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<p>Beidou GEO/IGSO satellites require regular station-keeping maneuvers to compensate for orbital secular drifts from their nominal positions induced by Earth's oblateness and 1:1 orbital resonance effects. However, the lack of publicly available thrust parameters creates substantial challenges for Precise Orbit Determination (POD), affecting navigation and especially GEO-dependent short-message communication and international search and rescue service availability. This study presents a novel automated framework for BDS satellite maneuver detection and thrust model establishment. This framework integrates: (1) maneuver detection via gradient analysis of triple-difference residuals, (2) thrust characterization through kinematic orbit determination with optimized observation geometry, (3) dynamic modeling using iterative short-arc fitting that simultaneously estimates initial states, Solar Radiation Pressure (SRP) coefficients, and thrust parameters while optimizing transition points of thrust model. Analyzing four years of BDS-2/BDS-3 maneuvers (2020–2023), we establish: (1) a Piece-Wise Linear (PWL) model for BDS-2 gradual maneuvers (10–30 min) and BDS-3 out-of-plane adjustments, and (2) a triangular (Tri) impulse model for BDS-3 rapid maneuvers (1–2 min). The proposed thrust modeling framework demonstrates centimeter-level kinematic orbit fitting accuracy in along-track and cross-track directions for standard maneuvers, while maintaining decimeter-level precision even in extreme GEO out-of-plane cases. Long-arc orbit fitting results further validate the framework’s effectiveness for consecutive dynamic orbit recovery.</p>

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Automatic orbital maneuver detection and thrust model establishment for Beidou GEO/IGSO satellites

  • 期刊论文

  • 发表日期：

    2026年3月5日

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  • Jing Qiao,
  • Hua Xu,
  • Bofeng Li

摘要

Beidou GEO/IGSO satellites require regular station-keeping maneuvers to compensate for orbital secular drifts from their nominal positions induced by Earth's oblateness and 1:1 orbital resonance effects. However, the lack of publicly available thrust parameters creates substantial challenges for Precise Orbit Determination (POD), affecting navigation and especially GEO-dependent short-message communication and international search and rescue service availability. This study presents a novel automated framework for BDS satellite maneuver detection and thrust model establishment. This framework integrates: (1) maneuver detection via gradient analysis of triple-difference residuals, (2) thrust characterization through kinematic orbit determination with optimized observation geometry, (3) dynamic modeling using iterative short-arc fitting that simultaneously estimates initial states, Solar Radiation Pressure (SRP) coefficients, and thrust parameters while optimizing transition points of thrust model. Analyzing four years of BDS-2/BDS-3 maneuvers (2020–2023), we establish: (1) a Piece-Wise Linear (PWL) model for BDS-2 gradual maneuvers (10–30 min) and BDS-3 out-of-plane adjustments, and (2) a triangular (Tri) impulse model for BDS-3 rapid maneuvers (1–2 min). The proposed thrust modeling framework demonstrates centimeter-level kinematic orbit fitting accuracy in along-track and cross-track directions for standard maneuvers, while maintaining decimeter-level precision even in extreme GEO out-of-plane cases. Long-arc orbit fitting results further validate the framework’s effectiveness for consecutive dynamic orbit recovery.