The Satellite Attitude Control System (ACS) is responsible for the control and injection phase of the satellite’s orbit where the angular velocities are extremely high until the ACS is able to drive the satellite to its normal mode of operation where the degree of pointing is extremely demanding compatible with the mission’s pointing requirements. The satellite ACS aims at determining and controlling the attitude of the satellite and often cannot be repaired in space. In that large-angle maneuvers phase the satellite dynamics is nonlinear and it can involve plant uncertainties. As a result, linear control techniques are unable to design the ACS that meet the mission requirements. In this paper one investigates the performance and robustness of the union of the SDRE (State-dependent Riccati Equation) and the H-Infinite (H∞) control techniques. This investigation developed a non-linear control algorithm with greater flexibility, which allows the space engineer to design an ACS with the balance between the performance of the SDRE technique with the robustness of the H∞ technique.