定常幅值小推力登月飞行器轨道研究

ON CONSTANT-AMPLITUDE LOW-THRUST LUNAR PROBE TRAJECTORIES

进行了基于平面三体模型的登月飞行器轨道控制方法的研究 ;研究了从近地低轨道到近月低轨道的飞行轨道 ;给出了在地球逃逸段、惯性漂移段和月球捕获段的运动轨迹和关键点的参数。提出使用“远地点可达”概念完成了地球逃逸段发动机推力终点的选择和使用飞行器相对月心能量完成了在月球捕获段止推发动机工作初始点的选择。

The flight trajectories from low earth parking orbit (LEO) to low lunar parking orbit (LLO) based on a planar three-body model are studied. Trajectories and some key parameters of the three stages, the earth escape stage, coast arc stage, and lunar capture stage, are presented as well. The concept of coverage apogee and the selenocentric energy are first, respectively, introduced to accomplish the terminal point determination of the earth escape stage and the initial point determination of the lunar capture stage.