Abstract: To address the design of transfer orbit from Distant Retrograde Orbit (DRO) to lunar circular orbit, a high-precision, computationally efficient and reliable method suitable for engineering applications was proposed. Based on a high-precision dynamic model, the impacts of orbital maneuver velocity increment, DRO orbital phase at maneuver time, and DRO selenocentric distance on the transfer orbit were quantitatively analyzed. Taking high-precision quantitative results as pre-generated empirical data and integrating them with analytical calculation, accurate computation of initial iteration values for design parameters was achieved, thus enabling the efficient solution of the transfer orbit design problem. Case study verification demonstrated that the proposed method was efficient and reliable with calculation completed within seconds. Quantitative analysis results and the proposed design method in this paper can provide technical reference for engineering applications.