Analysis of Stability、Simulation and Configuration Design for Satellite Formation under the Influence of the J2 Perturbation

Starting with the state transition matrix, the precise analytic solution of the small eccentricity reference orbit was obtained. Then the mechanism of formation drift due to the J2 perturbation was investigated and the drift of formation was split into several layers from which some ideas about satellite formation keeping and control could be provided. Based on the mechanism, the restriction on orbit that enables stable formation flying was derived and a method of satellite formation design came into being with which the relative motion in 3 orthogonal directions (radial, in-track, cross-track) would be synchronized. Finally, simulations with STK software were provided to demonstrate the correctness of analytical results and the efficacy of the proposed formation design method.