Aero-elasticity is a major concern in aerospace field. It resultes from the interaction between the air-stream and the structure. Wing flutter is a well known problem of the aero-elasticity. It which occurs when the two lowest system eigenvalues (plunge and pitch motion) coalesce at a certain air speed known as the flutter speed. The increasing use of active material induced-strain actuation such as piezoelectric materials in suppression of structural vibrations has seen its extension to wing flutter control. Higher flutter speed and hence, a wider operating envelope was achieved by delaying the coalescence of these two eigenvalues. This delaying is obtained by adding more strain energy to the system as a result of the activation of the piezoelectric actuators. This paper models a simple beam under nominal aerodynamic loading conditions for the determination of analytically-derived onset of flutter speeds. Also shown in this paper is the effect of orientation of actuated piezoelectric patches on the shift of the flutter speed.


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    Title :

    Control of structural flutter using piezoelectric patches


    Additional title:

    Steuerung des Flügelflatterns unter Nutzung eines piezoelektrischen Korrekturprogrammes


    Contributors:
    Hariri, M. (author) / John, S. (author) / Trivallo, P. (author)


    Publication date :

    2009


    Size :

    9 Seiten, 8 Bilder, 2 Tabellen, 10 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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