Abstract: In this paper,the problem of orbital design of landing moon detector is discussed which starts from near earth circular parking orbit,produces thrust in velocity direction ,entries landing moon orbit,and hits the moon with on guiding and free flight.Constraint condition are:①the sunshine of landing moon point;②successive ground based observation of the detector;③the limits of initial velocity and flight time of landing moon orbit;④the limits of relative moon velocity and its direction.Using theoretical analysis and simplified hypothesis,considering energy save and constraint conditions①and②,the method and examples are given about selection of the region,the date segment,and the time segment of landing the moon.Basing on numerical analysis and a large numbers of calculation,considering constraint conditions ③ and ④,the method and examples are given about determination of standard orbit.The idea and method in this paper are verified efficient and practical,they may be of important reference value to orbital design of the landing moon orbit of practical project.