Open hole and filled hole progressive damage and failure analysis of composite laminates with a countersunk hole

2018 ◽  
Vol 203 ◽  
pp. 523-538 ◽  
Author(s):  
Ashith P.K. Joseph ◽  
Paul Davidson ◽  
Anthony M. Waas
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Progressive Damage ◽  
Damage And Failure ◽  
Open Hole

scholarly journals Progressive Failure Analysis in Open-Hole Tensile Composite Laminates of Airplane Stringers Based on Tests and Simulations

2020 ◽  
Vol 11 (1) ◽  
pp. 185
Author(s):  
Jian Shi ◽  
Mingbo Tong ◽  
Chuwei Zhou ◽  
Congjie Ye ◽  
Xindong Wang
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Progressive Failure ◽  
Tensile Load ◽  
Fiber Failure ◽  
Stress Criterion ◽  
Progressive Failure Analysis ◽  
Analysis Technique ◽  
Open Hole ◽  
Failure Types

The failure types and ultimate loads for eight carbon-epoxy laminate specimens with a central circular hole subjected to tensile load were tested experimentally and simulated using two different progressive failure analysis (PFA) methodologies. The first model used a lamina level modeling based on the Hashin criterion and the Camanho stiffness degradation theory to predict the damage of the fiber and matrix. The second model implemented a micromechanical analysis technique coined the generalized method of cells (GMC), where the 3D Tsai–Hill failure criterion was used to govern matrix failure, and the fiber failure was dictated by the maximum stress criterion. The progressive failure methodology was implemented using the UMAT subroutine within the ABAQUS/implicit solver. Results of load versus displacement and failure types from the two different models were compared against experimental data for the open hole laminates subjected to tensile displacement load. The results obtained from the numerical simulation and experiments showed good agreement. Failure paths and accurate damage contours for the tested specimens were also predicted.

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

2016 ◽  
Vol 51 (10) ◽  
pp. 1493-1524 ◽  
Author(s):  
Stephen P Engelstad ◽  
Stephen B Clay
Keyword(s):  
Air Force ◽  
Composite Laminates ◽  
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 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.

scholarly journals Open holes in composite laminates with finite dimensions: structural assessment by analytical methods

2022 ◽  
Author(s):  
M. Nguyen-Hoang ◽  
W. Becker
Keyword(s):  
Failure Analysis ◽  
Analytical Methods ◽  
Composite Laminates ◽  
Design Feature ◽  
Potential Method ◽  
Finite Width ◽  
Efficient Computation ◽  
Stress Concentrations ◽  
Open Hole ◽  
Circular Holes

AbstractOpen circular holes are an important design feature, for instance in bolted joint connections. However, stress concentrations arise whose magnitude depends on the material anisotropy and on the defect size relative to the outer finite plate dimensions. To design both safe and light-weight optimal structures, precise means for the assessment are crucial. These can be based on analytical methods providing efficient computation. For this purpose, the focus of the present paper is to provide a comprehensive stress and failure analysis framework based on analytical methods, which is also suitable for use in industry contexts. The stress field for the orthotropic finite-width open-hole problem under uniform tension is derived using the complex potential method. The results are eventually validated against Finite-Element analyses revealing excellent agreement. Then, a failure analysis to predict brittle crack initiation is conducted by means of the Theory of Critical Distances and Finite Fracture Mechanics. These failure concepts of different modelling complexity are compared to each other and validated against experimental data. The size effect is captured, and in this context, the influence of finite width on the effective failure load reduction is investigated.

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

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.

Progressive damage modeling of open-hole composite laminates under compression

2015 ◽  
Vol 122 ◽  
pp. 507-517 ◽  
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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