Abstract:The point return orbit characteristics for a vehicle from a lunar mission were studied, and how the landing point and reentry point vary was focused upon. Firstly, analysis of some characteristic points was presented, and lunar antipode, reentry point and perigee were included. Then the stabilization property of the latitude and velocity at reentry point was achieved. Furthermore, based on the characteristics of the foregoing three points, approximate method for the theoretical relation of landing point and reentry point was proposed. In addition, relation of lighting condition at landing point and lunar return window was analyzed by using lunar phase law, and the basic conclusions was attained qualitatively. Finally, the orbit simulation was established with double two-body model, which shows the feasibility of this theoretical model in predicting the lunar point return orbit.