考虑月球升交点黄经的地月低能转移轨道

地月转移轨道研究的基本模型主要是限制性二体模型和限制性三体模型。在限制性三体建模下,基于轨道分类理论的地月脉冲变轨比传统的霍曼变轨节省了更多的燃料(至少13%以上)。单独的"地球-月球-飞行器"的限制性三体问题无法应用轨道分类的理论进行轨道设计,必须加入太阳。文章考虑了月球升交点赤经、黄白交角,以及正确的地月系统稳定流形的方向,整个"太阳-地球-月球-飞行器"系统拆分为"地球-月球-飞行器"的平面圆型限制性三体问题,和"太阳-地球-飞行器"三维圆型限制性三体问题进行分析,并利用Matlab仿真验证了方案的可行性。

Low Energy Transfer Orbit to the Moon Considering Longitude of the Ascending Node of the Moon

The basic models of the transfer orbit to the Moon were mainly the restricted two-body model and the restricted three-body model.In the restricted three-body model,the trajectory based on the trajectory class theory required less fuel(save at least 13%) comparing to that of the Hohmann transfer.Sun should be considered in trajectory design,because the trajectory class theory could not be used to solve the single Earth-Moon-Spacecraft restricted three-body problem.Considering the longitude of the ascending node of the Moon,the angle of the ecliptic and Moon orbit,and the correct stable manifolds of Earth-Moon system,the whole Sun-Earth-Moon-Spacecraft system was divided into two parts: the Earth-Moon-Spacecraft planar circular restricted three-body problem,and the Sun-Earth-Spacecraft three dimensional circular restricted three-body problem.The availability of the method was verified by Matlab.