In order to meet the large-range maneuvering requirements of manned lunar exploration in the future， four plans of low-altitude flight， high-altitude flight， ballistic flight and re-entry flight on the lunar surface are established. On this basis， a mathematical model is built to describe the relationship between parameters in each stage of the flight process. In order to reach the minimum propellant consumption， the optimal parameters of the four flight modes are calculated and analyzed. The investigations show that the consumption of propellant （liquid hydrogen & liquid oxygen） for a manned 1 000 km round trip is 1 403 kg for a ballistic flight， 2 160 kg for a low-altitude flight， 2 349 kg for a high-altitude flight， and 3 617 kg for a re-entry flight. Considering the factors such as flight scale， program feasibility， and technical difficulty， it is recommended to use the lunar low-altitude flight mode for 1 000 km large-range lunar surface maneuvers. This research can provide a technical foundation and technical support for the large-range detection of the manned lunar landing in the future.