The optimization of continuous rendezvous trajectories for low-thrust satellite targeting objective in near-Earth space presents a significant challenge in aerospace dynamics. For low-thrust satellite, the effect of J2 perturbation is not negligible due to their small propulsive acceleration. Based on the characteristics of the Bezier method, this paper presents a rendezvous trajectory optimization method considering J2 perturbation, which can greatly reduce the computation time required for trajectory optimization under perturbation conditions. The method first solves the rendezvous trajectory optimization problem in a two-body environment. Then, it uses this solution as an initial value to refine the trajectory considering the dynamical effects of perturbation. The simulation results indicate that, compared to directly applying the Bezier shape-method within the J2 dynamical environment, the proposed method effectively reduces the computation time while achieving similar performance metrics. To vali-date the effectiveness of the results obtained by this method, the results will be used as initial values in a Gaussian pseudospectral method (GPM) solver. It can be concluded from the simulation results that this method can yield results that are comparable to those obtained through the Gaussian pseudospectral method (GPM) in a very short amount of time. This method holds significant promise for the rapid preliminary design of continuous rendezvous missions in near-Earth space involving target.