An aeroelastic model is developed by using multivariable solid-shell elements. Geometrical nonlinearity and the elimination of corresponding locking phenomena are considered accurately in the modeling. Unsteady aerodynamic forces are addressed by solving Euler flow dynamic equations. The computational-structural-dynamics solver is loosely coupled to the computational-fluid-dynamics solver, and the full match of the computational structural dynamics and computational fluid dynamics interfaces is achieved by three-dimensional modeling. An interpolation method using finite-element shape functions is developed to transform forces from aerodynamic grids to structural grids. The aerodynamic mesh deformation is obtained by using radial basis functions combined with the transfinite interpolation method. The aeroelastic model is validated through the study of the flutter and the limit cycle oscillation of a cropped delta wing in transonic flow. Moreover, the establishment of the aeroelastic model using multivariable solid shell elements is compared with other modeling methods. Improved numerical results show that the multivariable finite-element method is an efficient and capable tool for simulating geometrical nonlinearity, and the developed three-dimensional data-exchange method also plays a key role in the nonlinear aeroelastic modeling.


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    Titel :

    Aeroelastic Modeling Using Geometrically Nonlinear Solid-Shell Elements


    Beteiligte:
    Chen, Tao (Autor:in) / Xu, Min (Autor:in) / Xie, Liang (Autor:in)

    Erschienen in:

    AIAA Journal ; 52 , 9 ; 1980-1993


    Erscheinungsdatum :

    2014-05-30


    Format / Umfang :

    14 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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