Progressive failure analysis of unidirectional-fabric laminated composite joints under pin-loading

被引：0

作者：

Kweon, Jin-Hwe ^{[1
]}

Son, Hee-Jin ^{[1
]}

Choi, Ji-Young ^{[1
]}

Shin, So-Young ^{[2
]}

Choi, Jin-Ho ^{[1
]}

Lee, Gun-Myung ^{[1
]}

机构：

[1] Gyeongsang Natl Univ, Res Ctr Aircraft Parts Technol, Sch Mech & Aerosp Engn, Jinju 660701, Gyeongnam, South Korea

[2] MSC Softeare Korea, Gyeonggi 463804, South Korea

来源：

ADVANCES IN COMPOSITE MATERIALS AND STRUCTURES, PTS 1 AND 2 | 2007年 / 334-335卷

关键词：

composite; joint; progressive failure; strength;

D O I：

10.4028/www.scientific.net/KEM.334-335.1

中图分类号：

TQ174 [陶瓷工业]; TB3 [工程材料学];

学科分类号：

0805 ; 080502 ;

摘要：

A two-dimensional progressive failure analysis is conducted to predict the failure loads and modes of carbon-epoxy composite joints under pin-loading. An eight-node laminated shell element is used for the finite element modeling. Post-failure stiffness is evaluated based on the complete unloading model combined with various failure criteria. The comparison of finite element and experimental results shows that the finite element analysis based on the combined maximum stress and Yamada-Sun criteria most accurately predicts the failure loads of the composite laminated joints.

引用

页码：1 / +

页数：2

共 9 条

[1]

Bathe K, 2007, Finite element procedures

[2] A progressive damage model for mechanically fastened joints in composite laminates [J].