This paper has presented a technique for the determination of an optimal configuration of fuselage mounted piezoelectric actuators for active structural acoustic control of interior noise in aircraft. The technique has demonstrated much potential in preliminary experiments where actuators were configured to couple into the first principal component of the acoustically coupled fuselage vibration. In this test, average reductions of 6 dB at the error microphones and 4 dB at five auxiliary microphones were observed for a pure tone disturbance at the left forward engine pylon of a business jet. This disturbance was used to simulate an oscillating force due to engine unbalance.


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    Title :

    Piezoelectric Actuator Configuration Optimization for Active Structural Acoustic Control in Aircraft


    Additional title:

    Sae Technical Papers


    Contributors:

    Conference:

    General, Corporate & Regional Aviation Meeting & Exposition ; 1997



    Publication date :

    1997-05-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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