Effect of fatigue loading on impact damage and buckling/post-buckling behaviors of stiffened composite panels under axial compression

被引：23

作者：

Feng, Yu ^{[1
]}

He, Yuting ^{[1
]}

Zhang, Haoyu ^{[1
]}

Tan, Xiangfei ^{[1
]}

An, Tao ^{[1
]}

Zheng, Jie ^{[2
]}

机构：

[1] Air Force Engn Univ, Aeronaut & Astronaut Engn Coll, Xian 710038, Peoples R China

[2] Aviat Ind Corp, Aircraft Inst 1, Xian 710089, Peoples R China

来源：

COMPOSITE STRUCTURES | 2017年 / 164卷

基金：

中国国家自然科学基金;

关键词：

Stiffened composite panels; Impact; Fatigue loading; Buckling; Post-buckling; LOW-VELOCITY IMPACT; POSTBUCKLING BEHAVIOR; CURVED PANELS; SIMULATION; PREDICTION; DESIGN;

D O I：

10.1016/j.compstruct.2016.12.069

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

Effect of fatigue loading on impact damage and buckling/post-buckling behaviors of stiffened composite panels under axial compression were studied in this paper. Barely visible impact damage (BVID) was introduced to stiffened composite panels. Damage areas and crater depths data were analyzed and their distributions were determined, whose upper limits were also calculated under different reliability. Then fatigue experiments were conducted on impact specimens. Damage areas, damage site shapes and crater depths were measured at every certain fatigue cycles. Compression after impact (CAI) as well as compression after impact and fatigue (CALF) were also studied, with a comparison of virgin specimens. The results exhibited impact damage and the following fatigue loading had no obvious influence on the bucking load and buckling modes. Additionally, failure modes of all types of specimens were similar, which included debonding and fracture of stiffeners together with splitting and cracking of skin bays. However, the average failure load of impact specimens decreased 9.9% compared to that of virgin specimens. Fatigue loading would lead a further decrease about 6.1% in failure load compared to impact specimens, although the impact damage had no obvious changes during and after fatigue loading. (C) 2016 Elsevier Ltd. All rights reserved.

引用

页码：248 / 262

页数：15

共 37 条

[1] BUCKLING AND POSTBUCKLING BEHAVIOR OF LAMINATED COMPOSITE STRINGER STIFFENED CURVED PANELS UNDER AXIAL COMPRESSION: EXPERIMENTS AND DESIGN GUIDELINES [J].

Abramovich, Haim ;

Weller, Tanchum .

JOURNAL OF MECHANICS OF MATERIALS AND STRUCTURES, 2009, 4 (7-8) :1187-1207

[2]

[Anonymous], GAO11849

[3] Elastic buckling analysis of single-walled carbon nanotube under combined loading by using the ANSYS software [J].

Arani, A. Ghorbanpour ;

Rahmani, R. ;

Arefmanesh, A. .

PHYSICA E-LOW-DIMENSIONAL SYSTEMS & NANOSTRUCTURES, 2008, 40 (07) :2390-2395

[4] Electro-thermo-torsional buckling of an embedded armchair DWBNNT using nonlocal shear deformable shell model [J].

Arani, A. Ghorbanpour ;

Abdollahian, M. ;

Kolahchi, R. ;

Rahmati, A. H. .

COMPOSITES PART B-ENGINEERING, 2013, 51 :291-299

[5] Electro-thermo-mechanical buckling of DWBNNTs embedded in bundle of CNTs using nonlocal piezoelasticity cylindrical shell theory [J].

Arani, A. Ghorbanpour ;

Amir, S. ;

Shajari, A. R. ;

Mozdianfard, M. R. .

COMPOSITES PART B-ENGINEERING, 2012, 43 (02) :195-203

[6] Buckling analysis of laminated composite rectangular plates reinforced by SWCNTs using analytical and finite element methods [J].

Arani, A. Ghorbanpour ;

Maghamikia, Sh. ;

Mohammadimehr, M. ;

Arefmanesh, A. .

JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY, 2011, 25 (03) :809-820

[7]

Chen Chuanyao, 2002, Fatigue and Fracture

[8]

CHEN Y, 2002, MATER SCI ENG, V20, P376

[9] COCOMAT - improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse [J].

Degenhardt, R ;

Rolfes, R ;

Zimmermann, R ;

Rohwer, K .

COMPOSITE STRUCTURES, 2006, 73 (02) :175-178

[10] Predicting low-velocity impact damage on a stiffened composite panel [J].

Faggiani, A. ;

Falzon, B. G. .

COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING, 2010, 41 (06) :737-749

← 1 2 3 4 →