航天器任意方位强迫绕飞轨迹规划方法研究OA

A universal elliptical fly-around trajectory design method with the target spacecraft as the primary focus is proposed.First,an elliptical trajectory determination algorithm based on the initial/target relative positions in the fly-around frame is designed,enabling both long-arc and short-arc fly-around through angular velocity polarity switching.Subsequently,a mission-adaptive fly-around coordinate system is constructed for trajectory planning.Finally,the reference trajectory is transformed into the target orbital coordinate system,and an equally-spaced impulsive control strategy designed with the Clohessy-Wiltshire(C-W)equation is used for trajectory tracking,achieving full-phase forced fly-around at arbitrary azimuth angles.The simulation results demonstrate that the chaser spacecraft successfully completes prescribed fly-around maneuvers with all three-axis position errors maintained below 1 m,validating the method's effectiveness.