CONTROL OF A WING SE CTION WITH STRUCTURA L NONLINEARITIES USING LEADING AND TRAILIN G EDGE CONTROL SURFACES

Herein, the authors describe theoretical, analytical, and experimental studies of nonlinear responses due to structural sources and the control thereof. Motivated by the limited effectiveness of using a single, trailing edge control surface, th e suppression of limit cycle oscillations (LCOs) is investigated using a wing section with both a leading and trailing edge control surface. A feedback linearization approach is taken by transforming the system equations of motion via Lie algebraic method s and an adaptive control strategy, based on a model reference approach, is incorporated to account for inexact cancellation of nonlinear terms, in particular, those found in the pitch stiffness. It is shown through development of theory, simulations, and experiment that by using two control surfaces, a globally stabilizing controller may be achieved.

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