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@ARTICLE{2026AdSpR..77.7155Z,
       author = {{Zhang}, Lei and {Li}, Kai and {Tang}, Chengpan and {Hu}, Xiaogong and {Shu}, Fengchun and {Yang}, Yan},
        title = "{Improving orbit accuracy for LEO navigation satellites by considering time-variable gravity fields}",
      journal = {Advances in Space Research},
     keywords = {Time-variable gravity, Orbit determination, Orbit prediction, LEO navigation satellites},
         year = 2026,
        month = mar,
       volume = {77},
       number = {6},
        pages = {7155-7167},
     abstract = "{Low Earth Orbit (LEO) navigation satellites are capable of enhancing the
        Global Navigation Satellite System (GNSS) and providing high-
        precision navigation services to users. Consequently, precise
        orbit determination (POD) is fundamental to the utility of LEO
        navigation satellites. A critical factor limiting the accuracy
        of POD is the gravity field. This research selects three LEO
        satellites with distinct orbital altitudes-GRACE-C, Sentinel-3B,
        and Jason-3, and conducts the orbit determination and prediction
        experiments using three different gravity models: EIGEN-GL04C,
        COST-G, and GOCO06s. The article mainly utilizes internal
        consistency and external comparisons with Precision Science
        Orbit (PSO) orbits to evaluate the accuracy of different gravity
        models. To validate the optimal performance of the model, the
        experiments utilized the CODE final products. The results
        indicate that the GOCO06s gravity field model exhibits the best
        accuracy in orbit accuracy. Employing GOCO06s for GRACE-C
        satellite orbit determination, the User Range Errors (URE) is
        1.70 cm, demonstrating 6.45\% and 26.09\% improvements over the
        COST-G and EIGEN-GL04C models, respectively. For 60-min orbit
        prediction, the URE is 8.59 cm while also outperforming COST-G
        (36.47\%) and EIGEN-GL04C (45.43\%). An experiment is designed
        to assess the impact of the time variable components on the
        orbit accuracy of LEO satellites by extracting the time variable
        components of GOCO06s model. The time variable component of the
        gravity field reduces the 60-min orbit prediction error (URE:
        8.59 cm) for GRACE-C (about 500 km) by nearly 79.39\%, whereas
        it decreases the error by 0.30\% for Jason-3 (more than 1300
        km). The research emphasizes optimizing gravity models and
        exploring their navigation applications to address increasing
        precision requirements of satellite services.}",
          doi = {10.1016/j.asr.2026.01.045},
       adsurl = {https://ui.adsabs.harvard.edu/abs/2026AdSpR..77.7155Z},
      adsnote = {Provided by the SAO/NASA Astrophysics Data System}
}