Effect of the stiffener stiffness on the buckling and post-buckling behavior of stiffened composite panels - Experimental investigation

被引：59

作者：

Zhu, Shuhua ^{[1
]}

Yan, Jiayi ^{[1
]}

Chen, Zhi ^{[1
]}

Tong, Mingbo ^{[1
]}

Wang, Yuequan ^{[1
]}

机构：

[1] Nanjing Univ Aeronaut & Astronaut, Key Lab Fundamental Sci Natl Def Adv Design Techn, Nanjing 210016, Jiangsu, Peoples R China

来源：

COMPOSITE STRUCTURES | 2015年 / 120卷

基金：

中国国家自然科学基金;

关键词：

Stiffened composite panels; Equivalent stiffness; Buckling; Post-buckling; Failure; Compression test; AIRFRAME STRUCTURES; CYLINDRICAL-SHELLS; COLLAPSE; COMPRESSION; STRENGTH; FAILURE; SIMULATION; PREDICTION; DESIGN; PLATES;

D O I：

10.1016/j.compstruct.2014.10.021

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

The purpose of this paper was to study the effect of I-shape stiffener stiffness on the buckling and post-buckling, up to collapse behavior of stiffened composite panel under the uniform uniaxial compression load. Six stiffened composite panel configurations, which were orthogonally designed with two skin configurations and three I-shape stiffener configurations, were took into account in the experimental investigation. Three specimens for each configuration (18 specimens in total) were manufactured for test. Before tests, the key dimensions of I-stiffener and skin were measured. Furthermore, all the specimens were also inspected visually and detected by the ultrasonic C-scan system. No initial delamination or debonding area was found on all the specimens according to their C-scan images. The experimental results show that the equivalent compression stiffness of I-shape stiffener has great influence on the buckling load and failure mode of stiffened panel, but a little effect on the failure load of stiffened panel. The skin thickness has great impact on the buckling load and the final failure load. (C) 2014 Elsevier Ltd. All rights reserved.

引用

页码：334 / 345

页数：12

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