Modifications of a simple I-beam and its effects on the stress state

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F16%3APU122226" target="_blank" >RIV/00216305:26210/16:PU122226 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.tandfonline.com/doi/abs/10.3846/16487788.2016.1227538" target="_blank" >http://www.tandfonline.com/doi/abs/10.3846/16487788.2016.1227538</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.3846/16487788.2016.1227538" target="_blank" >10.3846/16487788.2016.1227538</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Modifications of a simple I-beam and its effects on the stress state

Popis výsledku v původním jazyce

The motivation for this work is a desire for a deeper understanding of the structural failures in a composite glider wing, which has been tested in the laboratories of the Institute of Aerospace Engineering, Faculty of Mechanical Engineering, Brno University of Technology. To understand the causes of the encountered failures, one has to consider the effects of all the stages in the design, manufacturing and testing of the wing. This paper focuses only on the design stage. The presented facts were obtained from a finite element analysis. The geometry used for the analysis is that of the tested specimens. This allows validating the results by the comparison of the deformation and strains measured during the laboratory tests. The analysis starts with a simple I-beam loaded by three-point-bending. In the next step a cantilever is added. Several more modifications follow, changing the I-beam to the wing. The case evaluation considers the interaction between normal (material direction 1) and inter-laminar shear stresses in the upper flange. The goal of this paper is to quantify the effect of each design change in the wing structure and loading on the stress plane σ1-τ31.

Název v anglickém jazyce

Modifications of a simple I-beam and its effects on the stress state

Popis výsledku anglicky

The motivation for this work is a desire for a deeper understanding of the structural failures in a composite glider wing, which has been tested in the laboratories of the Institute of Aerospace Engineering, Faculty of Mechanical Engineering, Brno University of Technology. To understand the causes of the encountered failures, one has to consider the effects of all the stages in the design, manufacturing and testing of the wing. This paper focuses only on the design stage. The presented facts were obtained from a finite element analysis. The geometry used for the analysis is that of the tested specimens. This allows validating the results by the comparison of the deformation and strains measured during the laboratory tests. The analysis starts with a simple I-beam loaded by three-point-bending. In the next step a cantilever is added. Several more modifications follow, changing the I-beam to the wing. The case evaluation considers the interaction between normal (material direction 1) and inter-laminar shear stresses in the upper flange. The goal of this paper is to quantify the effect of each design change in the wing structure and loading on the stress plane σ1-τ31.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

R - Projekt Ramcoveho programu EK

Rok uplatnění

2016

Kód důvěrnosti údajů

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

Název periodika

AVIATION

ISSN

1648-7788

e-ISSN

—

Svazek periodika

20

Číslo periodika v rámci svazku

4

Stát vydavatele periodika

LT - Litevská republika

Počet stran výsledku

5

Strana od-do

168-172

Kód UT WoS článku

000390891200003

EID výsledku v databázi Scopus

2-s2.0-85008249028