Aiming at the complex problem of matching flight windows and orbits connection due to the multiple flight stages, long duration and complicated constraints of the manned lunar mission based on once LEO (low earth orbit) and twice LLO (low lunar orbit) RVDs (rendezvous and dockings), a design strategy of connecting the full-mission nominal flight windows and orbits with the combining layered decomposition and the forward and reverse design approach were proposed. The characteristics and application prospect of the manned lunar mission based on once LEO and twice LLO RVDs were introduced, and the basic mission requirements and engineering constraints were supposed. The effectiveness of the proposed method was verified by simulation. The nominal flight orbital elements and windows of the manned lunar mission based on once LEO and twice LLO RVDs can be responded rapidly.