Damage Tolerance Evaluation of the Wing Spar with Cracked Web

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F01%3APU23729" target="_blank" >RIV/00216305:26210/01:PU23729 - 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

Damage Tolerance Evaluation of the Wing Spar with Cracked Web

Popis výsledku v původním jazyce

Damage tolerance evaluation is required for the aircraft life determination according to FAR Part 25 regulations. This concept is based on the crack propagation and residual strength determination. The damage tolerance evaluation of an aircraft structureresults in the inspection program ensuring that fatigue initiated cracks would involve no failure prior to the detection. The inspection program must be developed for each principal structure element in the aircraft. Solutions to this problem usually foound in the literature deal mainly with the components subjected to tension, such as stiffened panels or lugs. This paper presents the testing program and FEM analysis focused on the wing spar with cracks in the web. It is characteristic for fatigue cracks in the web that they usually change their growth direction due to a combined stress state. Measured crack shape was used for constructing of a FEM model of the spar, the residual strength was calculated and compared with the experiment

Název v anglickém jazyce

Damage Tolerance Evaluation of the Wing Spar with Cracked Web

Popis výsledku anglicky

Damage tolerance evaluation is required for the aircraft life determination according to FAR Part 25 regulations. This concept is based on the crack propagation and residual strength determination. The damage tolerance evaluation of an aircraft structureresults in the inspection program ensuring that fatigue initiated cracks would involve no failure prior to the detection. The inspection program must be developed for each principal structure element in the aircraft. Solutions to this problem usually foound in the literature deal mainly with the components subjected to tension, such as stiffened panels or lugs. This paper presents the testing program and FEM analysis focused on the wing spar with cracks in the web. It is characteristic for fatigue cracks in the web that they usually change their growth direction due to a combined stress state. Measured crack shape was used for constructing of a FEM model of the spar, the residual strength was calculated and compared with the experiment

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

<a href="/cs/project/GA101%2F98%2F0292" target="_blank" >GA101/98/0292: Únosnost nosníku s porušující se stojinou pro analýzu životnosti letounu systémem 'damage tolerance'</a><br>

Návaznosti

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

Rok uplatnění

2001

Kód důvěrnosti údajů

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

Název periodika

RECENT RESEARCH AND DESIGN PROGRESS IN AERONAUTICAL ENGINEERING AND ITS INFLUENCE ON EDUCATION

ISSN

1425-2104

e-ISSN

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Svazek periodika

2001

Číslo periodika v rámci svazku

11

Stát vydavatele periodika

PL - Polská republika

Počet stran výsledku

5

Strana od-do

7-11

Kód UT WoS článku

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EID výsledku v databázi Scopus

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