Output feedback-based discrete-time sliding-mode controller design for model aircraft

A sliding-mode controller is designed for model aircraft with output feedback and dynamic compensation using a novel sliding function. The control law is derived for discrete-time implementation using the equivalent control approach for existence of a quasi-sliding mode. The matrices characterizing the switching surfaces are user-chosen and conditions are imposed on the system matrices. The algorithm is applied to design a pitch controller for an aircraft having controllable elevator and thrust deflections.