Journal of Astronautics ›› 2015, Vol. 36 ›› Issue (5): 489-495.doi: 10.3873/j.issn.1000-1328.2015.05.001

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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


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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