Vertical launched missile has highly nonlinearity and control deficiency at boost-phase because of its high angle of attack maneuver and low velocity. The purpose of this thesis is to design the autopilot with aerodynamic fin and thrust vectoring control by reflecting these system characteristics.
In this paper, modeling is performed based on the configuration of operating missile by using Missile DATCOM program. To analyze the model and maneuvering characteristics, trajectory optimization technique is introduced. Two control systems are designed, that are angle of attack controller which uses the command resulted from trajectory optimization and the pitch rate controller which follows real-time guidance command. Control techniques used in this research are the linear control using pole placement approach with gain scheduling method and the sliding mode control which is good for model uncertainty and nonlinearity. Because of little control power of aerodynamic fin at high angle of attack and low dynamic pressure, thrust vectoring control (TVC) system is developed and the control allocation is performed to cover all flight envelop. The 6-DOF simulation results can analyze and verify performances and capabilities of each control system.