Robust Sliding Mode Controller Design for the Complete Model of an Aircraft in the Presence of a Variety of Uncertainties

In this paper a robust flight control system is designed for the complete model of a six-degree-of-freedom nonlinear aircraft, without the need to reset the controller parameters and reconfigure it. To do this, a sliding mode controller has been used as one of the modern methods in robust control. Ensuring global and asymptotic robust aircraft stability using Lyapunov theory, in the presence of parametric uncertainties due to changes in flight speed, changes in aircraft altitude, as well as uncertainties due to external disturbances such as wind force, as well as uncertainties related to Inaccurate modeling of aerodynamic coefficients has been performed. The issue of saturation as well as the maximum rate of change of the output of the actuators is also taken into account to ensure that this method can be implemented practically. Finally, several simulations have been performed with different practical considerations to show the efficiency of the proposed method in different flight conditions.