Analysis of cracks in aging aircraft structures, with and without composite-patch repairs

DOI10.1007/BF00370088zbMath0780.73048MaRDI QIDQ1207273

T. Ogiso, J. H. Park, Satya N. Atluri

Publication date: 1 April 1993

Published in: Computational Mechanics (Search for Journal in Brave)

zbMATH Keywords

analytical solutionsresidual stressesstiffened panelsfinite element alternating methodstress-intensity-factors

Mathematics Subject Classification ID

Finite element methods applied to problems in solid mechanics (74S05) Composite and mixture properties (74E30) Fracture and damage (74R99)

Related Items

An elastic-plastic finite element alternating method for analyzing wide- spread fatigue damage in aircraft structures ⋮ Residual strength prediction for aircraft panels with multiple site damage, using the EPFEAM for stable crack growth analysis ⋮ Recent advances in the alternating method for elastic and inelastic fracture analyses ⋮ Effects of geometric nonlinearities on damage propagation in patched beam-plates subjected to pressure loading

Cites Work

• An application of the inclusion analogy for bonded reinforcements
• ORTHOGONAL POLYNOMIAL SOLUTIONS TO SOME MIXED BOUNDARY-VALUE PROBLEMS IN ELASTICITY THEORY
• The Effect of a Stringer on the Stress in a Cracked Sheet
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