Influence of internally dropped-off plies on the impact damage of asymmetrically tapered laminated CFRP

被引：29

作者：

Abdulhamid, Hakim ^{[1
,2
,3
,4
]}

Bouvet, Christophe ^{[1
,2
,3
]}

Michel, Laurent ^{[1
,2
,3
]}

Aboissiere, Jacky ^{[4
]}

Minot, Clement ^{[4
]}

机构：

[1] Univ Toulouse, F-31055 Toulouse 4, France

[2] INSA, UPS, Mines ALBI, ISAE, F-31055 Toulouse 4, France

[3] Inst Clement Ader, Inst Super Aeronaut & Espace, F-31055 Toulouse 4, France

[4] Sogeti High Tech, F-31703 Blagnac, France

来源：

COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING | 2015年 / 68卷

关键词：

Carbon fibre; Impact behaviour; Damage mechanics; Ply drop-off; DISCRETE INTERFACE ELEMENTS; FAILURE MECHANISMS; COMPOSITE PANELS; COMPRESSION; STRENGTH; DELAMINATION; SIMULATION; TENSION;

D O I：

10.1016/j.compositesa.2014.09.024

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

This paper presents an experimental study of low velocity impact response of carbon/epoxy asymmetrically tapered laminates. The tests are realised at energy between 10 and 30J on two types of layup with multiple terminated plies. The type and localisation of damage are analysed using C-scan and micrographs. Then, the data is compared with the response of corresponding respective plain laminate. The effects of some tapering parameters (taper angle, drop-off disposition and configuration) on the impact damage mechanisms are also investigated. Very similar impact damage phenomena are found between tapered and plain laminates. The presence of material discontinuity due to the resin pocket affects less the damage mechanism than the structural difference between the thick and the thin sections. (C) 2014 Elsevier Ltd. All rights reserved.

引用

页码：110 / 120

页数：11

共 29 条

[1]

Abrate S., 2005, Impact on Composite Structures

[2]

Airbus Industrie, 2008, REF STRUCT DES PRINC, V2

[3] Mesomodeling of delamination: towards industrial applications [J].