The recently derived structured model reference adaptive control (SMRAC) method is considered for the active suppression of limit cycle oscillations for a typical wing section with a structural nonlinearity. The SMRAC method uses the specific structure of the equations of motion governing general mechanical systems. This adaptive control method is implemented and tested in wind tunnel experiments to validate the performance. For comparison, results obtained with adaptive feedback linearization are also presented. It is shown that the derived SMRAC is advantageous in that it suppresses limit cycle oscillations at higher velocities, and also it can rigorously treat actuator saturation a priori.
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