Progressive damage modeling of an adhesively bonded unidirectional composite single-lap joint in tension at the mesoscale level

This study investigates initiation and propagation of damage zones in the composite plates of an adhesively bonded single-lap joint in tension at the mesoscale level. A set of material degradation rules is applied to the mechanical properties of each failed ply of the plates based on the Hashin failure criterion. The von Mises stress concentrates along the free edges of the adhesive layer and the corresponding lower and upper plate regions and peaks along the free edges of the adhesive-plate interfaces. Consequently, the damage initiates at the lower plate interface to the adhesive layer and propagates in the first ply along this adhesive free edge, and then spreads through the neighboring plies of the lower plate in a similar failure mechanism. The damage in the lower plate occurs in the matrix, delamination, and fiber-matrix failure modes, and the first ply-failure loads decrease significantly with increasing ply fiber angle. Tension tests showed that the adhesive joints with ply lay-ups between [0](10) and [15](10) fails through the adhesive layer, and the lower plates with larger fiber angles break along the free edge of the lower plate-adhesive interface whereas the adhesive layer is still intact. The adhesive failure is interfacial around the adhesive free edges and is through the adhesive in the middle of the overlap region in the joints with the ply lay-ups [0](10). Although a similar failure mechanism is observed in the ply lay-up [15](10), the damage zones in the first ply of the lower plate in which the matrix and fibers are damaged, are distributed in the overlap region. The damage is initiated in the first ply of the lower plate of th

Progressive damage modeling of an adhesively bonded composite single lap joint under flexural loads at the mesoscale level

This study investigates initiation and propagation of damage zones in the composite plates of an adhesively bonded single lap joint under flexural loads at the mesoscale level based on Tsai-Wu and Hashin failure criteria. The damage zones were evaluated in the unidirectional composite plates with ply lay-ups [0]10, [15]10, ... , [90]10. The mechanical properties of each failed ply of the upper and lower plates were modified based on a set of material degradation rules. Due to stress concentrations along the free edges of the adhesive layer and in the corresponding zones of the lower and upper plates, the peak stresses appeared along the left free edge of the upper plate-adhesive interface. Both failure criteria showed that the damage initiated in the first ply of the upper plate interface to the adhesive layer and propagated through this ply along this adhesive free edge, and then expanded through the neighboring plies in a similar failure mechanism. Hashin failure criterion predicted that the matrix and delamination failure modes were dominant in the upper plate, and higher first ply-failure loads and joint failure loads decreased significantly with increased ply fibre angle for the Tsai Wu failure criterion. The SEM photographs of the adhesive fracture surfaces due to three- and four-point bending tests showed that the local failure initiated inside the adhesive fillet and propagated along the upper plate adhesive interface. In addition, the interfacial adhesive failure and the partial damage in the first ply of the upper plate appeared for the ply lay-ups between [0]10 and [30]10 whereas the upper plates with larger fiber angles failed through the matrix of the upper plate in the fiber direction and a triangular adhesive bonding region, which decreases with increasing fiber angle. The interfacial adhesive failure is more apparent along the left free edge of the upper plate adhesive interface whereas the damage propagation is observed through both the adhesive layer and all plies from the interface to the top of the upper plate. Both failure criteria could predict reasonably the initiation and propagation of the damage zones in the composite plates of the adhesive joints, whereas the first ply failure and joint failure loads were underestimated since the non-linear adhesive model, non-linear matrix shear behavior, and geometrical non-linearity were not taken into account in the present analysis