Abstract: Since the circular restricted three-body problem model ignores the effect of perturbations,it can not accurately describe the dynamic characters of the three-body system.The dynamic characters and orbit design strategy of the perturbed three-body problem model was studied.Firstly,main perturbations of libration point missions were analyzed,and then the general dynamic equation of the perturbed three-body problem in the synodic frame was concluded from the dynamic equations in the inertial frame considering the effects of the eccentricity,the gravity of the fourth body and the solar radiation pressure.Finally,the two level differential corrections method was proposed to transform the orbit designed under the circular restricted three-body problem model into the perturbed three-body problem model.