This thesis presents an approach based on Dynamical Systems Theory (DST) for interplanetary orbit insertion maneuvers into Saturn-Titan three-body orbits. DST is used to identify invariant manifolds that guide the spacecraft into a candidate Titan-centered three-body orbit, chosen based on scientific value. Then, Particle Swarm Optimization (PSO) is performed to optimize insertion parameters, minimizing $\Delta V$. The proposed method achieves reduced $\Delta V$ compared to conventional methods (e.g., patched conics-based flybys), although leading to longer times of flight. This thesis serves as an interplanetary mission planning methodology to optimize spacecraft trajectories for the exploration of the Saturn-Titan system.