Numerical Simulation and Analysis for GOCE Satellite Orbit Perturbations

A 30-day arc of the GOCE satellite orbit is simulated using the method of orbit integration.The maximum perturbation accelerations and their percentage contribution in the sum of all accelerations due to the lunisolar perturbations,Earth tides,ocean tides,atmospheric tides,pole tides,relativity effects,atmospheric drag and solar radiation pressure are computed on the basis of simulated orbit.Moreover,the motion of GOCE satellite influenced by the conservative forces and tidal effects on gravity gradients are analyzed and evaluated.The analysis results can be as a reference for the POD and gravity field recovery of GOCE mission.