scholarly journals Computational Investigation of through the Width Delamination of a Composite Laminate using VCCT

2021 ◽  
Vol 9 (VI) ◽  
pp. 128-131
Author(s):  
K. S. Vishwanath
Keyword(s):  
Transverse Direction ◽  
Computational Prediction ◽  
Fiber Reinforced Polymer ◽  
Computational Investigation ◽  
Shell Elements ◽  
Delamination Growth ◽  
Weight Saving ◽  
Reinforced Polymer ◽  
Growth Initiation ◽  
Polymer Laminates

The fiber reinforced polymer laminates have found extensive applications because of its advantages over other materials in terms of strength, stiffness, stability, weight saving features, resistance to corrosion and erosion and many more. But due to poor transverse direction strength, a failure mechanism called delamination will occur in case of poor manufacturing or when tools are dropped which would make an impact. In this paper, VCCT is implemented at the interface between base and sub laminate to investigate for 20mm through the width buckling driven delamination growth. The computational prediction of delamination growth initiation is obtained by solving a T300/976 specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the required energy release rate at the edge of delamination geometry.

scholarly journals Computational Investigation of Square Embedded Delamination of a Composite Laminate using VCCT

2021 ◽  
Vol 9 (VI) ◽  
pp. 381-384
Author(s):  
K. S. Vishwanath
Keyword(s):  
Weight Ratio ◽  
Computational Prediction ◽  
Fiber Reinforced Polymer ◽  
Aviation Industry ◽  
Shell Elements ◽  
Delamination Growth ◽  
Reinforced Polymer ◽  
Interface Delamination ◽  
Growth Initiation ◽  
Polymer Laminates

The fiber reinforced polymer laminates are widely implemented in aviation industry due to its advantages and applications other materials in terms of strength to weight ratio, dsign features and many more. The strength of the interface compared to longitudinal and lateral directions of the plies are comparatively less and give rise too poor transverse direction strength. Hence a failure mechanism called delamination will occur in case when tools are dropped or due to poor manufacturing which would give rise to interface delamination. In this paper, VCCT is employed at the interface between base and sub laminate to investigate for a square shape delamination geometry of 20mm buckling driven delamination growth. The computational prediction of delamination growth initiation is obtained by solving a T300/976 specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the required energy release rate at the delamination geometry.

Computational Investigation of through the Width Delamination of a Composite Laminate using Surface based Cohesive Contact Behaviour

2021 ◽  
Vol 9 (VI) ◽  
pp. 743-747
Author(s):  
K. S. Vishwanath
Keyword(s):  
Composite Laminate ◽  
Weight Ratio ◽  
Computational Prediction ◽  
Shell Elements ◽  
Delamination Growth ◽  
Reinforced Polymer ◽  
Contact Behaviour ◽  
Out Of Plane ◽  
Growth Initiation ◽  
Polymer Laminates

The fiber reinforced polymer laminates have found extensive applications because of its advantages over other materials in terms of strength to weight ratio, manufacturing flexibility and so on. But in the transverse direction, strength is comparatively less so that a failure mechanism called delamination will occur in case of poor manufacturing or when tools are dropped. In this paper, Surface based Cohesive contact behavior is implemented at the interface between base and sub laminate to investigate for 60mm through the width buckling driven delamination growth. The computational prediction of delamination growth initiation is obtained by solving a HTA/6376C composite laminate specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the inplane loads versus out of plane displacements.

scholarly journals FEA of Circular Embedded Delamination with Variations in Temperature in a Composite Laminate using VCCT

2021 ◽  
Vol 9 (VI) ◽  
pp. 5058-5061
Author(s):  
K. S. Vishwanath
Keyword(s):  
Room Temperature ◽  
Transverse Direction ◽  
Weight Ratio ◽  
Computational Prediction ◽  
Aviation Industry ◽  
Shell Elements ◽  
Delamination Growth ◽  
Rate Versus ◽  
Interface Delamination ◽  
Growth Initiation

The FRP laminates are widely implemented in aviation industry due to its advantages and applications other materials in terms of strength to weight ratio, design features and many more. The strength of the interface compared to longitudinal and lateral directions of the plies are comparatively less and give rise too poor transverse direction strength. Hence a failure mechanism called delamination will occur in case when tools are dropped or due to poor manufacturing which would give rise to interface delamination. In this paper, VCCT is employed at the interface between base and sub laminate to investigate for a circular shape delamination geometry of 60mm buckling driven delamination growth with variations in temperature for -20C, room temperature, 523C, 773C and 1273C. The computational prediction of delamination growth initiation is obtained by solving a CFRP specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the required energy release rate versus inplane strains and inplane loads versus compressive strains.

Integrating Advanced Composite Materials Into the Chassis of a Sports Car

2004 ◽  
Author(s):  
Christopher J. Osborn ◽  
John M. Kennedy
Keyword(s):  
Element Model ◽  
Fiber Reinforced Polymer ◽  
Foam Core ◽  
Shell Elements ◽  
Advanced Composite ◽  
Weight Saving ◽  
Reinforced Polymer ◽  
Advanced Composite Materials ◽  
Total Vehicle ◽  
Isotropic Foam

This work evaluated the feasibility of replacing the current stamped-steel floor-pan bulkhead assembly (FBA) of a popular street car with one made of fiber reinforced polymer matrix composite material. To evaluate the feasibility, a finite element model was constructed which incorporated much of the midsection of the vehicle’s chassis. Each part of the chassis section assembly was modeled, meshed, and constrained such that the actual physical assembly relations were upheld. Shell elements were used to model the FBA, and brick and tetrahedron elements modeled the surrounding chassis. Six loading cases were considered: a torsion case, a bending case, and four seat load cases. The chosen composite consisted of an intermediate modulus fiber (AS4) and a typical thermal-set epoxy (3501-6). Four laminate stacking sequences were studied: two quasi-isotropic laminates, a zero-dominated laminate, and a symmetric laminate. A sandwich laminate case was also studied, which utilized quasi-isotropic face-sheets and an isotropic foam core. For comparison a steel case was also simulated. The overall result of the model showed that the sandwich case proved to be superior with the smallest displacements and stresses while reducing weight. The overall weight saving was an astonishing 3% of total vehicle weight which represents a significant savings for an automobile. Based on the results it was determined that the replacement of the steel FBA with a composite FBA is feasible.

scholarly journals Computational Investigation of Square Embedded Delamination of a Composite Laminate using Surface based Cohesive Contact Behavior

2021 ◽  
Vol 9 (VI) ◽  
pp. 909-913
Author(s):  
K. S. Vishwanath
Keyword(s):  
Composite Laminate ◽  
Impact Load ◽  
Weight Ratio ◽  
Computational Prediction ◽  
Shell Elements ◽  
Contact Behavior ◽  
Delamination Growth ◽  
Interface Delamination ◽  
Out Of Plane ◽  
Growth Initiation

The fiber reinforced polymer laminates have found extensive applications because of its advantages over other materials in terms of thrust to weight ratio, strength to weight ratio, manufacturing benefits such as tailoring, resistance to erosion and corrosion and so on. In the transverse direction, strength, stiffness and stability are comparatively less so that a failure mechanism called interface delamination comes into picture due to poor manufacturing or when tools are dropped that would create an impact load. In this paper, Surface based Cohesive contact behavior is implemented at the interface between base and sub laminate to investigate for 60mm square embedded buckling driven delamination growth. The computational prediction of delamination growth initiation is obtained by solving a HTA/6376C composite laminate specimen for geometric non linearity using SC8R continuum shell elements of Abaqus CAE and by plotting the inplane loads versus out of plane displacements.

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