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Fatigue growth of multiple-cracks near a row of fastener-holes in a fuselage lap-joint

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Abstract

The fatigue growth of multiple cracks, of arbitrary lengths, emanating from a row of fastener holes in a bonded, riveted, lap joint in a pressurized aircraft fuselage is studied. The effects of residual stresses due to a rivet misfit, and of plastic deformation near the hole, are included. A Schwartz-Neumann alternating method which uses the analytical solution for a row of multiple colinear cracks in an infinite sheet (the crack-faces being subject to arbitrary tractions), is developed to analyze this MSD problem on a personal computer. It is found that for a range of crack lengths, a phenomena wherein the shorter cracks may grow faster than longer cracks may exist.

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Author notes

  1. J. H. Park

    Present address: Chungbuk National University, Cheongju, Korea

Authors and Affiliations

  1. Computational Modeling Center, Georgia Institute of Technology, 30332-0356, Atlanta, GA, USA

    J. H. Park & S. N. Atluri

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  1. J. H. Park
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  2. S. N. Atluri
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Communicated by S. N. Atluri, March 2, 1992

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Park, J.H., Atluri, S.N. Fatigue growth of multiple-cracks near a row of fastener-holes in a fuselage lap-joint. Computational Mechanics 13, 189–203 (1993). https://doi.org/10.1007/BF00370135

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  • DOI: https://doi.org/10.1007/BF00370135

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