Journal of Space Science and Experiment >

2023 , Vol. 23 >Issue 3: 19 - 28

DOI: https://doi.org/10.19963/j.cnki.2096-4099.2023.03.002

Monitoring and Early Warning

A Method to Calculate the Short-Time Orbit Maneuver Acceleration Based on the Satellite Ephemeris

  • CUI Shuang-xing ,
  • YANG Zhi-tao ,
  • LIU wei ,
  • WANG Rong-lan ,
  • XIANG Kai-heng ,
  • HE Quan ,
  • WU Zhong-hao
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  • 1. China Satellite Network Group Co., Ltd, Beijing 100029, China;
    2. National Astronomical Observatories, Chinese Academy of Sciences, Beijing 100012, China;
    3. National Space Science Center, Chinese Academy of Sciences, Beijing 100190, China

Online published: 2024-02-01

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Abstract

For LEO (Low Earth Orbit) satellites, due to the greater impact of the atmosphere, orbital maneuvers are frequent. The rapid detection of orbital maneuvers and the calculation of thrust are of great significance for ensuring the operational safety and fault analysis of space targets. Based on the publicly released satellite ephemeris data, a method of identifying satellite orbit maneuver based on the satellite ephemeris is proposed. Through orbit prediction inversion and energy conversion, the calculation of satellite orbit maneuver acceleration under low thrust conditions is realized. The calculation results of the two methods are very consistent. By adding this maneuver acceleration to simulate the satellite orbit, the simulation results are basically consistent with the published ephemeris.

Key words： orbit maneuver; low thrust; orbit maneuver identify; orbit determination

Cite this article

CUI Shuang-xing , YANG Zhi-tao , LIU wei , WANG Rong-lan , XIANG Kai-heng , HE Quan , WU Zhong-hao . A Method to Calculate the Short-Time Orbit Maneuver Acceleration Based on the Satellite Ephemeris[J]. Journal of Space Science and Experiment, 2023 , 23(3) : 19 -28 . DOI: 10.19963/j.cnki.2096-4099.2023.03.002

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