Wing rock is a highly nonlinear phenomenon in which the aircraft undergoes limit cycle roll oscillations at high angles of attack. A single neuron control scheme for suppression of wing rock of slender delta wings is presented. The effectiveness of the control scheme is demonstrated through software simulation and real-time control experiments in a wind tunnel on a 80/spl deg/ swept back wing. The suppression of the limit cycle is achieved in presence of control saturation. The robustness of the scheme is demonstrated by the suppression of the wing rock at various initial conditions and different angles of attack.
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