DAMAGE ACCUMULATION IN FIBRE-REINFORCED COMPOSITE LAMINATES

1988 ◽  
Vol 12 (3) ◽  
pp. 133-137 ◽  
Author(s):  
P. LABOSSIERE ◽  
K.W. NEALE ◽  
K. NEGLO
Keyword(s):  
Finite Element ◽  
Circular Hole ◽  
Composite Laminates ◽  
Damage Accumulation ◽  
Progressive Failure ◽  
Failure Criteria ◽  
Progressive Damage ◽  
Fibre Breakage ◽  
Reinforced Composite ◽  
Finite Element Calculations

Finite element calculations are carried out to simulate progressive damage in fibre-reinforced composite laminates. Each element is taken to be linearly elastic up to failure, which is assumed to be caused by either fibre breakage, matrix rupture or delamination. These damage modes are modelled by incorporating Lee’s [2] failure criteria in the analysis. Behaviour subsequent to each type of damage is modelled by suitably modifying the element properties in the failure zones. Numerical results are present for the progressive failure of a four-layer symmetric cross-ply laminate with a circular hole.

Analysis and Experiment of Compressive Residual Strength of Composite Laminates with Holes

2014 ◽  
Vol 936 ◽  
pp. 43-52
Author(s):  
Xiang Hong Kong ◽  
Zhi Jin Wang
Keyword(s):  
Finite Element Analysis ◽  
Finite Element ◽  
Residual Strength ◽  
Composite Laminates ◽  
Failure Criteria ◽  
Fortran Program ◽  
Progressive Damage ◽  
Element Analysis ◽  
Program Segment ◽  
User Subroutine

Experiment and Finite element analysis were used to study the strengths of composite laminates with and without holes. Finite element progressive damage analysis with Tsai-Wu criteria was applied to calculate the compressive residual strength of composite laminate. Abaqus and its user subroutine USDFLD were used for the finite element analysis. Tsai-Wu criteria as the failure criteria was realized in USDFLD as a Fortran program segment, and the stiffness degradation for the damaged elements was also realized by USDFLD. Analytic results gotten by progressive damage method were very close to the experimental results.

Finite Element Analysis of the Tensile Properties of Composite Laminates with Open Holes

2014 ◽  
Vol 1004-1005 ◽  
pp. 451-454
Author(s):  
Xiao Qiang Wang ◽  
Wei Tao Zhao ◽  
Bo Fang ◽  
Shao Wei Lu ◽  
Ye Wei Zhang
Keyword(s):  
Finite Element ◽  
Composite Laminates ◽  
Failure Modes ◽  
Progressive Failure ◽  
Element Model ◽  
Element Analysis ◽  
Fiber Reinforced Composite ◽  
Thin Walled Structures ◽  
Reinforced Composite ◽  
Load Carrying

For different technical reasons, cutouts such as holes in thin-walled structures are inevitable and are of significant technical relevance. Unfortunately open holes usually lead to an undesired stress concentration at the hole vicinity and a reduced load carrying ability of the structure. Therefore the mechanical properties of fiber-reinforced composite laminates with open holes are studied in the paper. The influences of the size and shape of the holes are investigated. A progressive failure finite element model is developed with software ABAQUS. Different failure modes of the composite laminates with various holes are simulated under the Hashin failure criterion. The computational results show that the hole/s have a significant effects on composite laminates properties, and the conclusion can be provided as a good reference for the design of the composite laminates with hole/s.

Bearing strength and failure analysis on the interference-fit double shear-lap pin-loaded composite

2016 ◽  
Vol 27 (2) ◽  
pp. 179-200 ◽  
Author(s):  
Peng Zou ◽  
Kaifu Zhang ◽  
Yuan Li ◽  
Ping Liu ◽  
Huanhuan Xie
Keyword(s):  
Composite Laminates ◽  
Composite Structures ◽  
Progressive Failure ◽  
Tensile Load ◽  
Failure Criteria ◽  
Displacement Curve ◽  
Progressive Damage ◽  
Interference Fit ◽  
Bearing Strength ◽  
Load Displacement

Interference-fit technology has a wide effect on the strength and fatigue life of composite structures. The damage around the hole may accelerate the structure failure. In this paper, a progressive damage model is developed to predict the response of interference-fit pin-loaded composite laminates during the installation and loading process with the ABAQUS subroutine user-define-field (USDFLD). The model takes contact at the pin–hole interface, the nonlinear shear stress–strain relationship and the property progressive damage into consideration. The loading procedure is separated into two parts: (a) installing the Hi-Lok pin. (b) Applying the tensile load. To predict progressive failure, the mixed failure criteria combining Hashin criteria and the maximum stress failure criteria, and the Camanho and Matthews degradation rules are conducted. The insertion load, stress and damage around the hole, load–displacement curve, and the bearing strength are predicted. A series of experiments have also been performed and the rationality of the model is testified. The parametric study is also made to analyze the effect of fit conditions on insertion load, damage, and load–displacement curve.

scholarly journals Simulating Progressive Damage of Notched Composite Laminates with Various Lamination Schemes

2017 ◽  
Vol 22 (2) ◽  
pp. 333-347 ◽  
Author(s):  
B. Mandal ◽  
A. Chakrabarti
Keyword(s):  
Finite Element ◽  
Composite Laminates ◽  
Constitutive Relations ◽  
Damage Model ◽  
Three Dimensional ◽  
Failure Criteria ◽  
Progressive Damage ◽  
Damage Models ◽  
Matrix Shear ◽  
Three Dimensional Finite Element

AbstractA three dimensional finite element based progressive damage model has been developed for the failure analysis of notched composite laminates. The material constitutive relations and the progressive damage algorithms are implemented into finite element code ABAQUS using user-defined subroutine UMAT. The existing failure criteria for the composite laminates are modified by including the failure criteria for fiber/matrix shear damage and delamination effects. The proposed numerical model is quite efficient and simple compared to other progressive damage models available in the literature. The efficiency of the present constitutive model and the computational scheme is verified by comparing the simulated results with the results available in the literature. A parametric study has been carried out to investigate the effect of change in lamination scheme on the failure behaviour of notched composite laminates.

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