Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling
Autor(a) principal: | |
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Data de Publicação: | 2012 |
Outros Autores: | , , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Materials research (São Carlos. Online) |
Texto Completo: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002 |
Resumo: | In recent years, structural composites manufactured by carbon fiber/epoxy laminates have been employed in large scale in aircraft industries. These structures require high strength under severe temperature changes of -56° until 80 °C. Regarding this scenario, the aim of this research was to reproduce thermal stress in the laminate plate developed by temperature changes and tracking possible cumulative damages on the laminate using ultrasonic C-scan inspection. The evaluation was based on attenuation signals and the C-scan map of the composite plate. The carbon fiber/epoxy plain weave laminate underwent temperatures of -60° to 80 °C, kept during 10 minutes and repeated for 1000, 2000, 3000 and 4000 times. After 1000 cycles, the specimens were inspected by C-scanning. A few changes in the laminate were observed using the inspection methodology only in specimens cycled 3000 times, or so. According to the found results, the used temperature range did not present enough conditions to cumulative damage in this type of laminate, which is in agreement with the macro - and micromechanical theory. |
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Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cyclingcarbon fiber reinforcement plastics (CFRP)ultrasonicthermal cyclingIn recent years, structural composites manufactured by carbon fiber/epoxy laminates have been employed in large scale in aircraft industries. These structures require high strength under severe temperature changes of -56° until 80 °C. Regarding this scenario, the aim of this research was to reproduce thermal stress in the laminate plate developed by temperature changes and tracking possible cumulative damages on the laminate using ultrasonic C-scan inspection. The evaluation was based on attenuation signals and the C-scan map of the composite plate. The carbon fiber/epoxy plain weave laminate underwent temperatures of -60° to 80 °C, kept during 10 minutes and repeated for 1000, 2000, 3000 and 4000 times. After 1000 cycles, the specimens were inspected by C-scanning. A few changes in the laminate were observed using the inspection methodology only in specimens cycled 3000 times, or so. According to the found results, the used temperature range did not present enough conditions to cumulative damage in this type of laminate, which is in agreement with the macro - and micromechanical theory.ABM, ABC, ABPol2012-08-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002Materials Research v.15 n.4 2012reponame:Materials research (São Carlos. Online)instname:Universidade Federal de São Carlos (UFSCAR)instacron:ABM ABC ABPOL10.1590/S1516-14392012005000062info:eu-repo/semantics/openAccessShiino,Marcos YutakaFaria,Maria Candida MagalhãesBotelho,Edson CocchieriOliveira,Pedro Carlos deeng2012-08-24T00:00:00Zoai:scielo:S1516-14392012000400002Revistahttp://www.scielo.br/mrPUBhttps://old.scielo.br/oai/scielo-oai.phpdedz@power.ufscar.br1980-53731516-1439opendoar:2012-08-24T00:00Materials research (São Carlos. Online) - Universidade Federal de São Carlos (UFSCAR)false |
dc.title.none.fl_str_mv |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
title |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
spellingShingle |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling Shiino,Marcos Yutaka carbon fiber reinforcement plastics (CFRP) ultrasonic thermal cycling |
title_short |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
title_full |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
title_fullStr |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
title_full_unstemmed |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
title_sort |
Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling |
author |
Shiino,Marcos Yutaka |
author_facet |
Shiino,Marcos Yutaka Faria,Maria Candida Magalhães Botelho,Edson Cocchieri Oliveira,Pedro Carlos de |
author_role |
author |
author2 |
Faria,Maria Candida Magalhães Botelho,Edson Cocchieri Oliveira,Pedro Carlos de |
author2_role |
author author author |
dc.contributor.author.fl_str_mv |
Shiino,Marcos Yutaka Faria,Maria Candida Magalhães Botelho,Edson Cocchieri Oliveira,Pedro Carlos de |
dc.subject.por.fl_str_mv |
carbon fiber reinforcement plastics (CFRP) ultrasonic thermal cycling |
topic |
carbon fiber reinforcement plastics (CFRP) ultrasonic thermal cycling |
description |
In recent years, structural composites manufactured by carbon fiber/epoxy laminates have been employed in large scale in aircraft industries. These structures require high strength under severe temperature changes of -56° until 80 °C. Regarding this scenario, the aim of this research was to reproduce thermal stress in the laminate plate developed by temperature changes and tracking possible cumulative damages on the laminate using ultrasonic C-scan inspection. The evaluation was based on attenuation signals and the C-scan map of the composite plate. The carbon fiber/epoxy plain weave laminate underwent temperatures of -60° to 80 °C, kept during 10 minutes and repeated for 1000, 2000, 3000 and 4000 times. After 1000 cycles, the specimens were inspected by C-scanning. A few changes in the laminate were observed using the inspection methodology only in specimens cycled 3000 times, or so. According to the found results, the used temperature range did not present enough conditions to cumulative damage in this type of laminate, which is in agreement with the macro - and micromechanical theory. |
publishDate |
2012 |
dc.date.none.fl_str_mv |
2012-08-01 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.1590/S1516-14392012005000062 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
text/html |
dc.publisher.none.fl_str_mv |
ABM, ABC, ABPol |
publisher.none.fl_str_mv |
ABM, ABC, ABPol |
dc.source.none.fl_str_mv |
Materials Research v.15 n.4 2012 reponame:Materials research (São Carlos. Online) instname:Universidade Federal de São Carlos (UFSCAR) instacron:ABM ABC ABPOL |
instname_str |
Universidade Federal de São Carlos (UFSCAR) |
instacron_str |
ABM ABC ABPOL |
institution |
ABM ABC ABPOL |
reponame_str |
Materials research (São Carlos. Online) |
collection |
Materials research (São Carlos. Online) |
repository.name.fl_str_mv |
Materials research (São Carlos. Online) - Universidade Federal de São Carlos (UFSCAR) |
repository.mail.fl_str_mv |
dedz@power.ufscar.br |
_version_ |
1754212661327822848 |