption from 4 398 m/s to 4 014 m/s, and the flight duration is shortened from more than 9 years to less than 7.3 years, thus improving the efficiency of the spacecraft.

关 键 词：圆限制性三体问题 轨道转移 准流形 平动点 

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]