A minimax control design aimed at augmenting the flutter envelope and enhancing the dynamic aeroelastic response of a smart aircraft wing subject to gust/blast loads is presented. The smart aircraft wing is modeled as an anisotropic thin-walled beam featuring circumferentially asymmetric stiffness lay-up and a number of non-classical effects such as transverse shear, warping restraint and 3-D strain effects. Adaptive materials technology is used for implementing the active control via the boundary bending moment feedback mechanism. The unsteady aerodynamic loads in subsonic compressible flows are based on 2-D indicial functions considered in conjunction with aerodynamic strip theory extended to 3-D wing model. The capability of control on flutter suppression and dynamic response enhancement are investigated, the corresponding applied voltage requirement and power consumption are addressed.


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    Title :

    Aeroelastic vibration feedback control of smart aircraft wings in subsonic flight speeds


    Contributors:

    Conference:

    Smart Structures and Materials 2002: Smart Structures and Integrated Systems ; 2002 ; San Diego,California,United States


    Published in:

    Publication date :

    2002-07-15





    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English