Pursuing an alternative and effective numerical approximate method for structural analysis problems is always a demanding task for aerospace application. A natural element method is described in this paper. This method has the advantage of circumventing the difficulties of the mesh division and mesh dependency problems over existing finite element method methods. It also exhibits an automatic and optimal choice for the shape function and the imposition of essential boundary conditions as compared with other meshless methods, thus making it a robust method for solving mechanics problems such as buckling analysis and the free vibration of composite structures. The critical buckling loads and natural frequencies with their associated modes for several composite plates are determined, and the results are compared to the analytical solutions based on the first-order shear deformation theory. The proposed method is proved to have a good computational accuracy for composite plate analysis with various boundary conditions, thus demonstrating the fitness and flexibility of this approach and a promising perspective for solving structural analysis problems of composite structures.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Buckling Analysis and Free Vibration of Composite Laminates Using Natural Element Method


    Contributors:

    Published in:

    AIAA Journal ; 57 , 3 ; 1303-1311


    Publication date :

    2019-01-08


    Size :

    9 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English






    Free vibration and buckling of symmetric cross-ply rectangular laminates

    Yu, S. D. / Cleghorn, W. L. / Fenton, R. G. | AIAA | 1994



    Dynamic Delamination Buckling In Composite Laminates

    Grady, Joseph E. / Chamis, Christos C. / Aiello, Robert A. | NTRS | 1989