宇航学报

宇航学报 ›› 2016, Vol. 37 ›› Issue (10): 1157-1163.doi: 10.3873/j.issn.1000-1328.2016.10.001

• 飞行器设计与力学 • 上一篇    下一篇

月球探测软着陆与采样返回段弹道确定

宋叶志，黄勇，胡小工，王琰，茅永兴，朱凌凤，昌胜骐   

  1. 1．中国科学院国家授时中心，西安 710600；2．中国科学院上海天文台，上海200030；
    3．中国科学院大学，北京100049；4. 解放军信息工程大学地理空间信息学院，郑州450001；
    5．中国卫星海上测控部，江阴214431；6.北京卫星导航中心，北京100094
  • 收稿日期:2016-01-05 修回日期:2016-03-23 出版日期:2016-10-15 发布日期:2016-10-25
  • 基金资助:

    国家自然科学基金（11473056，11403076）; 飞行器海基测量与应用实验室（FOM2015OF001）

Trajectory Determination for Lunar Probe Soft Landing and Sampling Return

SONG Ye zhi, HUANG Yong, HU Xiao gong, WANG Yan,MAO Yong xing, ZHU Ling feng, CHANG Sheng qi   

  1. 1． National Time Service Centre, Chinese Academy of Sciences, Xi’an 710600, China;
    2．Shanghai Astronomical Observatory, Chinese Academy of Sciences, Shanghai 200030, China;
    3．University of Chinese Academy of Sciences, Beijing 100049, China;
    4．Institute of Surveying and Mapping, Information Engineering University, Zhengzhou 450001, China;
    5．China Satellite Maritime Tracking and Control Department, Jiangyin 214431, China;
    6．Beijing Satellite Navigation Center, Beijing 100094, China
  • Received:2016-01-05 Revised:2016-03-23 Online:2016-10-15 Published:2016-10-25

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摘要：

针对月球探测中软着陆与采样返回段弹道计算问题，提出用数值逼近弹道确定方法。通过B样条对探测器状态进行建模，进而综合全弧段数据进行统计定轨的方法。由于样条法良好的数值逼近性能，使得该方法对探测器弹道异常复杂情况下的状态确定较为有效。对嫦娥三号探测器动力软着陆弧段进行了仿真与实测数据处理。分析了采样返回段的基本动力学与控制特征，为后续的嫦娥五号探测器的软着陆及其采样返回提供初步的可行弹道计算方法。在嫦娥三号探测器动力落月段实测数据处理中，通过评估，该段弹道确定精度优于100 m，其弹道末点与NASA的月球勘测轨道器（LRO）给出的结果差异优于50 m，证实了文章提出的软着陆弹道确定方法的有效性。

关键词: 嫦娥三号, 嫦娥五号, 软着陆, 采样返回, 轨道确定, 标称轨道制导

Abstract:

A new method of trajectory determination for soft landing and sampling return for lunar probe by numerical approximation is presented. The method describes the probe′s trajectory by B-spline and makes full use of all the tracking data to determine the trajectory. It is very suitable for fitting complicated trajectory for spline′s special properties. The dynamics and control characteristics of the sampling return is analyzed, the preliminary feasible trajectory determination method for soft landing and sampling return of Chang’e-5 is provided. By processing the simulation data and measured data of Chang’e-3 lunar probe, it could be assumed that the accuracy of trajectory determination of soft landing is better than 100 meters in Chang’e -3 lunar probe data processing. It appears that the difference between the endpoint of the trajectory and the location got from the image processed by NASA′s lunar reconnaissance orbiter(LRO) is less than 50m. It demonstrates the effectiveness of the method of soft landing trajectory determination provided by the paper is verified.

Key words: Chang’e-3, Chang’e-5, Soft landing, Sampling return, Orbit determination, Nominal trajectory guidance

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