Flight control system design with high order sliding modes for nonlinear aircraft model

In this paper, an aircraft robust flight control system design is studied via high order sliding mode techniques with parameter uncertainties in flight speed, altitude, aerodynamic coefficients without any reconfiguration of control parameters. Complete nonlinear six degree of freedom flight dynamics model is built for a conventional aircraft in state space. Control commands are assumed to be aileron deflection of wings, elevator deflections of horizontal stabilizers, rudder deflection of vertical fin, trust input of jet-engine/propeller. Twisting and super-twisting algorithms are considered and compared to illustrate effectiveness of each control system on nonlinear aircraft dynamics for different flight conditions.