This research aims to optimize ascent trajectories for satellite launches into Sun-Synchronous Orbits (SSO) while minimizing propellant usage during launch to maximize payload capacity. The study evaluates various launch sites and directions, incorporating the multi-stage dynamics of the launch vehicle to accurately model the ascent trajectories and different mission launch times to evaluate performance in regard to the final local time of the ascending node (LTAN) that the insertion orbit should have. The optimization technique employs an indirect method rooted in optimal control principles and Pontryagin's Maximum Principle, aiming to identify a trajectory that maximizes the Hamiltonian, thereby minimizing propellant use.