The Three Body Problem

Escaping trajectories are investigated using a Poincar é map method in the circular restricted three body problem consisting of spacecraft , planet and moon .

基于由飞行器、行星及其卫星组成圆型限制性三体问题模型，通过庞加莱映射的方法，研究了飞行器从行星卫星附近逃逸的问题。

Under the general Circular Restricted Three Body Problem ( CRTBP ) model for deep space exploration , the Chief-Deputy spacecrafts formation model was built up .

针对深空探测中具有一般性的圆形限制性三体（CRTBP）模型，进行主从飞行器编队建模。

Based on the detailed discussions on a simplified ideal resonant model with perturbations which corresponds to the elliptic restricted three & body problem , we put forward a discriminating method on stability of orbital resonant states by means of an energy relation in this paper .

本文通过对一种简化的椭圆型限制性三体问题对应的受摄理想共振模型的详细讨论，建立了一种用能量关系来判别轨道共振态稳定性的方法。