Assessment of Aileron Tab Installation Influence on Light Sport Aircraft Flutter Characteristics

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F13%3A%230001551" target="_blank" >RIV/00010669:_____/13:#0001551 - isvavai.cz</a>

Výsledek na webu

<a href="http://pig.sagepub.com/content/227/6.toc" target="_blank" >http://pig.sagepub.com/content/227/6.toc</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1177/0954410012446396" target="_blank" >10.1177/0954410012446396</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Assessment of Aileron Tab Installation Influence on Light Sport Aircraft Flutter Characteristics

Popis výsledku v původním jazyce

This paper deals with the aileron flutter of the light sport aircraft. It gives an assessment of the influence of the retrofitting of the tab with regard to the aircraft aileron flutter characteristics. The necessary actuation system stiffness and the aileron flapping frequency to ensure stability at maximal speed of the aircraft are evaluated. The study was motivated by the M-7 aircraft accident in the western Bohemia in 2006. The finite element (FE) model was prepared by the optimization (gradient based methods) utilizing the geometry and the test results to obtain the unknown structural parameters (stiffness, inertia). The design variables were mass and stiffness characteristics, initial values of design variables were set according geometry. The design responses (constrains and objective functions) were formulated in order to match ground vibration tests and other known

Název v anglickém jazyce

Assessment of Aileron Tab Installation Influence on Light Sport Aircraft Flutter Characteristics

Popis výsledku anglicky

This paper deals with the aileron flutter of the light sport aircraft. It gives an assessment of the influence of the retrofitting of the tab with regard to the aircraft aileron flutter characteristics. The necessary actuation system stiffness and the aileron flapping frequency to ensure stability at maximal speed of the aircraft are evaluated. The study was motivated by the M-7 aircraft accident in the western Bohemia in 2006. The finite element (FE) model was prepared by the optimization (gradient based methods) utilizing the geometry and the test results to obtain the unknown structural parameters (stiffness, inertia). The design variables were mass and stiffness characteristics, initial values of design variables were set according geometry. The design responses (constrains and objective functions) were formulated in order to match ground vibration tests and other known

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

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Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2013

Kód důvěrnosti údajů

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

Název periodika

Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

ISSN

0954-4100

e-ISSN

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Svazek periodika

227

Číslo periodika v rámci svazku

6

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

9

Strana od-do

1000-1008

Kód UT WoS článku

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EID výsledku v databázi Scopus

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