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Boundary Element Analysis of Curved Cracked Panels with Mechanically Fastened Repair Patches

P. H. Wen1, M. H. Aliabadi1, A. Young2
Department of Engineering, Queen Mary and Westfield College, London University, London, E1 4NS, UK
Structural Materials Centre, DERA, Farnborough, Hants, GU14 6TD, UK

Computer Modeling in Engineering & Sciences 2002, 3(1), 1-10. https://doi.org/10.3970/cmes.2002.003.001

Abstract

In this paper, applications of the boundary element method to damaged and undamaged aircraft curved panels with mechanical repairs are presented. The effects of fastened repairs are replaced by uniform distribution forces in the area of cross-section of the rivet and can be determined from the compatibility condition of displacements. A coupled boundary integral formulation of a shear deformable plate and two dimensional plane stress elasticity is used to determine the bending and membrane forces on the rivets. Domain integrals in each integral equation are determined using the dual reciprocity method. The stress intensity factors due to bending and membrane loads are evaluated by opening displacements near the crack tips. Several numerical examples are presented to demonstrate the accuracy of the proposed method. It is shown that the bending behavior and plate curvature have significant influence on the magnitude of the stress intensity factors.

Keywords

Fracture, fastened repair, boundary element method, shell, stress intensity factor

Cite This Article

Wen, P. H., Aliabadi, M. H., Young, A. (2002). Boundary Element Analysis of Curved Cracked Panels with Mechanically Fastened Repair Patches. CMES-Computer Modeling in Engineering & Sciences, 3(1), 1–10.



This work is licensed under a Creative Commons Attribution 4.0 International License , which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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