Autonomous guidance for proximity to target spacecraft

This paper presents the guidance algorithms of chase spacecraft for autonomous proximity to target spacecraft. The process of autonomous proximity is initially divided into three phases including proximity maneuver, fly-around maneuver and final approach. Based on the Hill equation, the characteristic of each phase is analyzed and then the criteria to design guidance algorithm is proposed. Then, the multi-pulse algorithm is adopted in proximity maneuver and final approach phases, capable of achieving the maneuver in any direction and orbit plane. Different orbit is then planned in each phase in accordance with mission requirements and proposed criteria. Finally, simulation is performed to prove this guidance algorithm. The Offered is an easy way for engineering realize, the analyses and opinions included in this paper can be generic applied in the future space tasks.