Residual stress effects of a fatigue crack on guided lamb waves

Journal article (2017)

Authors

M.J. Martinez Structural Integrity & Composites - Aerospace Engineering , Clarkson University
S Pant National Research Council Canada
M Yanishevsky National Research Council Canada
D Backman National Research Council Canada
Research Group
Structural Integrity & Composites (Aerospace Engineering) (TU Delft)
Copyright: © 2017 M.J. Martinez, S Pant, M Yanishevsky, D Backman
DOI: https://doi.org/10.1088/1361-665X/aa8a0c
Fatigue crack growth Propagation Structural health monitoring Acoustic-ultrasonic Complex structures Guided lamb wave Residual stress field
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Published Date

29-09-2017

Language

English

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Faculty

Aerospace Engineering

Department

Aerospace Structures & Materials

Research Group

Structural Integrity & Composites

Abstract

Structural health monitoring has focused on the use of computational models to capture the effect of crack-like discontinuities on the behaviour of acoustic-ultrasonic signals. However, few models have taken into account the effect of geometric complexity in combination with residual stresses generated during the fatigue crack growth (FCG) process. In this study, a finite element analysis model of a C-channel type aeronautical structure is evaluated under a pitch-catch scenario. Three different finite element model configurations were considered in order to understand the effects that residual stresses of a fatigue crack emanating from a through-hole have on the guided Lamb wave propagation behaviour. The results demonstrate that numerical modelling is able to capture the change in amplitude and the effect of a phase shift on the guided Lamb wave behaviour due to the presence of the discontinuity and the stress field generated during the FCG process.