Approximation errors due to using reduced-order, instead of full-order, models in the nonlinear flutter problem of variable-stiffness composite laminates (VSCLs) are qualitatively and quantitatively discussed. These VSCLs are made of composite laminates with curvilinear fibers. A third-order shear deformation theory (TSDT) and a p -version finite element are used to model the laminate and discretize its displacements and rotations. The VSCLs are subjected to a supersonic airflow and the aerodynamic pressure is approximated using the linear piston theory. The equations of motion of the self-excited vibrational system are formed using the principle of virtual work. In this study, static condensation and/or a modal summation method are used to reduce the number of degrees of freedom of the full-order model. The equations of motion are solved using a method to calculate the amplitudes of limit-cycle oscillations (LCOs), and to study the dynamic responses, stresses, and damage indexes based on a failure criterion. Approximations are calculated for LCO amplitudes of VSCL plates with various boundary conditions, laminate thickness, and initial deflection (geometric imperfection). Viscous damping can have a major importance in this problem, and the approximation errors are discussed when viscous damping is included or excluded from the equations of motion.


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    Titel :

    Reduced-Order Models for Nonlinear Flutter of Composite Laminates with Curvilinear Fibers


    Beteiligte:
    Akhavan, Hamed (Autor:in) / Ribeiro, Pedro (Autor:in)

    Erschienen in:

    AIAA Journal ; 57 , 7 ; 3026-3039


    Erscheinungsdatum :

    01.07.2019




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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