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Active Flutter Suppression in a 2-D Airfoil Using Linear Matrix Inequalities
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TLDR
In this paper, the authors used linear matrix inequalities (LMIs) techniques to design an active state-feedback control to suppress flutter, which is a potentially destructive instability resulting from an interaction between aerodynamic, inertial, and elastic forces.Abstract:
Flutter is an in-flight vibration of flexible structures caused by energy in the airstream absorbed by the lifting surface. This aeroelastic phenomenon is a problem of considerable interest in the aeronautic industry, because flutter is a potentially destructive instability resulting from an interaction between aerodynamic, inertial, and elastic forces. To overcome this effect, it is possible to use passive or active methodologies, but passive control adds mass to the structure and it is, therefore, undesirable. Thus, in this paper, the goal is to use linear matrix inequalities (LMIs) techniques to design an active state-feedback control to suppress flutter. Due to unmeasurable aerodynamic-lag states, one needs to use a dynamic observer. So, LMIs also were applied to design a state-estimator. The simulated model consists of a classical flat plate in a two-dimensional flow. Two regulators were designed, the first one is a non-robust design for parametric variation and the second one is a robust control design, both designed by using LMIs. The parametric uncertainties are modeled through polytopic uncertainties. The paper concludes with numerical simulations for each controller. The open-loop and closed-loop responses are also compared and the results show the flutter suppression. The perfomance for both controllers are compared and discussed. Keywords : Flutter, active control, LMI, polytopic uncertainties, robustnessread more
Citations
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Journal ArticleDOI
Novel Nonlinear Control Design for a Two-Dimensional Airfoil Under Unsteady Flow
TL;DR: In this article, a partial state feedback continuous adaptive controller is proposed to suppress the aeroelastic vibrations of the wing section model, and the control design with respect to an appropriately chosen output variable yields an asymptotic stability result for all three of the pitching, plunging, and flapping degrees of freedom.
Journal ArticleDOI
Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
TL;DR: In this paper, a strategy to control nonlinear responses of aeroelastic systems with control surface freeplay is presented for the three degrees of freedom typical section airfoil considering aerodynamic forces from Theodorsen's theory.
Proceedings ArticleDOI
A mixed H2/Hx scheduling control scheme for a two degree-of-freedom aeroelastic system under varying airspeed and gust conditions
TL;DR: In this article, a two-degree-of-freedom aeroelastic system with a torsional stiness nonlinearity is considered and a controller in LFR is synthesized using Linear Matrix Inequalities.
Journal ArticleDOI
Discussion on “Active aeroelastic control of 2-D wing-flap systems operating in an incompressible flowfield and impacted by a blast pulse” by Librescu et al., Journal of Sound and Vibration 283 (3–5) (2005) 685–706
Journal ArticleDOI
A new approach for modeling and control of nonlinear systems via norm-bounded linear differential inclusions
TL;DR: In this paper, a linear control design approach for nonlinear systems using norm-bounded linear differential inclusions (NLDIs) is proposed, where the authors use the mean-value theorem to represent the nonlinear system by a linear parameter-varying model, which is then mapped into a polytopic linear differential inclusion (PLDI) within the region of interest.
References
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