宇航学报 ›› 2015, Vol. 36 ›› Issue (5): 489-495.doi: 10.3873/j.issn.1000-1328.2015.05.001

• 飞行器设计与力学 • 上一篇    下一篇

嫦娥三号探测器连续姿控的轨道动力学模型补偿及实现

张宇,曹建峰,段建锋,陈明,段成林   

  1. 1. 北京航天飞行控制中心,北京100094;2.航天飞行动力学技术重点实验室,北京100094
  • 收稿日期:2014-05-06 修回日期:2014-07-11 出版日期:2015-05-15 发布日期:2015-05-25
  • 基金资助:

    国家自然科学基金(11173005,11373013,11203003,11303001)

Orbit Dynamics Model Compensation and Implementation forContinuous Attitude Control of Chang′e 3 Probe

ZHANG Yu,CAO Jian feng, DUAN Jian feng,CHEN Ming, DUAN Cheng lin   

  1. 1. Beijing Aerospace Flight Control Center,Beijing 100094,China;
    2. Science and Technology on Aerospace Flight Dynamics Laboratory,Beijing 100094,China
  • Received:2014-05-06 Revised:2014-07-11 Online:2015-05-15 Published:2015-05-25

摘要:

针对嫦娥三号探测器的连续姿控喷气对飞行轨道产生的扰动影响,在精密定轨中建立了经验力补偿模型,并使用最小二乘估计算法计算经验力模型参数与探测器轨道。通过重叠弧段轨道精度评估法对该模型补偿效果进行了验证,结果显示,定轨预报的星历误差以及拟合残差均有所改善,特别是环月轨道的定轨精度由百米量级提高到十米量级。

关键词: 嫦娥三号, 姿控喷气, 轨道动力学, 模型补偿

Abstract:

The continuous attitude control jet propulsion of Chang′e 3 probe has disturbing force effect on the probe orbit, in this paper an empirical force compensation model is added to the high accuracy orbit determination model. The empirical model parameter and the probe orbit are calculated by the weighted least squares estimation algorithm. The new model is verified by assessment of overlapping arctrack accuracy. The result shows that both the orbit ephemeris errors and the fitting residuals of forecasted orbit are improved, and the orbit determination accuracy is enhanced from 100m to 10m.

Key words: Chang&prime, e 3 probe;Attitude control jet; Orbit dynamics; Model compensation

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