Integral Sliding-Mode Control with Applications to Aircraft Dynamics

Abstract

A Continuous Sliding-Mode Controller (CSMC) using integral action is implemented to control the response of the longitudinal dynamics of an aircraft. Model-following of the pitch rate q is obtained through this method. Asymptotic regulation achieved by integral control has its downsides because transient performance is reduced. A solution to this problem consists in using the integral action only “conditionally”, thus eliminating the performance downgrade. Finally a comparison will show how Sliding-mode control will minimize the chattering phenomenon and also reduce “integrator windup” problem, thus minimizing the loss of transient performance.