Experimental study of the low-velocity impact behaviour of primary sandwich structures in aircraft

被引：49

作者：

Leijten, Joris ^{[1
]}

Bersee, Harald E. N. ^{[1
]}

Bergsma, Otto K. ^{[1
]}

Beukers, Adriaan ^{[1
]}

机构：

[1] Tech Univ Delft, Fac Aerosp Engn, Dept Design & Prod Composite Struct, NL-2629 HS Delft, Netherlands

来源：

COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING | 2009年 / 40卷 / 02期

关键词：

Impact behaviour; Mechanical properties; Damage tolerance; Non-destructive testing; PANELS; DAMAGE; COMPOSITES; STRENGTH;

D O I：

10.1016/j.compositesa.2008.10.019

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

The susceptibility of sandwich structures to localised (impact) damage is one of the main reasons wily the sandwich concept is not yet used in large primary aircraft structures of airliners. The objective of this work is to experimentally investigate the damage tolerance of representative composite sandwich panels for primary aircraft structures. Instrumented low-velocity impact tests were performed oil sandwich Specimens consisting of carbon Non-Crimp Fabric/epoxy facings and a Rohacell (PMI) foam core. Both internal and external damage resulting from these impact events was evaluated. The foam core material has a considerable influence oil the amount of damage detected by ultrasonic TTU C-scan. CAI tests however showed that this core damage has no significant influence on the residual compressive strength of the specimens. (C) 2008 Elsevier Ltd. All rights reserved.

引用

页码：164 / 175

页数：12

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