Simulation of Fatigue Crack Growth in Integrally Stiffened Panels under the Constant Amplitude and Spectrum Loading

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F09%3APU80885" target="_blank" >RIV/00216305:26210/09:PU80885 - isvavai.cz</a>

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Simulation of Fatigue Crack Growth in Integrally Stiffened Panels under the Constant Amplitude and Spectrum Loading

Popis výsledku v původním jazyce

The paper describes methodology of numerical simulation of fatigue crack growth and its application on integrally stiffened panels made of 2024-T351 aluminium alloy using high speed cutting technique. Presented approach for crack growth simulation startsby the calculation of stress intensity factor function from finite element results obtained using MSC.Patran/Nastran. Subsequent crack growth analysis is done in NASGRO and uses description of crack growth rates either by the Forman-Newman-de Koning relationship or by the table lookup form. Three crack growth models were applied for spectrum loading: non-interaction, Willenborg and Strip Yield model. Relatively large experimental program comprising both the constant amplitude and spectrum tests on integral panels and CCT specimens was undertaken at the Institute of Aerospace Engineering laboratory in order to acquire crack growth rate data and enable verification of simulations. First analyses and verification tests of panels were perf

Název v anglickém jazyce

Simulation of Fatigue Crack Growth in Integrally Stiffened Panels under the Constant Amplitude and Spectrum Loading

Popis výsledku anglicky

The paper describes methodology of numerical simulation of fatigue crack growth and its application on integrally stiffened panels made of 2024-T351 aluminium alloy using high speed cutting technique. Presented approach for crack growth simulation startsby the calculation of stress intensity factor function from finite element results obtained using MSC.Patran/Nastran. Subsequent crack growth analysis is done in NASGRO and uses description of crack growth rates either by the Forman-Newman-de Koning relationship or by the table lookup form. Three crack growth models were applied for spectrum loading: non-interaction, Willenborg and Strip Yield model. Relatively large experimental program comprising both the constant amplitude and spectrum tests on integral panels and CCT specimens was undertaken at the Institute of Aerospace Engineering laboratory in order to acquire crack growth rate data and enable verification of simulations. First analyses and verification tests of panels were perf

Druh

D - Stať ve sborníku

CEP obor

JL - Únava materiálu a lomová mechanika

OECD FORD obor

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Projekt

<a href="/cs/project/1M0501" target="_blank" >1M0501: Centrum leteckého a kosmického výzkumu</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2009

Kód důvěrnosti údajů

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

Název statě ve sborníku

Fatigue of Aircraft Structures

ISBN

978-83-929922-1-9

ISSN

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e-ISSN

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Počet stran výsledku

14

Strana od-do

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Název nakladatele

Institute of Aviation

Místo vydání

Warsaw

Místo konání akce

Varšava

Datum konání akce

15. 1. 2009

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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