Structural cohesive element for the modelling of delamination in composite laminates without the cohesive zone limit

Abstract

Delamination is a critical mode of failure that occurs between plies in a composite laminate. The cohesive element, developed based on the cohesive zone model, is widely used for modeling delamination. However, standard cohesive elements suffer from a well-known limit on the mesh density-the element size must be much smaller than the cohesive zone size. This work develops a new set of elements for modelling composite plies and their interfaces in 3D. A triangular Kirchhoff-Love shell element is developed for orthotropic materials to model the plies. A structural cohesive element, conforming to the shell elements of the plies, is developed to model the interface delamination. The proposed method is verified and validated on the classical benchmark problems of Mode I, Mode II, and mixed-mode delamination of unidirectional laminates, as well as on the single-leg bending problem of a multi-directional laminate. All the results show that the element size in the proposed models can be ten times larger than that in the standard cohesive element models, with more than 90% reduction in CPU time, while retaining prediction accuracy. This would then allow more effective and efficient modeling of delamination in composites without worrying about the cohesive zone limit on the mesh density.

Figures (13)

• Figure 1: Geometrical comparison between conventional CE and structural CE
• Figure 1: Analytical solution of SLB model
• Figure 2: Coordinate system and DoFs for the triangular cubic plate element allman1976simple
• Figure 2: Beam model of SLB specimen ($a<L$)
• Figure 3: Sign conventions for shear force and bending moment resultants