Abstract:
This present work is performed in order to study the various techniques of reinforcement and repair of composite structures. It also consists of the analysis of peeling and shear stresses in the adhesive part of a composite structure repaired or reinforced by joining a composite patch.
A good knowledge of the stress state in this part, which represents the weakest link of the whole (structure-patch-glue), makes it possible to conceive a better repair. In this same axis, it was interested to study the effect of certain parameters such as the geometric and mechanical characteristics of the patch, as well as the thickness of the adhesive layer on the evolution of
these stresses. The composite structure to reinforce or repair is considered in this study under the action of a uniaxial traction. In the case of a reinforcement, the bonding is performed on one or both sides of the structure (bonded single or bonded doublers), whereas in the case of a repair, using a single or double strap. The material of the damaged structure considered in our study is a composite with excessive use in aeronautics, and also is Aluminum comprising silicon carbide particles. The composite patch, generally used for the reinforcement and repair by bonding and also considered in this contribution, is a unidirectional carbon/epoxy. On the other hand, the adhesive layer binding the patch to the structure is chosen epoxy resin and is
designated by FM73. For the both joint types, the obtained results showed low strength at their ends and also at the breakpoint in the case of strap configuration.
