Orbit maneuver for GEO on-orbit service satellite using Hohmann transfer

The orbit transfer strategy of geosynchronous spacecraft (GEO) is investigated in this paper. This method is suitable for the observation of GEO spacecraft before On-Orbit Servicing (OOS). Considering the computation, terminal constraint conditions (illumination condition, latitude deviation) and fuel consumption, Hohmann transfer and two-body mechanics model are adopted to simplify the mission process. In view of the difference between two-body mechanics model and High-Precision Orbit Propagator (HPOP) model, final time will be predicted precisely. By optimizing the final included angle of two spacecraft position vectors, the results got by two-body model can be used to HPOP model to simulate the real mission scenario. With the proposed method, complex perturbations can be ignored. Finally, the results of several numerical simulations demonstrate the validness of the proposed method on trajectory designing for observation of the spacecraft.