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.
Buckling Analysis and Free Vibration of Composite Laminates Using Natural Element Method
AIAA Journal ; 57 , 3 ; 1303-1311
2019-01-08
9 pages
Article (Journal)
Electronic Resource
English
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|Buckling analysis of general composite laminates by hybrid-stress finite element method
Tema Archive | 1991
|Dynamic Delamination Buckling In Composite Laminates
NTRS | 1989
|