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Comparative Study of Crack Growth Retardation Models for an Integral Stiffened Panel Subjected to Overload.

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Description

One major challenge for the aviation industry is the development of airframe structures safer, lighter and more tolerant to damage. A prominent approach in addressing this challenge involves the use of integrally stiffened panels, which have gained widespread acceptance in the aeronautical sector. This choice offers substantial benefits, including weight reduction and cost savings. Moreover, integrally stiffened panels have one key advantage over traditional built-up structures which is the absence of crack initiation sources. Considering that typical load spectra may include high-load cycles, some of which may represent overload, it is valuable to adopt a crack-propagation model that account for the retardation effect induced by overload. This effect plays a crucial role in accurately predicting fatigue crack growth. The primary objective of this study is to compare the crack growth retardation models in predicting the fatigue crack growth behavior of a specific type of integral panel commonly utilized in the aeronautical industry. This investigation focuses on two widely used aluminum alloys. Additionally, this work provides an overview of the current state of the art in crack growth retardation models.

Reference: VAL5-2024-039

Title: Comparative Study of Crack Growth Retardation Models for an Integral Stiffened Panel Subjected to Overload.
Author(s): J. D. Mattos, M. A. Arbelo
DOI: 10.48447/VAL5-2024-039
Event: VAL5 - Fifth International Conference on Material and Component Performance under Variable Amplitude Loading
Year of publication: 2024
Publication type: conference paper (PDF)
Language: English
Keywords: Overload Retardation Effect,Fatigue Crack-Growth,Integral Stiffened Panel,Aviation Integral Panel

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Fatigue Crack Growth in 7075-T6 Aluminum Alloy under Single-Spike Overloads and Aircraft Spectra

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Author(s): B. Möller, M. Scurria, T. Korschinsky

Application of Incremental Step Tests for Screening and Deriving Cyclic Properties of Metal Structures Using the Example of Additively Manufactured AlSi10Mg

Publication type: conference paper (PDF)

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Author(s): B. Spak, M. Schlicht, P. Froitzheim, W. Flügge, M. Kästner

Application of the Local Strain Approach to estimate fatigue life of clinched joints under constant and variable amplitude loading in different loading conditions

Publication type: conference paper (PDF)

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Author(s): M. Palmieri, A. Staffa, J. Slavic, F. Cianetti

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Author(s): J. Klemenc, J. Kajbic

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Application of nonlinear damage accumulation rules for predicting fatigue life of additivelly manufactured composites

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Author(s): A. Visentin, A. Campagnolo, V. Babini, G. Meneghetti

Fatigue strength assessment of tube-to-flange welded steel joints with reinforcement ribs under variable amplitude loadings according to the Peak Stress Method

Publication type: conference paper (PDF)

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Author(s): T. Lecleve, S. Courtin, F. Szmytka, C. Mai

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Author(s): M. Stoschka, M. Horvath, W. Mössler, F. Grün

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Service strength assessment of macroscopic imperfections in cast steel alloys

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Author(s): M. Česnik, J. Slavič, M. Boltežar

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Author(s): L. Heindel, P. Hantschke, M. Kästner

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1

A demonstrator example for virtual sensing approaches in predictive maintenance applications

Publication type: conference paper (PDF)

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1

English

€25.00

Online only