软着月任务窗口与轨道设计方法研究

An Approach to Window and Trajectory Design for Lunar Soft-landing Mission

建立了一套应用于多约束条件下软着月任务的窗口计算以及轨道设计方法。针对经历发射段、地月转移段、绕月段及动力下降段的月球探测器,综合考虑各个特征点的位置、光照、测控等约束,结合轨道特性,采用着月点→近月点→入轨点→发射点倒推的方式,快速确定探测器的发射窗口。在其中选择发射时刻后即可计算转移轨道的轨道根数初值,并搜索计算精确轨道。该方法对于我国月球探测后期工程的发射窗口计算与轨道设计工作有较重要的参考价值。

A suit of method of window calculation and trajectory design for lunar soft-landing mission is studied.Aiming at a lunar probe which passes launch phase,translunar phase,lunar orbit phase and soft-landing phase,considering constraints include position,lighting and TT＆amp;C of the feature points,combining with characteristics of the translunar trajectory,using retroversion mode of landing point→perilune→translunar injection→launch center,this paper fast calculates the launch window of the lunar probe.Initial value of the translunar trajectory＇ s elements are easily ealculated after launch time is specified in the launch window, then the precision trajectoU is obtained by search. This approach will be of irnportemt value for the launch window calculation and the orbital design in the future slage of China Lnnar Exploration Program.