Post-buckling behaviour of flat stiffened composite panels: Experiments vs. analysis

被引:50
作者
Boni, L. [1 ]
Fanteria, D. [1 ]
Lanciotti, A. [1 ]
机构
[1] Univ Pisa, Dipartimento Ingn Aerosp, I-56122 Pisa, Italy
关键词
Post-buckling; Composite stiffened panel; Finite element analysis; CYLINDRICAL-SHELLS; COMPRESSION; IMPERFECTIONS; COLLAPSE; DESIGN; SIMULATION;
D O I
10.1016/j.compstruct.2012.06.005
中图分类号
O3 [力学];
学科分类号
08 ; 0801 ;
摘要
The paper is focused on the development of a validated procedure for modelling, by means of Finite Element tools, the post-buckling behaviour of stiffened composite flat panels subjected to compression loads. The experimental data for model validation were collected during a test campaign on two sets of CFRP flat stiffened panels. Tests are briefly described and selected experimental results, used for the validation phase, are presented. A detailed description of modelling strategies and analysis set up for post-buckling simulation is provided and some results of the sensitivity studies, which helped in fine-tuning the model of the test specimens, are reported as well. Finally, a through comparison of the model results with the experimental data is presented and commented. The final validation is accomplished not only by qualitatively comparing the buckled shape of the panels numerically predicted with those observed in the experiments, but also by quantitatively evaluating the differences between predicted and measured strains and out-of-plane displacements. The comparison between numerical and experimental results highlights the substantial effectiveness of the FEM approach in predicting the structural response of the panels in terms of buckling occurrence and of their post-buckling behaviour. (c) 2012 Elsevier Ltd. All rights reserved.
引用
收藏
页码:3421 / 3433
页数:13
相关论文
共 27 条
[11]   Postbuckling behaviour of a blade-stiffened composite panel loaded in uniaxial compression [J].
Falzon, BG ;
Stevens, KA ;
Davies, GO .
COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING, 2000, 31 (05) :459-468
[12]   Post-buckling behavior of composite panels in the presence of unstable delaminations [J].
Gaudenzi, P ;
Perugini, P ;
Riccio, A .
COMPOSITE STRUCTURES, 2001, 51 (03) :301-309
[13]   Weight optimisation of damage resistant composite panels with a posteriori cost evaluation [J].
Gigliotti, Marco ;
Riccio, Aniello ;
Luspa, Luigi ;
Scaramuzzino, Francesco ;
Mormile, Luigi .
COMPOSITE STRUCTURES, 2009, 88 (02) :312-322
[14]   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
[15]  
Huth H., 1986, ASTM, P221
[16]   Laminated composite structures subjected to compressive loading: A material and structural buckling analysis [J].
Laurin, F. ;
Carrere, N. ;
Maire, J.-F. .
COMPOSITE STRUCTURES, 2007, 80 (02) :172-182
[17]   Stiffener debonding mechanisms in post-buckled CFRP aerospace panels [J].
Meeks, C ;
Greenhalgh, E ;
Falzon, BG .
COMPOSITES PART A-APPLIED SCIENCE AND MANUFACTURING, 2005, 36 (07) :934-946
[18]   Degradation investigation in a postbuckling composite stiffened fuselage panel [J].
Orifici, A. C. ;
Thomson, R. S. ;
Degenhardt, R. ;
Kling, A. ;
Rohwer, K. ;
Bayandor, J. .
COMPOSITE STRUCTURES, 2008, 82 (02) :217-224
[19]   Analytical-experimental correlation for a stiffened composite panel loaded in axial compression [J].
Park, O ;
Haftka, RT ;
Sankar, VB ;
Starnes, JH ;
Nagendra, S .
JOURNAL OF AIRCRAFT, 2001, 38 (02) :379-387
[20]   Post-buckling behaviour of graphite/epoxy stiffened panels with initial imperfections subjected to eccentric biaxial compression loading [J].
Romeo, G ;
Frulla, G .
INTERNATIONAL JOURNAL OF NON-LINEAR MECHANICS, 1997, 32 (06) :1017-1033