Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling
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 reproduc...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Associação Brasileira de Metalurgia e Materiais (ABM); Associação Brasileira de Cerâmica (ABC); Associação Brasileira de Polímeros (ABPol)
2012-08-01
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| Series: | Materials Research |
| Subjects: | |
| Online Access: | http://www.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002 |
| _version_ | 1811325200541679616 |
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| author | Marcos Yutaka Shiino Maria Candida Magalhães Faria Edson Cocchieri Botelho Pedro Carlos de Oliveira |
| author_facet | Marcos Yutaka Shiino Maria Candida Magalhães Faria Edson Cocchieri Botelho Pedro Carlos de Oliveira |
| author_sort | Marcos Yutaka Shiino |
| collection | DOAJ |
| 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. |
| first_indexed | 2024-04-13T14:30:06Z |
| format | Article |
| id | doaj.art-e9a18e723c2f429682e353c0d5346a34 |
| institution | Directory Open Access Journal |
| issn | 1516-1439 |
| language | English |
| last_indexed | 2024-04-13T14:30:06Z |
| publishDate | 2012-08-01 |
| publisher | Associação Brasileira de Metalurgia e Materiais (ABM); Associação Brasileira de Cerâmica (ABC); Associação Brasileira de Polímeros (ABPol) |
| record_format | Article |
| series | Materials Research |
| spelling | doaj.art-e9a18e723c2f429682e353c0d5346a342022-12-22T02:43:14ZengAssociação Brasileira de Metalurgia e Materiais (ABM); Associação Brasileira de Cerâmica (ABC); Associação Brasileira de Polímeros (ABPol)Materials Research1516-14392012-08-01154495499Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cyclingMarcos Yutaka ShiinoMaria Candida Magalhães FariaEdson Cocchieri BotelhoPedro Carlos de OliveiraIn 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.http://www.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002carbon fiber reinforcement plastics (CFRP)ultrasonicthermal cycling |
| spellingShingle | Marcos Yutaka Shiino Maria Candida Magalhães Faria Edson Cocchieri Botelho Pedro Carlos de Oliveira Assessment of cumulative damage by using ultrasonic C-scan on carbon fiber/epoxy composites under thermal cycling Materials Research carbon fiber reinforcement plastics (CFRP) ultrasonic thermal cycling |
| title | 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_short | 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 |
| topic | carbon fiber reinforcement plastics (CFRP) ultrasonic thermal cycling |
| url | http://www.scielo.br/scielo.php?script=sci_arttext&pid=S1516-14392012000400002 |
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