Dynamic modeling and control of the launchers utilized to fire munitions such as missiles and rockets become a significant field. When the launchers are allocated on the moving vehicles, their control, diminishing the thrust effect during the munition firing and preparing the system for a new shot within a short duration get more important. In this study, the control of a highly accurate two-degree-of-freedom electromechanically actuated launcher control system is investigated by considering the reduction of the impact effect caused by the munition firing. In this context, the two-loop cascaded control system is proposed. As the inner loop of this scheme is enrolled to provide the stabilization by taking the angular speed variables of the launcher in both azimuth and in elevation planes as control variables, its outer loop is designated to make the angular position control of the launcher. As comparison, the results of the computer simulations performed with the control systems regarding the computed torque and proportional -integral- derivative (PID) control action, and computed torque and sliding mode control in addition to the results of the cascaded control structure including computed torque and sliding mode control. Here, the computer simulations are carried out in the MATLAB SIMULINK environment.