Metis Element Model for Interlaminar Stresses in Composite Laminates

2009 ◽  
Author(s):  
N.T. Duong ◽  
H. Nguyen Dang
Keyword(s):  
Composite Laminates ◽  
Element Model ◽  
Interlaminar Stresses

scholarly journals Evaluation of Interlaminar Stresses in Composite Laminates with a Bolt-Filled Hole Using a Linear Elastic Traction-Separation Description

2017 ◽  
Vol 7 (1) ◽  
pp. 93
Author(s):  
Yong Cao ◽  
Yunwen Feng ◽  
Xiaofeng Xue ◽  
Wenzhi Wang ◽  
Liang Bai
Keyword(s):  
Composite Laminates ◽  
Interlaminar Stresses ◽  
Linear Elastic

Damage Control in Composite Laminates

2001 ◽  
Author(s):  
Alexander P. Suvorov ◽  
George J. Dvorak
Keyword(s):  
Composite Laminates ◽  
Composite Laminate ◽  
Damage Control ◽  
Thermomechanical Loading ◽  
Interlaminar Stresses ◽  
Damage Resistance ◽  
Viscoelastic Composite ◽  
Mechanical Loads ◽  
Composite Damage ◽  
The Matrix

Abstract Several effects that fiber prestress may have on stress redistribution in the plies of composite laminates and in the phases of individual plies are illustrated. These include improvement of composite damage resistance under tensile mechanical loads, reduction/cancelation of interlaminar stresses at free edges of composite laminate subjected to thermomechanical loading, and stress relaxation in the matrix phase of viscoelastic composite laminates. Specific results are found for quasi-isotropic and cross-ply symmetric S-glass/epoxy and carbon/epoxy AS4/EPON 828 laminates.

Interlaminar stresses in composite laminates with a circular hole

1997 ◽  
Vol 37 (2) ◽  
pp. 223-232 ◽  
Author(s):  
F.Z. Hu ◽  
C. Soutis ◽  
E.C. Edge
Keyword(s):  
Circular Hole ◽  
Composite Laminates ◽  
Interlaminar Stresses

Study of Interlaminar Stresses in Composite Laminates Subjected to Torsional Loading

AIAA Journal ◽  
2001 ◽  
Vol 39 (7) ◽  
pp. 1374-1382 ◽  
Author(s):  
John A. Mitchell ◽  
J. N. Reddy
Keyword(s):  
Composite Laminates ◽  
Interlaminar Stresses ◽  
Torsional Loading

A Preliminary Study on the Mechanical Performance of Tiled Polymer Composites

2006 ◽  
Author(s):  
M. A. Qidwai ◽  
J. N. Baucom ◽  
A. C. Leung ◽  
J. P. Thomas
Keyword(s):  
Composite Laminates ◽  
Load Transfer ◽  
Mechanical Performance ◽  
Local Stress ◽  
Superior Performance ◽  
Design Parameters ◽  
Interlaminar Stresses ◽  
Stress Concentrations ◽  
Critical Design ◽  
Composite Joint

We are developing and exploring the concept of in-plane tiling of composite laminates, called MOSAIC, to mitigate or control delamination at free edges due to interlaminar stresses. Initial mechanical testing has shown that MOSAIC composites with uniaxial graphite-fiber reinforced tiles retain the stiffness levels of traditional uniaxially reinforced composites but with reduced strength. The reduction in strength is attributed to the formation of resin-rich pockets between adjacent tiles. In this study, we have performed detailed finite element analyses to identify the critical design parameters that affect the mechanical performance of uniaxially reinforced MOSAIC composites. We have found that using continuous laminae on the outer surfaces significantly increases the overall loadcarrying capacity. Increasing aspect ratio of the pocket and decreasing material property differences between resin and tiles also cause better load transfer between tiles but may not necessarily improve overall strength due to increasing stress concentration. The tiling scheme and density of pocket placement influence the interaction of local stress concentrations. Consequently, a novel composite joint is proposed and found to have superior performance.

scholarly journals Effect of Gap and Shims on the Strain and Stress State of the Composite-Aluminum Hybrid Bolted Structure

2020 ◽  
Vol 2020 ◽  
pp. 1-19
Author(s):  
Xuande Yue ◽  
Luling An ◽  
Xin Ye ◽  
Chufan Wang ◽  
Yuebo Cai ◽  
...  
Keyword(s):  
Stress State ◽  
Strain Measurement ◽  
Strain Field ◽  
Composite Laminates ◽  
Element Model ◽  
Local Damage ◽  
Damage State ◽  
Assembly Structure ◽  
Bolt Connection ◽  
The Finite Element Model

The composite-aluminum hybrid bolted structures are widely used in aircraft. Due to low molding accuracy of composite components, gaps always occur between components during assembly. In this case, the bolt connection can cause a complex strain and stress state of component. It may adversely affect the mechanical properties or cause local damage of the structure. A simplified model of the composite-aluminum assembly structure was established in this paper. Then, the influence of forced assembly, liquid shim, and peelable fiberglass shim on the strain and stress state of the composite-aluminum hybrid bolted structure was studied. A bolt connection experimental device was designed to apply a preload to the specimen. The strain field on the specimen surface was measured using the 3D-DIC strain measurement system. The finite element model was established to study the interlaminar stress and damage state of composite laminates. It is found that the strain of specimen in the X -direction is mainly affected by the bending deformation, while the strain in the Y -direction is mainly affected by the compression of bolt head. For composite laminates, the strain value in the X -direction can be reduced by 8.31%-70.97% with shims. As for the strain value in the Y -direction, the liquid shim can only reduce it up to 23.93%when the gap is large. In addition, the liquid shim and peelable fiberglass shim cannot reduce the stress value of all interlaminar elements, but it can make the stress distribution more uniform and improve the stress state of the interlaminar element when the shim was more than 0.8 mm.

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