Abstract: Double Lunar-Swingby (DLS) trajectory is a type ofnon-linear orbit which has potential applications in the deep-spaceexploration. A nominal trajectory is given under CR3BP model, and itsdynamic characteristic is analyzed. According to the error dispersion of thenominal trajectory, several correction principles are established.Considering the solar gravitational perturbation, the R4BP model isestablished. A method of explicit guidance at the ``key node'' is developed,and the correction maneuver results of the initial error, navigation error,maneuver error and the solar gravitational perturbation are obtained. Thestatistical dispersion analysis is carried out with Monte-Carlo simulation.Based on these works, a new method of initial velocity supplement combinedwith explicit guidance is proposed to correct the initial error, navigationerror, maneuver error and the solar gravitational influence, and theparameters including the magnitude of supplement velocity and time of TCMare optimized. The simulation results show that this method can reduce thecorrection maneuver obviously. The results and conclusions of this paper canprovide a reference for the engineering applications of DLS trajectory.