中国空间科学技术

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“嫦娥一号”卫星轨控标定方法研究与实现

唐歌实;陈莉丹;刘勇;   

  1. 北京航空航天大学宇航学院;北京航天飞行控制中心;
  • 发布日期:2009-12-25

Analysis and Implement of Determining the Orbit Maneuver Effect of CE-1 Satellite

Tang Geshi1,2 Chen Lidan2 Liu Yong2(1 Beijing University of Aeronautics and Astronautics,Beijing 100191)(2 Beijing Aerospace Flight Control Center,Beijing 100094)   

  • Online:2009-12-25

被引次数

5

摘要： 在航天测控任务中,对轨控效果进行标定并合理利用可以实现更为精准的轨道控制。提出了一种综合利用控前控后精密轨道、轨控过程遥测姿态数据、遥测加速度计测量数据对沉底发动机、轨控发动机、加速度计刻度系数进行标定的方法;介绍了该方法在中国首次月球探测任务中的应用情况;最后分析了标定结果对定轨及定姿精度的敏感程度,从而在理论上进一步说明在后续深空探测中利用精密轨道进行轨控标定的可行性和重要性。

关键词: 轨道控制, 标定, 月球探测, 卫星

Abstract: The orbit maneuver accuracy of the satellite can be greatly improved by determining the maneuver effect.A method of calibrating the effect of control engines and accelerometer scale error by using the precise orbit parameters,telemetry data for attitude and accelerometer was produced.Then,the successful application of this method to the Chinese first lunar prospector mission was presented.Finally,the sensitivity of the calibrating result to the accuracy of orbit and attitude determination was analyzed.The results prove that the calibration of control effect is feasible,and also very important to deep space exploration in future.