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<p>Real-time precise orbit determination (RTPOD) of low Earth orbit (LEO) satellite is of paramount importance for fulfilling the time-critical missions such as real-time Earth monitoring and LEO-augmented navigation. It is commonly achieved by the reduced-dynamic (RD) approach which, however, generally suffers from a potential risk of orbit accuracy deterioration during orbit maneuver period. In this study, we develop a method to detect and estimate orbit maneuver in LEO RDRTPOD using global navigation satellite system (GNSS) observations. Orbit maneuver detection is implemented by a shifting window median absolute deviation (SWMAD) method based on posterior carrier phase residuals. Afterwards, the detected orbit maneuver is modeled as three instantaneous velocity pulse parameters in along-track, cross-track, and radial directions of the local orbit reference frame for absorbing aberrant dynamic information. We use datasets with orbit maneuver in 2022 from three LEO satellites, namely Sentinel-3&#xa0;A, Sentinel-3B, and Sentinel-6&#xa0;A, to verify this method. Our detection results show a good consistency with the planning maneuver information with the start time difference less than two sampling intervals (20&#xa0;s). Benefiting from proper modeling of orbit maneuver, the 3D consistency of the derived real-time orbits with kinematic precise orbits as well as external precise science orbits gains improvement more than 90% and reach a similar level of 5 ~ 6&#xa0;cm to that of maneuver-free orbits. Additionally, the estimated orbit maneuver results also agree well with the planning reference values.</p>

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Maneuver detection and estimation for LEO real-time precise orbit determination with GNSS observations

  • 期刊论文

  • 发表日期：

    2025年5月7日

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  • Wei Zhang,
  • Keke Zhang,
  • Xingxing Li,
  • Yehao Zhao,
  • Jiande Huang

摘要

Real-time precise orbit determination (RTPOD) of low Earth orbit (LEO) satellite is of paramount importance for fulfilling the time-critical missions such as real-time Earth monitoring and LEO-augmented navigation. It is commonly achieved by the reduced-dynamic (RD) approach which, however, generally suffers from a potential risk of orbit accuracy deterioration during orbit maneuver period. In this study, we develop a method to detect and estimate orbit maneuver in LEO RDRTPOD using global navigation satellite system (GNSS) observations. Orbit maneuver detection is implemented by a shifting window median absolute deviation (SWMAD) method based on posterior carrier phase residuals. Afterwards, the detected orbit maneuver is modeled as three instantaneous velocity pulse parameters in along-track, cross-track, and radial directions of the local orbit reference frame for absorbing aberrant dynamic information. We use datasets with orbit maneuver in 2022 from three LEO satellites, namely Sentinel-3 A, Sentinel-3B, and Sentinel-6 A, to verify this method. Our detection results show a good consistency with the planning maneuver information with the start time difference less than two sampling intervals (20 s). Benefiting from proper modeling of orbit maneuver, the 3D consistency of the derived real-time orbits with kinematic precise orbits as well as external precise science orbits gains improvement more than 90% and reach a similar level of 5 ~ 6 cm to that of maneuver-free orbits. Additionally, the estimated orbit maneuver results also agree well with the planning reference values.