Actively twisting the entire rotor blade is being investigated as an approach to reduce helicopter vibration and noise. In the present work, an induced shear piezoelectric tube is analytically evaluated as an active blade twist actuator. A finite element model of the induced shear actuator and rotor blade is used to guide the designs of the induced shear tube for small scale and full scale rotor blade applications. The finite element analysis indicates that a 48 inch long tube actuator generates a tip twist of +/-1.1 degree in a full scale blade and an 18 inch long actuator produces a tip twist of +/-1.40 degree for a small scale blade. The performance of the induced shear actuator is compared to the state of the art in active twist actuators. The results indicate that the induced shear tube shows promise as an active blade twist actuator.


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    Titel :

    Induced-shear piezoelectric actuators for active twist rotor blades


    Beteiligte:
    Centolanza, L.R. (Autor:in) / Smith, E.C. (Autor:in)


    Erscheinungsdatum :

    2002


    Format / Umfang :

    11 Seiten, 37 Quellen


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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