In Earth-Moon low-energy transfers, the strict geometric constraints among the
Sun, Earth, and Moon often complicate trajectory redesign when the original
transfer window is missed. To address this issue, this paper presents a
nominal-trajectory-based reconstruction method for Earth-Moon low-energy
transfers. Using the original mission trajectory as the reference, the method
fixes the middle arc and performs segmented reconstruction that combines
position targeting with velocity matching, so that only the escape and lunar
insertion phases are locally corrected. This approach enables rapid trajectory
reconstruction, efficient search for feasible launch windows, and evaluation of
the corresponding velocity increment. Following this strategy, the existence and
distribution of feasible solutions are examined on the hour, day, month, and
year timescales. Simulation results show that feasible transfer windows with
relatively low cost still exist within approximately four to six hours before or
after the nominal window. Once the departure time shifts by one day, the total
velocity increment rises sharply, and local reconstruction is no longer
engineering-feasible. After waiting for about one synodic month, feasible
windows reappear, and the required velocity increment falls back within the 200
m/s threshold. Within a one-year range around the nominal epoch, the feasible
windows exhibit an overall periodic pattern that repeats approximately every 27
days. The proposed method provides a reference for trajectory reconstruction
after a missed transfer window.