A very important factor for recovering the high accuracy Earth's gravity field is the knowledge of the GOCE satellite
orbit. In this paper, a 30-day arc of the GOCE satellite orbit (called the reference orbit) was simulated using dynamic
orbit integration method, and the perturbation accelerations due to the lunisolar perturbations, the Earth tides, the ocean
tides, the atmospheric tides, the pole tides, the relativity effects, the atmospheric drag and the solar radiation pressure
were computed along the simulated orbit according to the dynamic models. Then the maximum perturbation
accelerations and their percentage contribution in the sum of all accelerations due to the aforementioned forces were
given and analyzed. In addition, the various variants of the satellite orbit (called the modified reference orbits) were
obtained by subtracting the selected conservative forces to the satellite motion model for the reference orbit. Finally, the
motion of GOCE satellite that influenced by the conservative forces were analyzed through comparing the satellite
positions between the reference orbit and the modified reference orbits. The analysis results can be as a reference for the
precise orbit determination and gravity field recovery of GOCE mission.
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