Multi-Input/Multi-Output Sliding Mode Control for a Tailless Fighter Aircraft

A frequency-domain procedure for the design of sliding mode controllers for multi-input/multi-output systems is presented. The methodology accommodates the effects of parasitic dynamics, such as those introduced by unmodeled actuators through the introduction of multiple asymptotic observers and model reference hedging. The design procedure includes a frequency-domain approach to specify the sliding manifold, the observer eigenvalues, and the hedge model. The procedure is applied to the development of a flight-control system for a linear model of the Innovative Control Effector fighter aircraft. The stability and performance robustness of the resulting design is demonstrated through the introduction of significant degradation in the control effector actuators and variation in vehicle dynamics.