中国空间科学技术

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多约束条件下探测器击中月球的轨道设计

郗晓宁,王海丽,肖齐英   

  1. 国防科技大学
  • 发布日期:1997-04-25

ORBITAL DESIGN OF HITTING MOON DETECTOR UNDER MULTI-CONSTRAINT CONDITIONS

Xi Xiaoning Wang Haili Xiao Qiying (National University of Defense Technology,Changsha 410073)   

  • Published:1997-04-25

摘要： 讨论了探测器从低高度圆型地球停泊轨道出发，沿速度方向施加脉冲推力进入登月轨道，不加制导自由飞行击中月球的轨道设计问题。考虑的约束条件包括：①着月点光照；②探测器通视；③登月轨道初速及飞行时间限制；④着月时探测器相对月面落速大小和方向限制；等等。利用理论分析和简化假设，考虑节省能量、约束条件①和②，给出了着月区域、着月日期段、着月时刻段的选择方法及算例；基于数据分析和大量计算，考虑约束条件③和④，给出了确定标准轨道的方法和算例。该思路和方法经数值仿真验证是高效实用的，可为实际工程的登月轨道设计提供重要依据

关键词: 月球探测器, 环月轨道, 硬着陆

Abstract: In this paper,the problem of orbital design of landing moon detector is discussed which starts from near earth circular parking orbit,produces thrust in velocity direction ,entries landing moon orbit,and hits the moon with on guiding and free flight.Constraint condition are:①the sunshine of landing moon point;②successive ground based observation of the detector;③the limits of initial velocity and flight time of landing moon orbit;④the limits of relative moon velocity and its direction.Using theoretical analysis and simplified hypothesis,considering energy save and constraint conditions①and②,the method and examples are given about selection of the region,the date segment,and the time segment of landing the moon.Basing on numerical analysis and a large numbers of calculation,considering constraint conditions ③ and ④,the method and examples are given about determination of standard orbit.The idea and method in this paper are verified efficient and practical,they may be of important reference value to orbital design of the landing moon orbit of practical project.