The traffic within the Cislunar region continues to grow, yielding an increasing demand for efficient techniques to determine the trajectory of a satellite in the circular restricted three-body problem (CR3BP). In this talk, we introduce a novel technique that incorporates interpolation with boundary conditions, presenting a low-complexity algorithm for efficient trajectory generation of a satellite in CR3BP. This offers a significant advantage over existing iterative techniques, demonstrating favorable results in terms of arithmetic complexities. Numerical results will be shown to indicate that the proposed algorithm exhibits favorable time complexity when generating trajectories for low-Lunar, Lyapunov, near-rectilinear halo, and distant retrograde orbits in comparison to the traditional iterative method-based trajectory generation.