Quality and performance of the Aeronautical Industry products are of extreme importance. In the context of the aeroelasticity, the continuous demand for lighter and, consequently, more flexible structures, increases the susceptibility to aeroelastic vibrations. Therefore, the study of aeroelastic phenomena and the development of theoretical and experimental techniques of aeroelastic analysis have attracted the attention of researchers. Aerospace structures must be submitted to some form of verification before the flight, to assure that the aircraft is free of any aeroelastic instability phenomenon, which may provoke structural fatigue problems or its failure. One of the more important instability phenomena is flutter, a dynamic aeroelastic phenomenon that can lead to the destruction of the aircraft. Currently the research in this area points in the direction of developing technology that allows on-line identification of modal parameters associated to flutter. In Rebolho (2006) an algorithm for on-line identification of modal parameters of an aluminum plate was applied, where satisfactory results were achieved, proving the efficiency of the method for on-line identification. In this way, the main objective of this project is to accomplishment on-line experimental identification of modal parameters involved in flutter phenomenon. A flexible mounting system associated with a rigid wing model in a tunnel will be carried out the wind Laboratory of Aeroelasticity of EESC-USP.
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