Journal of Astronautics ›› 2014, Vol. 35 ›› Issue (5): 506-514.doi: 10.3873/j.issn.1000-1328.2014.05.003

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A Dynamics Parameter On Line Compensation Based Orbit Determination Method for Descending Phase of Lunar Explorer

ZHANG Zhong kai,  CHEN Shi Jie,  DU Lan,  DANZENG Qu ying,  WANG He,  ZHANG Qi fu   

  1. 1.College of Navigation & Aerospace Engineering, Information Engineering University, Zhengzhou 450052, China;
    2. 95948 Troop, Lanzhou 732750,China;  3. 77535,Troop, Lasa  850000,China; 4. 65015,Troop, Dalian 116023,China
  • Received:2012-05-07 Revised:2013-03-11 Online:2014-05-15 Published:2014-05-25


The soft landing mission of lunar explorer is much in demand for real time tracking and navigation along the descending flight. The soft landing process includes complicated orbital control and attitude control. This article focuses on accurately monitoring the orbital maneuver process by using linear attitude control force model and two kinds of orbital control thrust models. An EKF filter for augmented dynamics system is developed to estimate position velocity and dynamics parameters accurately by use of consecutive high accuracy observations. Due to the compensation for the uncertainties of dynamics model, the accurate real time orbit determination during the continuous maneuver process can be realized.

Key words: Lunar explorer; , Dynamics model compensation; , Orbital maneuver; , Dynamic parameter estimation

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