Buckling analysis of a laminated composite plate with delaminations using the enhanced assumed strain solid shell element

Nonlinear Dynamics Analysis of FGM Shell Structures with a Higher Order Shear Strain Enhanced Solid-Shell Element

“…However, for the thickness strains, 33 c E , we adopt the ANS method as in Klinkel et al (1999), Vu-Quoc and Tan (2003) and Hajlaoui et al (2012Hajlaoui et al ( , 2015Hajlaoui et al ( , 2016 and evaluated at four collocation points defined in the reference surface ( ) …”

“…For the detailed description of the ANS method, refer to Hajlaoui et al (2012Hajlaoui et al ( , 2015Hajlaoui et al ( , 2016. The compatible part is arranged in (6x1) column matrix as follows 11 22 33 12 13 23…”

Buckling analysis of functionally graded materials structures with enhanced solid-shell elements and transverse shear correction

“…This formulation utilizes the standard first order shear deformation solid-shell finite element developed by Hajlaoui et al [22] where the transverse shear stresses are considered constant through the thickness. In this manner, the need for the shear correction factor is vital.…”

“…Klinkel et al [20] and Vu-Quoc and Tan [21], among many others, developed three-dimensional locking-free solidshell elements by using the EAS and ANS methods. In Hajlaoui et al [22], the authors presented a solid-shell finite element with an ANS method to resolve the shear locking effect and a nine parameters EAS method which avoided completely the volumetric locking to study the buckling behavior of laminated composite plate with delamination.…”

“…The aim of this paper is to extend the work of Hajlaoui et al [22] to develop an enhanced assumed solid-shell element based on the assumed natural strain and the enhanced strain method to investigate the behavior of FGM structures under buckling loads. Since FGM material are non-symmetric and it will be experiencing bending at the initial stage of loading under compressive load with simply supported boundary condition, therefore a suitable bending moment is applied to keep the plate flat under in-plane loading before buckling as proposed in Naderi and Saidi [36].…”