Journal
AEROSPACE SCIENCE AND TECHNOLOGY
Volume 29, Issue 1, Pages 363-372Publisher
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2013.04.007
Keywords
Composite material; Impact damage; Structural design; Finite element analysis
Categories
Funding
- Howon University
- Chosun University
Ask authors/readers for more resources
This work is focusing on the low velocity impact damage evaluation and the external patch repair techniques of carbon/epoxy UD and fabric laminate adopted developing aircraft. The impact damages of composite laminates of the carbon/epoxy UD and fabric are simulated by the drop-weight type impact test equipment. The damaged specimens are repaired using the external patch repair method after removing the damaged area. The compressive strength test and analysis results of the repaired impact damaged specimens are compared with the compressive strength test and analysis results of the undamaged specimens and the impact damaged specimens. Finally, through investigation of compressive strengths of the damaged specimens at different environmental conditions, the damage criteria for repairable design of both the impact damaged UD and fabric laminate structure are suggested. (C) 2013 Elsevier Masson SAS. All rights reserved.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available