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Orbit determination and thrust force modeling for a maneuvered GEO satellite using two-way adaptive Kalman filtering

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Abstract

A two-way adaptive Kalman filter is proposed by combining a two-way filter with an adaptive filter for orbit determination of a maneuvered GEO satellite. A method of using Newton’s high-resolution differential formula and polynomial fitting for modeling the thrust force of a maneuvered GEO satellite is developed. The adaptive factor, which balances the contributions of the measurements and the dynamic model information, is determined by using a two-segment function and predicted residual statistics. Simulations with a maneuvered GEO satellite tracked by the Chinese ground tracking network were conducted to verify the performance of the proposed orbit determination technique and the method of thrust force modeling. The results show that refining the thrust force model is beneficial for the orbit determination of a maneuvered GEO satellite; the two-way adaptive Kalman filter can efficiently control the influence of the dynamic model errors on the orbit state estimate.

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Authors and Affiliations

  1. Xi’an Research Institute of Surveying and Mapping, Xi’an, 710054, China

    TianHe Xu

  2. GFZ German Research Centre for Geosciences, Potsdam, 14473, Germany

    TianHe Xu, KaiFei He & GuoChang Xu

Authors
  1. TianHe Xu
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  2. KaiFei He
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  3. GuoChang Xu
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Correspondence to TianHe Xu.

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Xu, T., He, K. & Xu, G. Orbit determination and thrust force modeling for a maneuvered GEO satellite using two-way adaptive Kalman filtering. Sci. China Phys. Mech. Astron. 55, 738–743 (2012). https://doi.org/10.1007/s11433-012-4670-4

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  • DOI: https://doi.org/10.1007/s11433-012-4670-4

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