Abstract:

The paper presents a numerical analysis method allowing the determination of the degree of failure of an adhesive joint with the use of CAE software. The results of an experimental test are used to describe properties of the joint parts. Described herein is the behaviour of a multi-stepping lap joint of metal with a multilayered fibre composite that is often used in the aircraft industry. Modelling of the contact problem between the metal surface and layer of the composite enables determination of the value of the external tensile load at which the process of failure of the joint begins. The author also proposes a simple method to shape solid finite elements which allows the elimination of the singularity around finite element vertices. The method has been applied to numerical analysis of the joint, in which the layers were stacked at various angle orientations. The influence of the step length of the metal part on the joint strength was also considered. The results of numerical analysis were compared with those of experimental investigations of the joint strength, giving satisfactory agreement.