Aiming at the demand of contingency return at any time during the Earth-Moon transfer in a crewed lunar mission, this paper presents an approach to design an optimal two-impulse abort trajectory based on the quasi-lambert problem. An optimization model is first established by defining the maneuvering point’s position variables. For a solution in the optimization process, the strict entry interface constraint is analytically satisfied by solving a quasi-lambert problem. In contrast to the past method, it offers a more efficient and simpler way to get the initial solution. Then the exact solution with a high-fidelity gravitational model is achieved by differential correction. Finally, the design variables are optimized quickly and the performance of the proposed method is verified by numerical simulation. The results indicate that the proposed method is effective and has a higher efficiency than the method in literature by applying the quasi-lambert problem. Furthermore, the characteristics of the two-impulse abort trajectory are studied expeditiously. The research findings can provide a tool and reference for the design of the two-impulse abort trajectory in engineering.