Fatigue delamination of a carbon fabric-reinforced epoxy composite with carbon nanotubes

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00010669%3A_____%2F15%3A%230001893" target="_blank" >RIV/00010669:_____/15:#0001893 - isvavai.cz</a>

Výsledek na webu

<a href="http://www.eccm15.org/index.php" target="_blank" >http://www.eccm15.org/index.php</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Fatigue delamination of a carbon fabric-reinforced epoxy composite with carbon nanotubes

Popis výsledku v původním jazyce

Carbon fibre-reinforced epoxy composites are used in aerospace applications as primary aircraft structures where material fatigue can be an issue. Carbon nanotubes (CNTs) appear to enhance the fatigue resistance according to literature. This work presents the results of precise crack growth rate measurement on double cantilever beam (DCB) specimens made from a carbon fibre fabric-reinforced epoxy composite. Two plates were evaluated where the resin was enhanced using 0.5 % CNTs and a flame retardant forone of the plates. Loading in mode I was displacement controlled with R = 0.1, f = 4 Hz and a constant maximum strain energy release rate (GI)max during the cycle. The value of (GI)max was defined to be 20 % up to 60 % of the mode I interlaminar fracture toughness. The crack length was determined from the modified compliance calibration (MCC) method by video-recording the specimen edges. The specimens enhanced by CNTs had a significantly decreased fatigue crack growth rate by approximat

Název v anglickém jazyce

Fatigue delamination of a carbon fabric-reinforced epoxy composite with carbon nanotubes

Popis výsledku anglicky

Carbon fibre-reinforced epoxy composites are used in aerospace applications as primary aircraft structures where material fatigue can be an issue. Carbon nanotubes (CNTs) appear to enhance the fatigue resistance according to literature. This work presents the results of precise crack growth rate measurement on double cantilever beam (DCB) specimens made from a carbon fibre fabric-reinforced epoxy composite. Two plates were evaluated where the resin was enhanced using 0.5 % CNTs and a flame retardant forone of the plates. Loading in mode I was displacement controlled with R = 0.1, f = 4 Hz and a constant maximum strain energy release rate (GI)max during the cycle. The value of (GI)max was defined to be 20 % up to 60 % of the mode I interlaminar fracture toughness. The crack length was determined from the modified compliance calibration (MCC) method by video-recording the specimen edges. The specimens enhanced by CNTs had a significantly decreased fatigue crack growth rate by approximat

Druh

O - Ostatní výsledky

CEP obor

JI - Kompositní materiály

OECD FORD obor

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Projekt

<a href="/cs/project/7E13060" target="_blank" >7E13060: IMPROVING THE AIRCRAFT SAFETY BY SELF HEALING STRUCTURE AND PROTECTING NANOFILLERS</a><br>

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