Abstract: For the problem of multi-impulse long-range rendezvous trajectory optimization of spacecraft under complex constraints and perturbation conditions, this paper proposes a step-by-step optimization solution strategy that combines global optimization under the ideal two-body model and local correction under the perturbation model. Considering constraints such as sunlight exposure and tracking and control arcs during the rendezvous process, the comprehensive particle swarm algorithm is first used for global optimization under the ideal two-body model, and then the global optimization result is taken as the initial guess. The rendezvous problem is successively subjected to local optimization and correction in the J₂ model and high-precision model through sequential quadratic programming, and finally the rendezvous impulses that satisfy the constraints in the high-precision orbital model are obtained through solution. The simulation results show that the optimization solution strategy proposed in this paper can generate long-range rendezvous control impulses that conform to the actual orbital environment and meet the requirements and constraints of different scenarios.