The use of Fiber Bragg Grating sensors during the static load test of a composite wing structure

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F14%3A00215187" target="_blank" >RIV/68407700:21220/14:00215187 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.scopus.com/record/display.url?eid=2-s2.0-84892159902&origin=inward&txGid=B49100522A34C861A307E062E923B249.f594dyPDCy4K3aQHRor6A%3a1" target="_blank" >http://www.scopus.com/record/display.url?eid=2-s2.0-84892159902&origin=inward&txGid=B49100522A34C861A307E062E923B249.f594dyPDCy4K3aQHRor6A%3a1</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.4028/www.scientific.net/AMM.486.102" target="_blank" >10.4028/www.scientific.net/AMM.486.102</a>

Jazyk výsledku

angličtina

Název v původním jazyce

The use of Fiber Bragg Grating sensors during the static load test of a composite wing structure

Popis výsledku v původním jazyce

The article describes process of implementation of optical Fiber Bragg Grating (FBG) sensors into the composite wing structure and their behavior during the strength test. The wing is of all-composite construction. The upper and lower skins are made of glass/epoxy composite. The spar caps are made of carbon/epoxy unidirectional composite. Optical fibers were integrated directly into the spar caps and into the adhesive joints. They were oriented in parallel with the main spar axis. The first optical fiber with chain of multiple FBG sensors was integrated into the structure of upper spar cap. Another FBG chain of FBG sensors was located in the adhesive joint of lower spar cap and shear web. The wing was instrumented with strain gages as well. Strain gages were glued to the sides of the spar caps. Static load was produced by a hydraulic actuator. Experimental results from strain gages and FBG sensors were compared with the results of the analytical analysis of the wing.

Název v anglickém jazyce

The use of Fiber Bragg Grating sensors during the static load test of a composite wing structure

Popis výsledku anglicky

The article describes process of implementation of optical Fiber Bragg Grating (FBG) sensors into the composite wing structure and their behavior during the strength test. The wing is of all-composite construction. The upper and lower skins are made of glass/epoxy composite. The spar caps are made of carbon/epoxy unidirectional composite. Optical fibers were integrated directly into the spar caps and into the adhesive joints. They were oriented in parallel with the main spar axis. The first optical fiber with chain of multiple FBG sensors was integrated into the structure of upper spar cap. Another FBG chain of FBG sensors was located in the adhesive joint of lower spar cap and shear web. The wing was instrumented with strain gages as well. Strain gages were glued to the sides of the spar caps. Static load was produced by a hydraulic actuator. Experimental results from strain gages and FBG sensors were compared with the results of the analytical analysis of the wing.

Druh

D - Stať ve sborníku

CEP obor

JI - Kompositní materiály

OECD FORD obor

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Projekt

<a href="/cs/project/FR-TI1%2F290" target="_blank" >FR-TI1/290: *Demonstrátor kompozitové řídící plochy velkého dopravního letounu podle předpisu CS-25</a><br>

Návaznosti

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

Rok uplatnění

2014

Kód důvěrnosti údajů

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

Název statě ve sborníku

51st Annual of the International Scientific Conference on Experimental Stress Analysis, EAN 2013

ISBN

978-3-03785-977-3

ISSN

1660-9336

e-ISSN

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Počet stran výsledku

4

Strana od-do

102-105

Název nakladatele

Trans Tech Publications Ltd

Místo vydání

Kreuzstrasse 10, 8635 Durnten-Zurich

Místo konání akce

Litoměřice

Datum konání akce

11. 6. 2013

Typ akce podle státní příslušnosti

EUR - Evropská akce

Kód UT WoS článku

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