Robust Analysis of Active Flutter Suppression Using Multiple Control Surfaces via Second-Order Controllers

The robust stability of an active flexible wing section with leading- and trailing-edge control surfaces is further investigated via the μ -method. Motivated by a more detailed servo control dynamics, the two controllers K1 and K2, which command the deflections of the trailing-edge flap and the leading-edge flap respectively, are modeled as two second-order shock absorbers in this study. The nominal and robust stability margins, modal properties, critical flutter airspeeds and frequencies are computed to predict the flutter of a nonlinear aeroelastic system and to investigate the aeroservoelastic stability in the μ -framework. The simulation results are compared with the previous study of which the controllers were modeled as the simplified (first-order) shock absorbers. The improved sensitivity to detect the control-structure coupling is observed by applying the second-order shock absorbers in the ASE model.

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See papers presented at AeroTech Congress & Exhibition, September 2007, Los Angeles, CA, USA, Session: Certification and Vehicle Control Issues

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