Experimental investigation on different positional impact damages and shear-after-impact (SAI) behaviors of stiffened composite panels

被引：19

作者：

Feng, Yu ^{[1
]}

He, Yuting ^{[1
]}

Tan, Xiangfei ^{[1
]}

An, Tao ^{[1
]}

Zheng, Jie ^{[2
]}

机构：

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

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

来源：

COMPOSITE STRUCTURES | 2017年 / 178卷

基金：

中国国家自然科学基金;

关键词：

Stiffened composite panel; BVID; SAI; Buckling mode/load; Failure mode/load; PROGRESSIVE FAILURE; AIRFRAME STRUCTURES; TEMPERATURE-CHANGE; FATIGUE LIFE; EDGE SHEAR; COMPRESSION; DELAMINATION; PERFORMANCE; SIMULATION; PREDICTION;

D O I：

10.1016/j.compstruct.2017.06.053

中图分类号：

O3 [力学];

学科分类号：

08 ; 0801 ;

摘要：

Buckling and postbuckling performances of stiffened composite panels with different positional impact damage under in-plane shear load were investigated. Barely visible impact damage (BVID) was introduced into three different positions with the same impact energy of 50 J. Damage areas and impact crater depths were both measured and their relationship in each impact position was affirmed. Shear after impact (SAI) experiments were conducted on the damaged specimens. Compared with pristine panels, the impact damaged panels showed a similar buckling mode during the shear process, which was three buckling waves in each skin bay without buckling transition, but had a far different failure mode. Additionally, the changes in buckling and failure load both were different depending on the impact position. The most serious decline in buckling and failure load was caused by the combination of material properties degradation and debonding due to the impact damage. (C) 2017 Elsevier Ltd. All rights reserved.

引用

页码：232 / 245

页数：14

共 30 条

[1] Progressive failure studies of stiffened panels subjected to shear loading [J].

Ambur, DR ;

Jaunky, N ;

Hilburger, MW .

COMPOSITE STRUCTURES, 2004, 65 (02) :129-142

[2]

[Anonymous], GAO11849

[3] Fatigue life and damage tolerance of postbuckled composite stiffened structures with initial delamination [J].

Davila, Carlos G. ;

Bisagni, Chiara .

COMPOSITE STRUCTURES, 2017, 161 :73-84

[4] 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

[5] Future structural stability design for composite space and airframe structures [J].

Degenhardt, Richard ;

Castro, Saullo G. P. ;

Arbelo, Mariano A. ;

Zimmerman, Rolf ;

Khakimova, Regina ;

Kling, Alexander .

THIN-WALLED STRUCTURES, 2014, 81 :29-38

[6] Effect of impact damage positions on the buckling and post-buckling behaviors of stiffened composite panel [J].

Feng, Yu ;

Zhang, Haoyu ;

Tan, Xiangfei ;

He, Yuting ;

An, Tao ;

Zheng, Jie .

COMPOSITE STRUCTURES, 2016, 155 :184-196

[7] Investigation on tension-tension fatigue performances and reliability fatigue life of T700/MTM46 composite laminates [J].

Feng, Yu ;

Gao, Chao ;

He, Yuting ;

An, Tao ;

Fan, Chaohua ;

Zhang, Haoyu .

COMPOSITE STRUCTURES, 2016, 136 :64-74

[8] Effect of hygrothermal condition on buckling and post-buckling performance of CCF300/5228A aero composite stiffened panel under axial compression [J].

Feng, Yu ;

He, Yuting ;

An, Tao ;

Cui, Ronghong ;

Shao, Qing ;

Fan, Chaohua .

JOURNAL OF REINFORCED PLASTICS AND COMPOSITES, 2015, 34 (12) :989-999

[9] THE USE OF COMPOSITES IN AIRCRAFT PRIMARY STRUCTURE [J].

FREEMAN, WT .

COMPOSITES ENGINEERING, 1993, 3 (7-8) :767-775

[10] Effects of imperfections on the buckling response of compression-loaded composite shells [J].

Hilburger, MW ;

Starnes, JH .

INTERNATIONAL JOURNAL OF NON-LINEAR MECHANICS, 2002, 37 (4-5) :623-643

← 1 2 3 →