Aircraft Wing Flutter Assessment Considering Damage Tolerance based Failure States

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F17%3AN0000018" target="_blank" >RIV/00010669:_____/17:N0000018 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.engmech.cz/2017/" target="_blank" >http://www.engmech.cz/2017/</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Aircraft Wing Flutter Assessment Considering Damage Tolerance based Failure States

Popis výsledku v původním jazyce

This paper deals with aircraft wing flutter analysis considering the failure states, originated by the application of the damage - tolerance design philosophy on the wing structure. Such damages may influence the integral stiffness of a wing structure and, as a consequence, to influence its flutter characteristics. Therefore, airworthiness regulation standards require flutter analysis of these failure states. The paper presents the simple method of the wing stiffness transformation. The source model is the detailed static FE model, applicable to include the mentioned damages. Target model is the aeroelastic stick FE model, applicable for aeroelastic analyses. The method of assessment of the influence of damage on the wing flutter is shown. The methodology is demonstrated on the example of a commuter aircraft wing bending - torsional flutter. The method is applicable for compliance with FAR / CS 23.629(g)(h) requirements.

Název v anglickém jazyce

Aircraft Wing Flutter Assessment Considering Damage Tolerance based Failure States

Popis výsledku anglicky

This paper deals with aircraft wing flutter analysis considering the failure states, originated by the application of the damage - tolerance design philosophy on the wing structure. Such damages may influence the integral stiffness of a wing structure and, as a consequence, to influence its flutter characteristics. Therefore, airworthiness regulation standards require flutter analysis of these failure states. The paper presents the simple method of the wing stiffness transformation. The source model is the detailed static FE model, applicable to include the mentioned damages. Target model is the aeroelastic stick FE model, applicable for aeroelastic analyses. The method of assessment of the influence of damage on the wing flutter is shown. The methodology is demonstrated on the example of a commuter aircraft wing bending - torsional flutter. The method is applicable for compliance with FAR / CS 23.629(g)(h) requirements.

Druh

D - Stať ve sborníku

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

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Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2017

Kód důvěrnosti údajů

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

Název statě ve sborníku

Engineering Mechanics 2017

ISBN

978-80-214-5497-2

ISSN

1805-8248

e-ISSN

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Počet stran výsledku

4

Strana od-do

234-237

Název nakladatele

Ústav Termomechaniky, AV ČR

Místo vydání

Praha, ČR

Místo konání akce

Svratka, ČR

Datum konání akce

15. 5. 2017

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

000411657600048