Firstly, we introduce the E/I vectors and the relative E/I vectors and then deduce the relative motion e-quations with the relative E/I vectors. Secondly, we analyze the effects of perturbation on the relative E/I vectors and satellite formation flight safety, thus obtaining the conditions under which the relative E/I vectors must meet the safety requirements. Thirdly, we apply the E/I combined separation method to designing the safe trajectories of a satellite formation. Fourthly, we give two safe formation configurations that use the same and different orbital elements and propose three different control maintenance strategies which use the E/I combined control. Finally, we carry out the numerical simulation of the safety, perturbation effects, safe trajectory design and control. The simulation results, given in Figs. 3 through 10, and their comparison show preliminarily that our E/I combined separation method is effective for designing the safe trajectories of a satellite formation and control its flight.%研究了偏心率/倾角(E/I)联合隔离方法在卫星编队安全轨迹设计和保持控制中应用.首先,引入E/I矢量和相对E/I矢量,建立了相对E/I矢量描述的相对运动方程.然后,分析了摄动对相对E/I矢量和编队安全性的影响,得到了安全性要求下相对E/I矢量需要满足的条件；推导了E/I联合隔离控制方程,提出了安全轨迹保持控制策略.最后,通过仿真验证了基于E/I联合隔离的安全轨迹设计与控制策略的有效性.
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