摘要：Point return orbit(PRO) of manned lunar mission is constrained by both lunar parking orbit and reentry corridor associated with reentry ***,the fuel consumption and flight time should be *** patched conic equations which are adaptive to PRO are derived first,the PRO is modeled with fuel and time constraints based on the design variables of orbit parameters with clear physical *** that,by combining analytical method with numerical method,a serial orbit design strategy from initial value design to precision solution is *** example indicates that the method has excellent convergence performance and *** to a great deal of simulation results by the method,the PRO characteristics such as Moon centered orbit parameters,Earth centered orbit parameters,transfer velocity change,*** analyzed,which can supply references to the manned lunar mission orbit scheme.