control of limit cycle oscillation in a three degrees of freedom airfoil section using fuzzy takagi-sugeno modeling

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ID: 239838
2014
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Abstract
This work presents a strategy to control nonlinear responses of aeroelastic systems with control surface freeplay. The proposed methodology is developed for the three degrees of freedom typical section airfoil considering aerodynamic forces from Theodorsen’s theory. The mathematical model is written in the state space representation using rational function approximation to write the aerodynamic forces in time domain. The control system is designed using the fuzzy Takagi-Sugeno modeling to compute a feedback control gain. It useds Lyapunov’s stability function and linear matrix inequalities (LMIs) to solve a convex optimization problem. Time simulations with different initial conditions are performed using a modified Runge-Kutta algorithm to compare the system with and without control forces. It is shown that this approach can compute linear control gain able to stabilize aeroelastic systems with discontinuous nonlinearities.
Reference Key
bueno2014shockcontrol Use this key to autocite in the manuscript while using SciMatic Manuscript Manager or Thesis Manager
Authors ;Douglas Domingues Bueno;Luiz Carlos Sandoval Góes;Paulo José Paupitz Gonçalves
Journal Nano letters
Year 2014
DOI
10.1155/2014/597827
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