针对卫星在非开普勒轨道下的运动特征,提出了研究卫星交会变轨决策的方法。首先,在Hill坐标下,采用比例导引方法求解卫星进行变轨机动时所需要的速度增量。然后,再通过Lagrange插值算法解出卫星在任意特征点上变轨机动所需要的速度增量,根据数字仿真得出大量的仿真数据并画出满足变轨决策条件的决策曲面。最后,对决策曲面的涵义做出分析,说明了该方法对于研究非开普勒轨道下卫星变轨决策问题具有一定的意义。 Aiming at the motion characteristics of satellites under non-Keplerian orbit, a method to study the orbit transition of satellite satellites is proposed. First of all, under the Hill coordinates, the proportional guidance method is used to solve the speed increment needed when the satellites perform the orbit maneuver. Then, the Lagrange interpolation algorithm is used to solve the velocity increment required for orbital maneuvering of the satellite at any feature point. Based on the numerical simulation, a large number of simulation data are obtained and the decision-making surface that meets the decision of changing trajectory is drawn. Finally, the definition of the decision surface is analyzed, which shows that this method is of some significance for the study of satellite orbit change decision under non-Kepler orbit.