Variable Structure H(inf.) Controller for Aircraft

This paper proposes a new synthesis method and tuning procedure for a variable structure H∞ multivariable controller for fixed wing aircrafts attitude control, which consists in switching from one-degree of freedom controller (1-DOF) to two degrees of freedom controller (2-DOF), and vice versa, with a method for bump-less transfer in switching transitions . The proposed method is tested using robustness analysis based on frequency domain and time analysis computer simulations based on a nonlinear mathematical model of the F-16 aircraft published by the NASA, from which satisfactory results are obtained.