Advanced search
Start date
Betweenand
Related content
(Reference retrieved automatically from Web of Science through information on FAPESP grant and its corresponding number as mentioned in the publication by the authors.)

Assessment of Cumulative Damage by Using Ultrasonic C-Scan on Carbon Fiber/Epoxy Composites Under Thermal Cycling

Full text
Author(s):
Shiino, Marcos Yutaka [1] ; Magalhaes Faria, Maria Candida [1] ; Botelho, Edson Cocchieri [1] ; de Oliveira, Pedro Carlos [2]
Total Authors: 4
Affiliation:
[1] Univ Estadual Paulista UNESP, Fatigue & Aeronaut Mat Res Grp, Mat & Technol Dept, Guaratingueta Fac Engn, BR-12516410 Guaratingueta, SP - Brazil
[2] Univ Sao Paulo, Escola Engn Lorena, BR-12602810 Lorena, SP - Brazil
Total Affiliations: 2
Document type: Journal article
Source: MATERIALS RESEARCH-IBERO-AMERICAN JOURNAL OF MATERIALS; v. 15, n. 4, p. 495-499, JUL-AUG 2012.
Web of Science Citations: 5
Abstract

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 degrees until 80 degrees 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 degrees to 80 degrees 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. (AU)

FAPESP's process: 09/04123-4 - Development of composites processed by RTM for landing gear components
Grantee:Marcos Yutaka Shiino
Support Opportunities: Scholarships in Brazil - Master
FAPESP's process: 11/01937-0 - Crack growth rate in 5HS carbon/epoxy composites manufactured by RTM: Relationship between axial loadings with pure modes of delamination I and II
Grantee:Marcos Yutaka Shiino
Support Opportunities: Scholarships in Brazil - Doctorate
FAPESP's process: 06/02121-6 - Composite processing by RTM
Grantee:Maria Odila Hilário Cioffi
Support Opportunities: Research Grants - Young Investigators Grants