Abstract
The aim of this study is to investigate the effect of the adherend material on the mode I fracture behaviour of bi-material composite bonded joints. Both single-material (steel-steel and composite-composite) and bi-material (steel-composite) joints bonded with a structural epoxy adhesive are studied. Additionally, two adhesive bondline thicknesses are considered: 0.4 mm (thin bondline) and 10.1 mm (thick bondline). The Penado-Kanninen reduction scheme is applied to evaluate the mode I strain energy release rate. The results show that the mode I fracture energy, GIc, is independent of the adherend type and joint configuration (single or bi-material). GIc shows average values between 0.60 and 0.72 N/mm for thin bondlines and 0.90–1.10 N/mm for thick bondlines. For thin bondlines, the failure is cohesive and the similar degree of constraint that is imposed to the adhesive by the high-modulus (i.e., steel) and/or relatively thick (i.e., composite) adherends results in similar values of GIc for both single- and bi-material joint types. For thick bondlines, the crack grows closer to one of the adhesive-adherend interfaces, but still within the adhesive. The results show that the adhesive could deform similarly, although the crack has been constrained on one side by different types of adherends, either a steel or composite.
Highlights
The theoretical understanding and practical robustness of composites have driven research into lightweight construction in the shipbuilding industry
Both single‐material and bi‐material joints bonded with a structural epoxy adhesive are studied
The results show that the mode I fracture energy, GIc, is independent of the adherend type and joint configuration
Summary
The theoretical understanding and practical robustness of composites have driven research into lightweight construction in the shipbuilding industry. One possible solution is found to be the replacement of metallic superstructures by composite ones. Steel used to be the dominating material in the shipbuilding industry. The emergence of composites brought initially attention to the mechanical fastening technique and more recently to the adhesive bonding technology. The mechanical fastening technique requires drilling of the composite components, resulting in fibres damage, delamination and non‐continuous components, among others. This joining technique requires fasteners, which leads to a total weight increase. In the adhesive bonding technique, neither fastening holes nor fasteners are needed [1]
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