Adhesive stress distribution in aeronautical structures with stiffeners and repaired by composite patches

In this study, the finite element method is used to analyse the distribution of shear stresses in aeronautical structures repaired by composite patching and reinforced with a metallic stiffener. The stress distribution in the adhesive layer will be analysed to estimate the durability of the repair technique in the presence and absence of the stiffener in the aeronautical structure. The results obtained show that the presence of the stiffener does not have a significant effect on the level of adhesive stresses under the composite patch, but conversely the adhesive stresses under the stiffener are quite high. This study was carried out for the case of plates.