Stabilizer Autopilot Design For Fixed Wing UAV Using ODSMC

Abstract

In this paper we build an ODSMC (Output Feedback Discrete Time Sliding Mode Control) controller for a fixed-winged aircraft. ODSMC control is employed, which is widely utilized in commercial and reconnaissance applications. The small-disturbance theory is used to obtain the mathematical model of the system which has highly nonlinear and non minimum characteristics. The ODSMC, due to its dynamic structure has been proved to be better than conventional linear controllers. Because of its output feedback structure, it also eliminates the need for a state observer. The ODSMC is designed based on the obtained linear model of the given plant. The effectiveness of the aircraft control system is analyzed by means of numerical simulations. The ODSMC control algorithm gives quite satisfactory results regarding the disturbance rejection capability of the closed loop system.