Sliding mode control for the fin actuation mechanism

The flight of the guided missiles mainly depend on the actuator's dynamic performance and the deflection rate capability of the control surfaces or fins. To obtain the desired flight performance, the actuators need to control these fins with high accuracy and agility along with the controllable and reliable response. This paper mainly deals with the robust control of the fin actuation mechanism of the tail fin controlled missiles. A sliding mode control is proposed here using first order sliding mode (FOSM). The proposed controller is compared with the PID controller.