关键词: 逃逸轨道, 圆形限制性三体问题, 庞加莱截面

Abstract:

Escaping trajectories are investigated using a Poincaré map method in the circular restricted three body problem consisting of spacecraft, planet and moon. On the condition that Jacobi constant is fixed, the escaping trajectories are integrated back to the first periapsis from vicinity of  L-1 and L-2 and the escaping velocity of moon is obtained.

Key words: escaping , trajectory,  , circular , restricted , three , body , problem,  , Poincaré,  , section