The vibrational behavior of cantilevered aircraft wings modeled as thin-walled beams and incorporating piezoelectric effects is studied. Based on the converse piezoelectric effect, the system of piezoelectric actuators conveniently located on the wing yield the control of its associated vertical and lateral bending eigenfrequencies. The possibility revealed by this study enabling one to increase adaptively the eigenfrequencies of thin-walled cantilevered beams could play a significant role in the control of the dynamic response and flutter of wing and rotor blade structures.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Vibrational behavior of adaptive aircraft wing structures modelled as composite thin-walled beams


    Contributors:
    Song, O. (author) / Librescu, L. (author) / Rogers, C. A. (author)


    Publication date :

    1992-09-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English