scholarly journals Progressive failure analysis for impact damage and compressive strength of composite laminates

2017 ◽  
Vol 4 (5) ◽  
pp. 16-00710-16-00710 ◽  
Author(s):  
Yukihiro SATO ◽  
Kazuhiro MIURA ◽  
Masahiro KASHIWAGI ◽  
Masayoshi SUHARA ◽  
Yoshinori NONAKA ◽  
...  
Keyword(s):  
Compressive Strength ◽  
Failure Analysis ◽  
Composite Laminates ◽  
Impact Damage ◽  
Progressive Failure ◽  
Progressive Failure Analysis

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.

scholarly journals Progressive Failure Analysis of Laminates with Embedded Wrinkle Defects Based on an Elastoplastic Damage Model

Materials ◽  
2020 ◽  
Vol 13 (10) ◽  
pp. 2422
Author(s):  
Zhi Hua Ning ◽  
Guan Liang Huo ◽  
Ren Huai Liu ◽  
Wei Lin Wu ◽  
Jia Ming Xie
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
High Efficiency ◽  
Progressive Failure ◽  
Golden Section ◽  
Damage Model ◽  
Failure Behavior ◽  
Progressive Failure Analysis ◽  
Out Of Plane ◽  
Elastoplastic Damage

Out-of-plane wrinkling has a significant influence on the mechanical performance of composite laminates. Numerical simulations were conducted to investigate the progressive failure behavior of fiber-reinforced composite laminates with out-of-plane wrinkle defects subjected to axial compression. To describe the material degradation, a three-dimensional elastoplastic damage model with four damage modes (i.e., fiber tensile failure, matrix failure, fiber kinking/splitting, and delamination) was developed based on the LaRC05 criterion. To improve the computational efficiency in searching for the fracture angle in the matrix failure analysis, a high-efficiency and robust modified algorithm that combines the golden section search method with an inverse interpolation based on an existing study is proposed. The elastoplastic damage model was implemented in the finite-element code Abaqus using a user-defined material subroutine in Abaqus/Explicit. The model was applied to the progressive failure analysis of IM7/8552 composite laminates with out-of-plane wrinkles subjected to axial compressive loading. The numerical results showed that the compressive strength prediction obtained by the elastoplastic damage model is more accurate than that derived with an elastic damage model. The present model can describe the nonlinearity of the laminate during the damage evolution and determine the correct damage locations, which are in good agreement with experimental observations. Furthermore, it was discovered that the plasticity effects should not be neglected in laminates with low wrinkle levels.

Failure Analysis of Laminated Composites under in-Plane Compressive Loading

2012 ◽  
Vol 476-478 ◽  
pp. 583-586
Author(s):  
Yin Huan Yang
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Parametric Design ◽  
Laminated Composites ◽  
Progressive Failure ◽  
Compressive Loading ◽  
Laminated Composite ◽  
Progressive Failure Analysis ◽  
Ultimate Failure

Failure prediction of laminated composites is performed by progressive failure analysis method. A modified form of Hashin’s failure criterion by Shokrieh is used to detect the failure, where a sudden degradation model is proposed to reduce engineering material constants. The numerical analysis of composite laminates is implemented in ANSYS Parametric Design Language (APDL) with commercial finite element codes ANSYS. The method can predict the initiation and propagation of local damage and response of laminated composite structures from initial loading and ultimate failure. The model has been validated by comparing numerical results with existing experimental results. And then failure analysis specimen fabricated from M40J/Ag80 and investigation on influence of stacking sequences and fiber orientations under in-plane compressive loading have been performed by the proposed model.

Progressive failure analysis for the interaction of interlaminar and intralaminar failure modes in composite structures with an initial delamination

2013 ◽  
Vol 117 (1187) ◽  
pp. 71-85 ◽  
Author(s):  
W. Ji ◽  
A. M. Waas
Keyword(s):  
Failure Analysis ◽  
Composite Laminates ◽  
Composite Structures ◽  
Failure Modes ◽  
Progressive Failure ◽  
Laminated Composite ◽  
Composite Panel ◽  
Analysis Tool ◽  
Plane Failure ◽  
Progressive Failure Analysis

AbstractThis paper is concerned with the development of a failure initiation and progressive failure analysis (PFA) method for advanced composite structures. The present PFA model is capable of predicting interactive out-of-plane and in-plane failure modes observed in fiber reinforced composite laminates including interlaminar behavior and matrix microdamage at the mesoscale. A probability analysis tool is coupled with the PFA to account for uncertainty in modelling parameters caused by material variability and manufacturing inconsistencies. The progressive damage response of a laminated composite panel with an initial delamination is studied and used to demonstrate the PFA modelling framework that is presented here.

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