Structural analyses of small transport aircraft by the Institute of Aerospace Engineering

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F15%3APU122179" target="_blank" >RIV/00216305:26210/15:PU122179 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.czaerospace.eu/en/2015-03-54.html" target="_blank" >http://www.czaerospace.eu/en/2015-03-54.html</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Structural analyses of small transport aircraft by the Institute of Aerospace Engineering

Popis výsledku v původním jazyce

The participation of the Institute of Aerospace Engineering on small transport aircraft design is presented in this paper. This commuter category aircraft named L 410 NG is developed according to the CS-23 regulation standard. For a structural design and modifications the modern non-linear FE methods and innovative approaches in stress analyses were used. An elongation of the fatigue durability of critical undercarriage spars and wall segments of aircraft fuselage was investigated. Stress analyses of aileron, flap, elevator and rudder control systems were proved. Also load comparisons and three particular stress analyses of the horizontal tail unit and its separated parts are described. The research of progressive non-linear computation methods and complex stress analyses of longitudinal structural system of the rear fuselage part are presented in this article.

Název v anglickém jazyce

Structural analyses of small transport aircraft by the Institute of Aerospace Engineering

Popis výsledku anglicky

The participation of the Institute of Aerospace Engineering on small transport aircraft design is presented in this paper. This commuter category aircraft named L 410 NG is developed according to the CS-23 regulation standard. For a structural design and modifications the modern non-linear FE methods and innovative approaches in stress analyses were used. An elongation of the fatigue durability of critical undercarriage spars and wall segments of aircraft fuselage was investigated. Stress analyses of aileron, flap, elevator and rudder control systems were proved. Also load comparisons and three particular stress analyses of the horizontal tail unit and its separated parts are described. The research of progressive non-linear computation methods and complex stress analyses of longitudinal structural system of the rear fuselage part are presented in this article.

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

Výsledek vznikl pri realizaci vícero projektů. Více informací v záložce Projekty.

Návaznosti

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

Rok uplatnění

2015

Kód důvěrnosti údajů

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

Název periodika

Letecký zpravodaj

ISSN

1211-877X

e-ISSN

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Svazek periodika

2015

Číslo periodika v rámci svazku

3

Stát vydavatele periodika

CZ - Česká republika

Počet stran výsledku

3

Strana od-do

21-23

Kód UT WoS článku

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EID výsledku v databázi Scopus

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