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Chinese Journal of Space Science ›› 2015, Vol. 35 ›› Issue (6): 730-737.doi: 10.11728/cjss2015.06.730

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Orbit Determination Method Based on Thrust Force Model for GEO Satellite in the Period of Orbit Recovery

LI Xiaojie1, HUANG Yong2, GUO Rui1, ZHU Lingfeng1, SU Ranran1, WU Shan1   

  1. 1 China Beijing Satellite Navigation Center, Beijing 100094;
    2 Shanghai Astronomical Observatory, Chinese Academy of Sciences, Shanghai 200030
  • Received:2014-12-29 Revised:2015-07-02 Online:2015-10-15 Published:2015-12-07

Abstract:

Real time, continuous and high precision navigation service is needed due to the frequent geostationary satellite (GEO) orbit maneuver. How to recover orbit rapidly for geostationary satellite based on short-arc tracking is the key factor. A new orbit determination method uniting the data before, during and after satellite maneuver is studied, and C-band transfer ranging data as well as the telemetry and telecontrol parameters during satellite maneuver are all used. The results based on observation data for geostationary satellite in Beidou System (BDS) indicate that the integrated solution strategy of orbit parameters and thrust force parameters needs to be adopted in the period of orbit recovery. The accuracy of 3-dimensional positions is about 20m, and the orbital precision in radial component is better than 2.5m using the data 4 hours after orbit maneuver. The method provides a solution to resolve several problems of dynamic orbit determination and point positioning in short-arc tracking.

Key words: Beidou System (BDS), Geostationary orbit satellites, Orbit maneuver, Orbit rapid recovery, Thrust force, Telemetry and telecontrol data

CLC Number: