中文摘要：

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。

英文摘要：

Firstly, we introduce the E/I vectors and the relative E/I vectors and then deduce the relative motion equations 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 ele- ments 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 simula- tion 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.