Modeling and Experimental Validation of Composite Stiffened Panels under Uniaxial Tension

Hong Qing Wang; Qun Yan; Zong Hong Xie; Xiao Dong Sui

doi:10.4028/www.scientific.net/AMR.791-793.415

Paper Titles

Nano SiO₂/Cellulose Composite Films Prepared via Ionic Liquids
p.398

Analysis of Release Behavior of Pressure Sensitive MF-Resin Microcapsules Containing CVL
p.402

The Effect of Magnetron Co-Sputtering Parameters on the Microhardness of TiZrN Thin Films
p.407

The Finite Element Numerical Simulation of the Temperature Distribution of the Glass that under the Irradiation of Laser
p.411

Modeling and Experimental Validation of Composite Stiffened Panels under Uniaxial Tension
p.415

The Research on Glass Transition Temperature of Ionic Liquids Using DFT Method
p.419

Preparation of Hydroxylated Carbon Nanotubes/Magnetic Iron Oxide Compound Particles
p.423

Finite Element Analysis of the Process of the Metal Liquid Flows in the Die Cavity
p.427

Influence of Tempering Temperature on Microstructure and Mechanical Properties of 35CrMnSiMo Cast Steel
p.431

HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 791-793Modeling and Experimental Validation of Composite...

Modeling and Experimental Validation of Composite Stiffened Panels under Uniaxial Tension

Abstract:

A finite element model implemented with a progressive damage propagation mechanism was generated to study the mechanical behavior of stiffened composite panels under uniaxial tension. Typical damage modes including fiber breakage, matrix crushing and delamination were considered in the model. Failure criteria with corresponding stiffness degradation technologies was used to predict the initiation and evolution of intra-laminar damage modes by a user-defined subroutine. Cohesive elements with thickness of 0.01mm were defined along the interface areas between the filler and the adjacent laminate layers for predicting the initiation and propagation of delamination. Corresponding tests on composite stiffened panel with a web cut-out were conducted. A good correlation between the numerical results and test data was obtained, which validated the finite element models. Both the numerical and experimental results conclude that the delamination in the flange around the cut-out region is the most critical failure mode for the composite stiffened panel under the uniaxial tensile load.

You might also be interested in these eBooks

View Preview

Info:

Periodical:

Advanced Materials Research (Volumes 791-793)

Pages:

415-418

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.791-793.415

Citation:

Cite this paper

Online since:

September 2013

Authors:

Hong Qing Wang, Qun Yan, Zong Hong Xie, Xiao Dong Sui

Keywords:

Composite Stiffened Panel, Finite Element Analysis (FEA), Uniaxial Tension, Validation

Export:

RIS, BibTeX

Price:

Permissions CCC:

Request Permissions

Permissions PLS:

Request Permissions

Сopyright:

Citation:

References

[1] Zhen Shen, Xiaojing Zhang: An introduction to design and verification for composite aircraft structures. Shanghai Jiao Tong University Press, Shanghai (2011).

Google Scholar

[2] Christos kassapoglou: Design and analysis of composite structures with applications to aerospace structures. John Wiley and sons, United Kingdom (2010).

Google Scholar

[3] J.N. Reddy: Mechanics of laminated composite plates and shells: theory and analysis. CRC Press, Boca Raton (2004).

Google Scholar

[4] Hashin Z: Failure criteria for unidirectional fiber composites. Journal of Applied Mechanics, Vol. 47 (1980), pp.329-334.

DOI: 10.1115/1.3153664

Google Scholar

[5] ABAQUS Inc.: ABAQUS version 6. 10 user's manual, Pawtucket, RI, USA (2010).

Google Scholar