Supplementary Aeroelastic Analysis of Modified LSA-category Aircraft

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F22%3AN0000043" target="_blank" >RIV/00010669:_____/22:N0000043 - 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

Supplementary Aeroelastic Analysis of Modified LSA-category Aircraft

Popis výsledku v původním jazyce

Flutter analysis must include all applicable mass configurations of an aircraft. In the case of the aircraft modification, the appropriate assessment and supplementary analyses are required. Considering the general aviation aircraft, aeroelastic certification is usually based the analyses using directly the GVT results. Therefore, the possibilities for the supplementary analyses are limited. Submitted paper presents the practical application. Analysis is based on the data gained by the previously performed GVT of the unmodified aircraft. The structure changes are considered using mass perturbation method. Also, very simple measurement of the wing bending mode was provided. Flutter analyses were performed using g-method. Various flutter states were identified. The detailed assessment into rudder flutter was performed as the flutter speed was found inside the envelope of the required flutter stability. The influences of modes and structural parameters were evaluated. Finally, the appropriate modification of the structure to increase the flutter speed was proposed.

Název v anglickém jazyce

Supplementary Aeroelastic Analysis of Modified LSA-category Aircraft

Popis výsledku anglicky

Flutter analysis must include all applicable mass configurations of an aircraft. In the case of the aircraft modification, the appropriate assessment and supplementary analyses are required. Considering the general aviation aircraft, aeroelastic certification is usually based the analyses using directly the GVT results. Therefore, the possibilities for the supplementary analyses are limited. Submitted paper presents the practical application. Analysis is based on the data gained by the previously performed GVT of the unmodified aircraft. The structure changes are considered using mass perturbation method. Also, very simple measurement of the wing bending mode was provided. Flutter analyses were performed using g-method. Various flutter states were identified. The detailed assessment into rudder flutter was performed as the flutter speed was found inside the envelope of the required flutter stability. The influences of modes and structural parameters were evaluated. Finally, the appropriate modification of the structure to increase the flutter speed was proposed.

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

2022

Kód důvěrnosti údajů

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

Název statě ve sborníku

Proceedings of Computational Mechanics 2022

ISBN

978-80-261-1116-0

ISSN

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e-ISSN

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Počet stran výsledku

4

Strana od-do

14-17

Název nakladatele

ZČU Plzeň

Místo vydání

ČR

Místo konání akce

Srní

Datum konání akce

1. 1. 2022

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

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