Estimation of the Stress-Intensity Factor Value in the Presence of an Adhesive Defect for a Damaged Plate Repaired with a Composite Patch

Since the implementation of the process for repairing damage in aeronautical structures, the composite patch repair process continues to show its performance with respect to reducing the concentration of stresses in the vicinity of geometric discontinuities and, therefore, ensures a long lifespan of the repaired structure.Despite the advantages, which this process represents compared to conventional riveting, bolting and welding processes, this process still remains applicable for secondary structures.In fact, the exposure of the adhesive to temperature and humidity and the existence of flaws within the adhesive layer remain a major problem of its use.Indeed, during the implementation of this process, several defects are