the design of autonomous systems is a growing research field which attract an increasing interest in various civilian and military applications. The design of control system can be considered a leading factor for developing any autonomous system. In this paper devoted to a missile autopilot which should achieve specific characteristics and performance criteria to ensure the overall system stability to track the desired commands in the presence of high dynamics and different uncertainties with high accuracy. The investigation of accurate missile 6DOF model is developed and linearization has been performed for designing the proper controllers for the pitch and roll channels and choose the optimum trim points based on system dynamic pressure. A design of lead compensator classical controller is presented to meet certain requirement of both time and frequency characteristic to ensure the system stability. The designed autopilot is evaluated using Matlab simulation is carried out for evaluating the proposed missile autopilot controller performance, the proposed controller presented sufficient performance during flight and