Abstract: A multi-maneuver approach to transition from Lunar Frozen Orbit (LFO) to a cislunar L2 Near Rectilinear Halo Orbit (NRHO) was expected in this research. LFO was predicted to be utilized to provide the navigation or communication platform for lunar exploration. They are long-term stable orbits with constant orbital elements on average. Subsets of Halo orbit families, known as NRHO, are orbits that are nearly stable. Due to their important locations in cislunar space, the L2 NRHO are considered as possible launching platforms for deep space or lunar exploration mission. For upcoming cislunar space exploration missions, the low fuel consumption transfer approach between these orbits is very valuable. Utilizing the maximum stretching direction to determine the insertion maneuver, the spacecraft may rapidly approach NRHO. In order to optimize the transfer orbits, a nonlinear programming problem was developed. The optimization results with different transfer windows in the high-fidelity model were given for the transfer from LFO to NRHO, which demonstrated the reliability of the proposed strategy.