The goal of this study is the multi-mode structural vibration control in the composite fin-tip of an aircraft. Structural model of the composite fin-tip with surface bonded piezoelectric actuators is developed using the finite element method. The finite element model is updated experimentally to reflect the natural frequencies and mode shapes accurately. A model order reduction technique is employed for reducing the finite element structural matrices before developing the controller. Particle swarm based evolutionary optimization (PSO) technique is used for optimal placement of piezoelectric patch actuators and accelerometer sensors to suppress vibration. Hinfinity based active vibration controllers are designed directly in the discrete domain and implemented using dSpace(registered trademark) (DS-1005) electronic signal processing boards. Significant vibration suppression in the multiple bending modes of interest is experimentally demonstrated for sinusoidal and band limited white noise forcing functions.


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    Title :

    Experimental demonstration of Hinfinity control based active vibration suppression in composite fin-tip of aircraft using optimally placed piezoelectric patch actuators


    Additional title:

    Experimenteller Nachweis der Steuerung von H<sub>unendlich</sub> basierend auf einer aktiven Vibrationsunterdrückung in den Verbund-Flossenspitzen eines Flugzeugs durch optimal positionierte piezoelektrische Aktoren


    Contributors:


    Publication date :

    2008


    Size :

    19 Seiten, 31 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




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