In ground-to-ground military engagements, launchers used in land vehicles play an important role for armies. In application, orienting missiles and rockets which are fired from the land vehicles and finally hitting the intended targets with high accuracy are issues that should be taken into consideration. In order to attain this goal, it is vital that an effective control algorithm be designed. As proven several times, the most robust and reliable control systems can be designed in a model-based manner. Namely, the governing dynamic equations of motion of the intended system should be derived. In this study, the differential equations of motion of an electromechanically actuated launcher are presented regarding its motion in both azimuth and elevation axes and closed-form expressions are put so as to make a control system design.