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.
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
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
libration point
interplanetary superhighway
Halo orbit
stable manifold
ordinal optimization
differential correction
