Simulation of Fatigue Crack Growth in the High Speed Machined Panel 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%3APU80911" target="_blank" >RIV/00216305:26210/09:PU80911 - 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 the High Speed Machined Panel 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 starts by the calculation of stress intensity factor function from finite element results obtained using MSC.Patran/Nastran. Subsequent crack growth analyses were done in NASGRO. For predictions of crack growth under the spectrum loading a sequence representing service loading of the transport airplane wing was prepared. Three crack growth models were applied: non-interaction, Willenborg and Strip Yield. Relatively large experimental program comprising both the constant amplitude and spectrum tests on integral panels and CCT specimens was undertaken in order to acquire crack growth rate data and enable verification of simulations. The work was performed within the scope of the 6th Framework Programme project DaToN.

Název v anglickém jazyce

Simulation of Fatigue Crack Growth in the High Speed Machined Panel 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 starts by the calculation of stress intensity factor function from finite element results obtained using MSC.Patran/Nastran. Subsequent crack growth analyses were done in NASGRO. For predictions of crack growth under the spectrum loading a sequence representing service loading of the transport airplane wing was prepared. Three crack growth models were applied: non-interaction, Willenborg and Strip Yield. Relatively large experimental program comprising both the constant amplitude and spectrum tests on integral panels and CCT specimens was undertaken in order to acquire crack growth rate data and enable verification of simulations. The work was performed within the scope of the 6th Framework Programme project DaToN.

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

Proceedings of the 25th Symposium of the International Committee on Aeronautical Fatigue

ISBN

978-90-481-2745-0

ISSN

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e-ISSN

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Počet stran výsledku

14

Strana od-do

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Název nakladatele

Springer Science+Business Media

Místo vydání

Dodrecht

Místo konání akce

Rotterdam

Datum konání akce

27. 5. 2009

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

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