Dynamic tests of composite panels of an aircraft wing

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F15%3APU114310" target="_blank" >RIV/00216305:26210/15:PU114310 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.sciencedirect.com/science/article/pii/S0376042115000366" target="_blank" >http://www.sciencedirect.com/science/article/pii/S0376042115000366</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1016/j.paerosci.2015.05.005" target="_blank" >10.1016/j.paerosci.2015.05.005</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Dynamic tests of composite panels of an aircraft wing

Popis výsledku v původním jazyce

The paper describes the analysis of aerospace composite structures under dynamic loading. Today, it is common to use design procedures based on assumption of static loading only, and dynamic loading is rarely assumed and applied in design and certification of aerospace structures. The paper describes the application of dynamic loading for the design of aircraft structures, and the validation of the procedure on a selected structure. The goal is to verify the possibility of reducing the weight through improved design/modelling processes using dynamic loading instead of static loading. The research activity focuses on the modelling and testing of a composite panel representing a local segment of an aircraft wing section, investigating in particular the buckling behavior under dynamic loading. Finite Elements simulation tools are discussed, as well as the advantages of using a digital optical measurement system for the evaluation of the tests. The comparison of the finite element simulations with the results of the tests is presented.

Název v anglickém jazyce

Dynamic tests of composite panels of an aircraft wing

Popis výsledku anglicky

The paper describes the analysis of aerospace composite structures under dynamic loading. Today, it is common to use design procedures based on assumption of static loading only, and dynamic loading is rarely assumed and applied in design and certification of aerospace structures. The paper describes the application of dynamic loading for the design of aircraft structures, and the validation of the procedure on a selected structure. The goal is to verify the possibility of reducing the weight through improved design/modelling processes using dynamic loading instead of static loading. The research activity focuses on the modelling and testing of a composite panel representing a local segment of an aircraft wing section, investigating in particular the buckling behavior under dynamic loading. Finite Elements simulation tools are discussed, as well as the advantages of using a digital optical measurement system for the evaluation of the tests. The comparison of the finite element simulations with the results of the tests is presented.

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

—

Návaznosti

R - Projekt Ramcoveho programu EK

Rok uplatnění

2015

Kód důvěrnosti údajů

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

Název periodika

PROGRESS IN AEROSPACE SCIENCES

ISSN

0376-0421

e-ISSN

—

Svazek periodika

2015

Číslo periodika v rámci svazku

78

Stát vydavatele periodika

US - Spojené státy americké

Počet stran výsledku

12

Strana od-do

50-61

Kód UT WoS článku

000364259300006

EID výsledku v databázi Scopus

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