Fatigue life analysis of aging aircraft based on previous service usage

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F18%3APU128922" target="_blank" >RIV/00216305:26210/18:PU128922 - isvavai.cz</a>

Výsledek na webu

<a href="https://www.crcpress.com/New-Trends-in-Civil-Aviation-Proceedings-of-the-19th-International-Conference/Socha-Hanakova-Lalis/p/book/9780815376026" target="_blank" >https://www.crcpress.com/New-Trends-in-Civil-Aviation-Proceedings-of-the-19th-International-Conference/Socha-Hanakova-Lalis/p/book/9780815376026</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Fatigue life analysis of aging aircraft based on previous service usage

Popis výsledku v původním jazyce

This paper describes the approach for the fatigue evaluation of Aero Ae 45 S aircraft (registration OK-KGB). An analysis was carried out to define the individual fatigue life of this airplane based on its service history. By applying a newly developed flight loading spectrum and airframe full-scale fatigue test results, the original safe-life limit was proposed to be extended from 3000 to 4600 flight hours, which was approved by CAA. The limit extension was supported by eddy current and penetrant inspection programs for the primary fatigue critical area of the lower wing main spar attachment lugs made of L-ROL steel. Inspection intervals were determined using damage tolerance analysis techniques, fracture mechanics, and fatigue crack growth code NASGRO.

Název v anglickém jazyce

Fatigue life analysis of aging aircraft based on previous service usage

Popis výsledku anglicky

This paper describes the approach for the fatigue evaluation of Aero Ae 45 S aircraft (registration OK-KGB). An analysis was carried out to define the individual fatigue life of this airplane based on its service history. By applying a newly developed flight loading spectrum and airframe full-scale fatigue test results, the original safe-life limit was proposed to be extended from 3000 to 4600 flight hours, which was approved by CAA. The limit extension was supported by eddy current and penetrant inspection programs for the primary fatigue critical area of the lower wing main spar attachment lugs made of L-ROL steel. Inspection intervals were determined using damage tolerance analysis techniques, fracture mechanics, and fatigue crack growth code NASGRO.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/TE02000032" target="_blank" >TE02000032: Výzkumné centrum pokročilých leteckých konstrukcí</a><br>

Návaznosti

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

Rok uplatnění

2018

Kód důvěrnosti údajů

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

Název statě ve sborníku

New Trends in Civil Aviation

ISBN

978-0-8153-7602-6

ISSN

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e-ISSN

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Počet stran výsledku

330

Strana od-do

113-118

Název nakladatele

CRC Press/Balkema

Místo vydání

Leiden, The Netherlands

Místo konání akce

Department of Air Transport, Czech Technical Uni

Datum konání akce

7. 12. 2017

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

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