Sliding Mode Controller Design for an Aircraft Pitch Rate Track System

Sliding mode control is valued for their robust accommodation of uncertainties and their ability to reject disturbance. In this study, Sliding mode control is applied to the design of a pitch rate track system for a nonlinear model of an aircraft. To minimize control chattering which is the characteristic of sliding mode control, a thin boundary layer is incorporated around the sliding surface. The simulation result demonstrates that the proposed controller can be effectively applied to an aircraft pitch rate track system.