Application of the Relative Orbit in an On-Orbit Service Mission

To achieve an on-orbit service mission, the mission spacecraft must approach target first, which is based on spacecraft’s relative motion. enhance safety and reliability of missions, hovering orbit was proposed needed to be studied further. A high-precision design method for presented dynamics model in this paper. Firstly, stability analysis model, a determine initial value periodic motion explored, example given verify validity method. Then, through theoretical analysis, formulae control acceleration required during flying were put forward both without considering perturbation with J2 perturbation, numerical simulations made feasibility approaches proposed. Simulation results show that curves are smooth, indicates easier achieve, sliding mode theory adopted control. The can provide references space missions practical engineers.