Applying eccentricity/inclination (E/I) combined separation method to designing safe trajectories of satellite formation and controlling its flight

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 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.