摘要
在限制性四体模型下研究基于小推力方式的地月低能转移问题,通过借助于平动点轨道的相空间结构来揭示小推力转移的机理。重点研究了小推力转移自由飞行段的构造:经由LL1点穿越获得最小能量的低能转移;而经由LL1点Halo轨道穿越,得到(M,N)-圈穿越轨道;由于Halo轨道相对于平动点增加了一维度的选择,根据(2,2)-圈穿越轨道构造该转移的自由飞行段。在地球势阱逃逸和月球势阱捕获段,分别设计了合适的小推力的控制律及发动机开/关机时间,成功实施近地球段的小推力加速和近月球段的减速。尽管未对所得到的结果进行优化,所得转移轨道的燃料消耗也与类似边界条件的SMART-1轨道基本一致。
This article deals with the trajectory from Earth to Moon based on the low thrust,and attempts to expose the mechanism of low-thrust transfer in the frame of restricted four body problem.The article emphasizes the constructions for the low-energy transfer trajectories： the minimum energy cislunar transfer is acquired by the trajectory transiting LL1,and the（M,N）-loopy transiting trajectories are achieved by transiting the Halo orbit around LL1.Thus one of（2,2）-loopy transiting trajectories is chosen as the free-flight trajectory,which has more one option attained by Halo orbit than the transiting trajectory gained by LL1.In the escaping phase from Earth and the capturing phase by Moon,the simple control laws and on/off-schedules for the engine of the low-thrust are proposed to accelerate and decelerate the spacecraft near the Earth＇s and Moon＇s gravitation traps respectively. In despite of no performance on the optimization for the trajectories,the results in the fuel consumptions are consistent with SMART-1 for the similar boundary conditions.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2008年第4期781-787,共7页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(10702003)
北京航空航天大学博士研究生创新基金
关键词
地月低能转移
小推力
平动点
HALO轨道
(M
N)-圈穿越轨道
low-energy transfer from Earth to Moon
low thrust
libration point
Halo orbit
（M,N）-loopy transiting trajectory
