Effect of drilling-induced defects on progressive damage of open-hole composite laminates under compression

This paper provides overall comparisons of the static results of an Air Force Research Laboratory exploration into the state of the art of existing technology in composite progressive damage analysis. In this study, blind and re-calibration bench-marking exercises were performed using nine different composite progressive damage analysis codes on unnotched and notched (open-hole) composite coupons under both static and fatigue loading. This paper summarizes the results of the static portion of this program. Comparisons are made herein of specimen stiffness and strength predictions against each other and the test data. Overall percent error data is presented, as well as a list of observations and lessons learned during this year-long effort.

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Recent Developments in Modelling of Progressive Damage in Fibre-Reinforced Composites

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.784.274 ◽

2015 ◽

Vol 784 ◽

pp. 274-283

Author(s):

Bo Yang Chen ◽

Tong Earn Tay

Keyword(s):

Composite Laminates ◽

Progressive Damage ◽

Reinforced Composites ◽

Matrix Cracks ◽

Reinforced Composite ◽

Recent Developments ◽

Open Hole ◽

Tension And Compression ◽

And Migration ◽

Fibre Reinforced Composites

This paper provides an overview of recent developments in the modeling of progressive damage in fiber-reinforced composite laminates. Some insights into modeling the size effects of open-hole composite laminates under in-plane tension and compression, the significance of ply-blocking and delamination are discussed. Recent interest in the interaction and migration of matrix cracks and delamination, resulting in development of integrated XFEM-CE and floating node methods will also be presented.

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Progressive damage modeling of open-hole composite laminates under compression

Composite Structures ◽

10.1016/j.compstruct.2014.12.022 ◽

2015 ◽

Vol 122 ◽

pp. 507-517 ◽

Cited By ~ 85

Author(s):

Z.C. Su ◽

T.E. Tay ◽

M. Ridha ◽

B.Y. Chen

Keyword(s):

Composite Laminates ◽

Progressive Damage ◽

Damage Modeling ◽

Open Hole

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Material orthotropy effects on progressive damage analysis of open-hole composite laminates under tension

Journal of Reinforced Plastics and Composites ◽

10.1177/0731684417710329 ◽

2017 ◽

Vol 36 (20) ◽

pp. 1473-1486 ◽

Cited By ~ 5

Author(s):

Song Zhou ◽

Yi Sun ◽

Boyang Chen ◽

Tong-Earn Tay

Keyword(s):

Composite Laminates ◽

Damage Mechanics ◽

Damage Model ◽

Continuum Damage Mechanics ◽

Tensile Loading ◽

Progressive Damage ◽

Cohesive Elements ◽

Damage Initiation ◽

Proposed Model ◽

Open Hole

The sizes effects on the strengths of open-hole fibre-reinforced composite laminates subjected to tensile loading (OHT) have been investigated widely. However, little attention has been paid to the influence of material orthotropy. This paper presents a progressive damage model for the model failure of notched laminates under tensile loading based on continuum damage mechanics and cohesive elements. The effects of orthotropy on the failure of notched laminates with seven different ply sequences are investigated by our proposed model. The prediction results adopting the Hoffman and Pinho failure criterions to determine matrix damage initiation are compared with the results of experiments. Our proposed models are able to predict the strong influence of orthotropy on strengths of open-hole laminate under tension, and model using Pinho criterion can predict the open-hole tension strength most accurately.

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Comparison of composite damage growth tools for fatigue behavior of notched composite laminates

Journal of Composite Materials ◽

10.1177/0021998317694948 ◽

2017 ◽

Vol 51 (15) ◽

pp. 2227-2249 ◽

Cited By ~ 5

Author(s):

SP Engelstad ◽

SB Clay

Keyword(s):

Composite Laminates ◽

Fatigue Behavior ◽

Fatigue Loading ◽

Lessons Learned ◽

Progressive Damage ◽

Damage Analysis ◽

Damage Growth ◽

Composite Damage ◽

Open Hole ◽

Air Force Research Laboratory

This paper provides overall comparisons of the fatigue results of an Air Force Research Laboratory exploration into the state of the art of existing technology in composite progressive damage analysis. This program performed blind and recalibration benchmarking exercises for nine different composite progressive damage analysis codes using unnotched and open-hole composite coupons under both static and fatigue loading. This paper summarizes the results of the fatigue portion of this program in which seven of the codes were evaluated. Comparisons are made herein for all seven participants’ predictions with the test data. Overall percent error data are presented, as well as a long list of observations and lessons learned during this year-long effort.

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