Arming at the formation reconfiguration problem for the elliptic reference orbit under J₂perturbation, a multiple impulsive trajectory optimization strategy was developed on the basis of the Gauss variation equation and with the objective function of minimal fuel consumption. A relative dynamics equation using the orbital element difference was derived, in which the J₂ perturbation and the coupling effects between in-plane and out-of-plane relative movements were considered. The hybrid approach of the genetic algorithm and the sequence quadratic programming was proposed to optimize the total velocity increment. The simulation results show that the hybrid approach is effective, and can obtain the feasible solution efficiently. Since the J₂ perturbation and elliptic reference orbit are considered in the study, the approach has some reference significance for the trajectory optimization of space mission.