Damage initiation and propagation mechanisms of 3-D angle-interlock woven composites under thermo-oxidative aging

2021 ◽  
Vol 259 ◽  
pp. 113462
Author(s):  
Yanan Ke ◽  
Baozhong Sun ◽  
Bohong Gu ◽  
Wei Zhang
Keyword(s):  
Woven Composites ◽  
Oxidative Aging ◽  
Damage Initiation ◽  
Initiation And Propagation

Damage Initiation and Evolution in Woven Composites

2001 ◽  
Author(s):  
Xiaodong Tang ◽  
John D. Whitcomb
Keyword(s):  
Three Dimensional ◽  
Woven Composites ◽  
Element Analysis ◽  
Damage Initiation ◽  
Loss And Damage ◽  
Dimensional Finite Element ◽  
Strain Relationship ◽  
Three Dimensional Finite Element ◽  
Stiffness Loss ◽  
Damage Initiation And Evolution

Abstract The damage initiation and evolution mechanisms in plain and satin weave composites were studied using three-dimensional finite element analysis. The tow paths of the weave were selected such that the wavy region of the tows were identical in both weaves. The damage initiation and evolution behaviors in these comparable wavy regions were compared and discussed in terms of stress components that initiate damage, the overall stress/strain relationship and the accumulation of the damaged volume in the warp tow, fill tow and matrix pockets. The results showed significant similarities in many aspects of the damage behaviors such as damage modes, stiffness loss and damage accumulation processes.

Numerical and digital image correlation analysis of tensile behavior of thin-ply hybrid laminates with discontinuous carbon sandwiched by continuous glass and carbon

2021 ◽  
pp. 002199832110565
Author(s):  
Amos Ichenihi ◽  
Wei Li ◽  
Li Zhe
Keyword(s):  
Digital Image Correlation ◽  
Digital Image ◽  
Element Model ◽  
Image Correlation ◽  
Continuous Glass ◽  
Damage Initiation ◽  
3D Digital Image Correlation ◽  
Initiation And Propagation ◽  
Hybrid Laminates ◽  
Strain Increase

Thin-ply hybrid laminates of glass and carbon fibers have been widely adopted in engineering pseudo-ductility. In this study, a Finite Element model is proposed using Abaqus to predict pseudo-ductility in thin-ply laminates consisting of three materials. These materials comprise continuous carbon (CC) and continuous glass sandwiching partial discontinuous carbon (DC). The model adopts the Hashin criterion for damage initiation in the fibers and the mixed-mode Benzeggagh-Kenane criterion on cohesive surfaces for delamination initiation and propagation. Numerically predicted stress–strain results are verified with experimental results under tensile loading. Results show pseudo-ductility increases with the increase in DC layers, and pseudo-yield strength and strain increase with the increase in CC layers. 3D-Digital Image Correlation results indicate delamination growth on pseudo-ductile laminates, and the calculated Poisson’s ratios show pseudo-ductility occurs below 0.27. Moreover, Poisson’s ratio decreases with an increase in pseudo-ductility.

Damage Progress Simulation in Unidirectional Composites by Extended Finite Element Method (XFEM)

2010 ◽  
Vol 152-153 ◽  
pp. 73-76 ◽  
Author(s):  
Huai Wen Wang ◽  
Qing Hua Qin ◽  
Hong Wei Zhou ◽  
Hui Miao
Keyword(s):  
Finite Element Method ◽  
Finite Element ◽  
Extended Finite Element Method ◽  
Independent Solution ◽  
Single Fibre ◽  
Extended Finite Element ◽  
Damage Initiation ◽  
Initiation And Propagation ◽  
As Stress ◽  
Element Method

Damage initiation and propagation in unidirectional glass fibre reinforced epoxy matrix composites under tension load were simulated in this study. Cell models with either single fibre or multiple fibres were modelled by extended finite element method (XFEM). The damage progress in the cells was investigated and then the nominal stress-strain curves as well as stress distributions in the fibre and matrix were obtained. Results presented here indicate that the extended finite element method is an effective modelling technique to study the initiation and propagation of a crack along an arbitrary, mesh-independent, solution-dependent path.

Damage Initiation and Propagation in Hybrid Composite Structures

2018 ◽  
Author(s):  
Masoud Yekani Fard ◽  
Brian Raji ◽  
John Woodward ◽  
Mateo Oramas ◽  
Michael Padilla ◽  
...  
Keyword(s):  
Hybrid Composite ◽  
Composite Structures ◽  
Damage Initiation ◽  
Initiation And Propagation

Guidelines and Limitations of the Compact Compression Specimen

2019 ◽  
Author(s):  
David J. Plechaty ◽  
Kevin T. Carpenter ◽  
John P. Parmigiani
Keyword(s):  
Carbon Fiber ◽  
Test Specimen ◽  
Loading Rate ◽  
Material Models ◽  
Damage Initiation ◽  
Matrix Compression ◽  
Initiation And Propagation ◽  
Back Edge ◽  
Notch Length ◽  
Compression Damage

Abstract Damage initiation and propagation material models for carbon fiber composites can be categorized according to the loading applied to constituent components. An example of such categorization is fiber tension, fiber compression, matrix tension, and matrix compression material models. Of these, matrix compression has been by far the least studied based on amount of published literature. Recent work at Oregon State University (OSU) has begun to address this lack of study. OSU researchers have published several papers culminating in the specification of an effective test specimen for isolating matrix compression damage initiation and propagation in carbon fiber laminates. While providing compelling results indicating the effectiveness and usefulness of this test specimen, little or no information has been provided regarding its manufacture, usable notch lengths, and optimum loading rate during testing. Experience at OSU has shown that this information is critical and not trivial to obtain. The purpose of this paper is to provide specific guidelines and “lessons learned” needed for other researchers to efficiently and effectively use this specimen in a comprehensive study. Test specimens are manufactured in the OSU Composites Materials Manufacturing Laboratory using typical commercial pre-peg carbon fiber following the specified layup and curing procedures. Once the material was cured the carbon fiber plate was then water-jet cut into the desired geometry and notch length. Usable notch length and optimum loading rate was determined by testing a series of specimens. All testing was conducted at an OSU lab using a universal testing machine with Digital Image Correlation (DIC) data collected. Specimens were preloaded and matrix compression initiation and propagation data collected until tensile failure occurred on the back edge of the specimen. Testing showed that shorter notch lengths result in inconsistent data and longer in effective initiation but limited propagation due to reduced ligament length. Testing suggested that a speed less than 5 mm/min gave the best results as faster displacement rates caused less crack propagation to occur, while increasing the likelihood of the specimen to fail in tension along its back edge. Through the use of these guidelines, researchers are able to manufacture and use an effective test specimen for the investigation of matrix compression damage initiation and propagation.

scholarly journals Experimental and numerical investigation of interface damage in composite L-angle sections under four-point bending

2020 ◽  
Vol 55 (2) ◽  
pp. 187-200
Author(s):  
Xi Zou ◽  
Shibo Yan ◽  
Mikhail Matveev ◽  
James P Rouse ◽  
I Arthur Jones
Keyword(s):  
Numerical Study ◽  
Cohesive Element ◽  
Interlaminar Stresses ◽  
Damage Initiation ◽  
Interface Damage ◽  
Four Point Bending ◽  
Initiation And Propagation ◽  
Bending Load ◽  
Modelling Strategies ◽  
Cohesive Surface

Curved laminates in aero-structures, such as the L-angle sections where webs and flanges meet, are prone to delamination due to high interlaminar stresses in these regions. Some efforts to investigate delamination in these structures can be found in the literature but commonly structures are limited to unidirectional layups or modelling approaches are constrained to the cohesive element based methods. In this work, multi-directional L-angle laminates were manufactured using unidirectional prepregs and tested under four-point bending load conditions to examine the interface damage. Acoustic emission technique was used to assist the capture of damage initiation and propagation. Three interface modelling strategies for predicting delamination, namely cohesive element, cohesive surface and perfectly bonded interface were used in the numerical study. The interface damage behaviour was successfully predicted by the simulation methods and differences among the strategies were compared.

A progressive damage model for 3D woven composites under compression

2018 ◽  
Vol 28 (6) ◽  
pp. 857-876 ◽  
Author(s):  
Huaiyu Lu ◽  
Licheng Guo ◽  
Gang Liu ◽  
Li Zhang
Keyword(s):  
Failure Modes ◽  
Damage Model ◽  
Woven Composites ◽  
Progressive Damage ◽  
Misalignment Angle ◽  
Woven Composite ◽  
Damage Initiation ◽  
3D Woven Composites ◽  
Progressive Damage Model ◽  
Transverse Failure

A progressive damage model is proposed to investigate the damage initiation and evolution of 3D woven composites under uniaxial compression at a micromechanical level. The typical compressive experiments were carried out. Based on the observations, the compression failure modes of 3D woven composites mainly include fiber kinking, transverse failure of fiber tow, matrix fracture, and interfacial debonding. The initial damage criteria are according to the physically based failure criteria for the fiber kinking, the Puck criteria for the transverse failure of fiber tow, and the maximum stress criterion for the matrix. The damage of fiber tow–matrix interfacial is simulated through cohesive contact. Particularly, the fiber’s initial misalignment angle is taken into account in the damage model. The simulated compression results agree well with the experimental ones. The compressive stress–strain response of the 3D woven composite is forecasted. The damage evolution of each constituent of the 3D woven composite is obtained. The results show that the influence of the fiber’s initial misalignment angle on the compression strength of the 3D woven composite needs to be considered.

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