The postbuckling behaviour of adhesively bonded stiffened panels subjected to in-plane shear loading

被引：17

作者：

Guedes Villani, Anaisa de Paula ^{[1
]}

Donadon, Mauricio V. ^{[1
]}

Arbelo, Mariano A. ^{[1
]}

Rizzi, Paulo ^{[1
]}

Montestruque, Carlos V. ^{[1
]}

Bussamra, Flavio ^{[1
]}

Rodrigues, Marcelo R. B. ^{[2
]}

机构：

[1] Inst Tecnol Aeronaut ITA IEA, Sao Jose Dos Campos, SP, Brazil

[2] Empresa Brasileira Aeronaut Embraer, Sao Jose Dos Campos, SP, Brazil

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2015年 / 46卷

关键词：

Adhesive; Post-buckling; Finite elements; Mechanical characterization; COMPOSITE; DELAMINATION; FAILURE;

D O I：

10.1016/j.ast.2015.06.028

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

This paper presents a detailed investigation on the post-buckling behaviour of adhesively bonded stiffened panels subjected to in-plane shear loading. An experimental programme was carried to determine the buckling load, buckling shape, collapse load and failure modes of two bonded stiffened panels. A nonlinear finite element based modelling approach, accounting for geometrical and material nonlinearities as well as progressive failure in the adhesively bonded interface between the skin and the stiffener is proposed to predict the structural behaviour of the panels up to failure. This approach consists in inodelling the bonded interfaces using a newly developed cohesive zone based constitutive damage model. In order to account for damage in the stiffener and the skin a Von Mises based constitutive damage model is also formulated and presented in the paper. Both constitutive models were implemented into ABAQUS/Explicit finite element code as user-defined material models. A very good agreement between experimental results and numerical predictions is obtained using the proposed modelling approach, with deviations smaller than 8% in buckling load and bonded interface failure load onset. (C) 2015 Elsevier Masson SAS. All rights reserved.

引用

页码：30 / 41

页数：12

共 28 条

[21] Thermal Postbuckling Behavior of Laminated Composite Spherical Shell Panel Using NFEM# [J].

Panda, S. K. ;

Singh, B. N. .

MECHANICS BASED DESIGN OF STRUCTURES AND MACHINES, 2013, 41 (04) :468-488

[22] Post-Buckling Analysis of Laminated Composite Doubly Curved Panel Embedded with SMA Fibers Subjected to Thermal Environment [J].

Panda, S. K. ;

Singh, B. N. .

MECHANICS OF ADVANCED MATERIALS AND STRUCTURES, 2013, 20 (10) :842-853

[23] Thermal post-buckling analysis of a laminated composite spherical shell panel embedded with shape memory alloy fibres using non-linear finite element method [J].

Panda, S. K. ;

Singh, B. N. .

PROCEEDINGS OF THE INSTITUTION OF MECHANICAL ENGINEERS PART C-JOURNAL OF MECHANICAL ENGINEERING SCIENCE, 2010, 224 (C4) :757-769

[24] Thermal post-buckling behaviour of laminated composite cylindrical/hyperboloid shallow shell panel using nonlinear finite element method [J].

Panda, S. K. ;

Singh, B. N. .

COMPOSITE STRUCTURES, 2009, 91 (03) :366-374

[25]

SHUART MJ, 1983, 2153 NASA

[26]

Singer J., 1998, BUCKLING EXPT EXPT M, V1

[27]

United States, 2003, MIL HDBK 5J MET MAT

[28]

WU EM, 1965, 275 U ILL T AM

← 1 2 3 →