Author(s)

N.K. Salgado and M.H. Aliabadi

Abstract

This paper presents a new boundary element formulation for the analysis of aircraft adhesively bonded repair patches. The Dual Boundary Element Method (DEEM) is used to model the cracked panel. Adhesive shear stresses are modelled as action-reaction body forces exchanged by the panel and patches. The Dual Reciprocity Method (DRM) is coupled to the DBEM to transform the domain integrals due to the adhesive stresses to the boundary integrals. 1 Introduction In Aircraft structures adhesively bonded patches are regarded as an accept- able and efficient method of repair [l], [2]. A cracked panel is often repaired by attaching a reinforcing patch over the cracked region. The patch provides an alternative load path and stresses in the cracked sheet are reduced, as part of the load is trans

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