Abstract: In this paper, a hierarchical reconstruction modeling method and a two-layer optimization algorithm based on discrete orbit data were proposed to solve the multi-pulse orbit transfer problem under the Earth-Moon circular restricted three-body model. The minimum pulse problem was reconstructed and modeled as a two-layer optimization problem, and the two-layer optimization algorithm was given to realize the transfer orbit design. The upper layer optimization problem took the discrete orbit data constraints into account, and the algorithm adopted intelligent algorithm to make it universal and achieve computational efficiency. The lower optimization problem only optimized the pulse sequence under the constraints of start-end state constraints, time constraints, pulse constraints and pulse point constraints, so as to avoid the sensitivity to the initial value. The algorithm can obtain the local optimal solution by sequential quadratic programming. Through simulation verification in various scenarios, it can be concluded that the two-layer optimization modeling framework and solution algorithm proposed in this paper are suitable for different types of orbit transfer, and can achieve multi-pulse energy optimal transfer. Comparison simulation is of great significance to transfer orbit design between special orbits in the Earth-Moon three-body system.