A family of simple and robust finite elements for linear and geometrically nonlinear analysis of laminated composite plates

Zhang, Y. X. and Yang, C. H. 2006, A family of simple and robust finite elements for linear and geometrically nonlinear analysis of laminated composite plates, Composite structures, vol. 75, no. 1-4, pp. 545-552.

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Title A family of simple and robust finite elements for linear and geometrically nonlinear analysis of laminated composite plates
Author(s) Zhang, Y. X.
Yang, C. H.
Journal name Composite structures
Volume number 75
Issue number 1-4
Start page 545
End page 552
Publisher Elsevier
Place of publication Amsterdam, The Netherlands
Publication date 2006-09
ISSN 0263-8223
1879-1085
Keyword(s) flat plate/shell element
laminate composite plates
first-order shear deformation theory
Timonshenko’s beam functions
shear-locking
Summary A family of simple, displacement-based and shear-flexible triangular and quadrilateral flat plate/shell elements for linear and geometrically nonlinear analysis of thin to moderately thick laminate composite plates are introduced and summarized in this paper.

The developed elements are based on the first-order shear deformation theory (FSDT) and von-Karman’s large deflection theory, and total Lagrangian approach is employed to formulate the element for geometrically nonlinear analysis. The deflection and rotation functions of the element boundary are obtained from Timoshenko’s laminated composite beam functions, thus convergence can be ensured theoretically for very thin laminates and shear-locking problem is avoided naturally.

The flat triangular plate/shell element is of 3-node, 18-degree-of-freedom, and the plane displacement interpolation functions of the Allman’s triangular membrane element with drilling degrees of freedom are taken as the in-plane displacements of the element. The flat quadrilateral plate/shell element is of 4-node, 24-degree-of-freedom, and the linear displacement interpolation functions of a quadrilateral plane element with drilling degrees of freedom are taken as the in-plane displacements.

The developed elements are simple in formulation, free from shear-locking, and include conventional engineering degrees of freedom. Numerical examples demonstrate that the elements are convergent, not sensitive to mesh distortion, accurate and efficient for linear and geometric nonlinear analysis of thin to moderately thick laminates.
Notes Paper presented at the International Conference on Composite Structures (13th : 2005 : Monash University, Melbourne)
Language eng
Field of Research 091202 Composite and Hybrid Materials
HERDC Research category C1.1 Refereed article in a scholarly journal
Copyright notice ©2006, Elsevier Ltd.
Persistent URL http://hdl.handle.net/10536/DRO/DU:30025965

Document type: Journal Article
Collection: School of Engineering
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