Abstract
In composite structures adhesive bonding is preferred to mechanical fasteners because they provide even stress distribution, smooth surface contours and excellent fatigue properties. Interfaces of adherend and adhesive are the potential sources for the initiation of debonding leading to failure. In the present work, composite joints are analysed using the finite element method for the computation of the strain energy release rate, which is used as a measure for possible debonding. Interfaces are modelled by paired nodes and are released one after another in a proper sequence, modelling the crack opening. Joints with various values of elastic moduli, thickness of adherend and adhesive, and overlap lengths for different crack growth lengths along the interfaces are analysed. Laminae of different fibre orientations and lay-up sequences are also considered. Failure loads are estimated and material and geometrical parameters and lay-up sequences are suggested.
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