Abstract
W ing rock is an oscillatory ro lling motion which arises at high angles of attack in aircraft with highly-swept wings. In the present paper, a method to suppress wing rock through sliding mode control is proposed. Sliding mode control is designed to min imize together roll angle error and co mmand input through a cost function. The procedure is performed on a wing-only analytical model, the controller is then applied to a complete wing-fuselage model. Simu lations include different angles of attack and robustness is assessed using a model altered by parametric d isturbances. Results are compared with the behavior obtained by a conventional roll damper.
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