Control of limit cycle oscillations of a two-dimensional aeroelastic system

M. R. Hajj, M. Ghommem, A. H. Nayfeh

Research output: Contribution to journalArticlepeer-review

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Abstract

Linear and nonlinear static feedback controls are implemented on a nonlinear aeroelastic system that consists of a rigid airfoil supported by nonlinear springs in the pitch and plunge directions and subjected to nonlinear aerodynamic loads. The normal form is used to investigate the Hopf bifurcation that occurs as the freestream velocity is increased and to analytically predict the amplitude and frequency of the ensuing limit cycle oscillations (LCO). It is shown that linear control can be used to delay the flutter onset and reduce the LCO amplitude. Yet, its required gains remain a function of the speed. On the other hand, nonlinear control can be effciently implemented to convert any subcritical Hopf bifurcation into a supercritical one and to significantly reduce the LCO amplitude.

Original languageEnglish
Article number782457
JournalMathematical Problems in Engineering
Volume2010
DOIs
StatePublished - 2010

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