Comparative Study of Prediction Methods for Fatigue Life Evaluation of an Integral Skin-Stringer Panel under Variable Amplitude Loading

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F15%3AN0000007" target="_blank" >RIV/00010669:_____/15:N0000007 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.sciencedirect.com/science/article/pii/S1877705815016896" target="_blank" >http://www.sciencedirect.com/science/article/pii/S1877705815016896</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.proeng.2015.08.050" target="_blank" >10.1016/j.proeng.2015.08.050</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Comparative Study of Prediction Methods for Fatigue Life Evaluation of an Integral Skin-Stringer Panel under Variable Amplitude Loading

Popis výsledku v původním jazyce

The study deals with an integral skin-stringer wing panel made of AA 7475-T7351. DT solutions for fatigue life prediction are based on computational methods. Crack growth is analysed under the flight by flight loading representative for a commuter aircraft. Crack growth predictions are performed by using both the linear damage accumulation principle and the FASTRAN retardation model. Different solutions of crack and structural geometry, which are expressed by the Ecorrection factor related to stress intensity factor assessment, are compared. The predicted crack growth and original data for the integral wing panel are discussed. The influence of geometry correction factors, which are defined by considering different hypotheses of their determination, is not significant for the integrally stiffened panel. In contrast, the retardation effect for the flight by flight loading, investigated alloy and structural part is significant. The FASTRAN retardation model gives underestimated predictions of approximately 10% compared with the experimental data. The reason underlying the increasing difference between the experimental data and numerical predictions of longest crack length propagation is discussed.

Název v anglickém jazyce

Comparative Study of Prediction Methods for Fatigue Life Evaluation of an Integral Skin-Stringer Panel under Variable Amplitude Loading

Popis výsledku anglicky

The study deals with an integral skin-stringer wing panel made of AA 7475-T7351. DT solutions for fatigue life prediction are based on computational methods. Crack growth is analysed under the flight by flight loading representative for a commuter aircraft. Crack growth predictions are performed by using both the linear damage accumulation principle and the FASTRAN retardation model. Different solutions of crack and structural geometry, which are expressed by the Ecorrection factor related to stress intensity factor assessment, are compared. The predicted crack growth and original data for the integral wing panel are discussed. The influence of geometry correction factors, which are defined by considering different hypotheses of their determination, is not significant for the integrally stiffened panel. In contrast, the retardation effect for the flight by flight loading, investigated alloy and structural part is significant. The FASTRAN retardation model gives underestimated predictions of approximately 10% compared with the experimental data. The reason underlying the increasing difference between the experimental data and numerical predictions of longest crack length propagation is discussed.

Druh

D - Stať ve sborníku

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

—

Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2015

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název statě ve sborníku

Procedia Engineering

ISBN

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ISSN

1877-7058

e-ISSN

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Počet stran výsledku

8

Strana od-do

124-131

Název nakladatele

Elsevier Ltd.

Místo vydání

Neuveden

Místo konání akce

Madeira, Portugalsko

Datum konání akce

1. 9. 2014

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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