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.

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 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.

HYDRAULIC BULGE TESTING TO COMPARE FORMABILITY OF CONTINUOUS AND STRETCH BROKEN CARBON FIBER PREPREG LAMINATES

2021 ◽  
Author(s):  
YONI SHCHEMELININ ◽  
JARED W. NELSON ◽  
ROBERTA AMENDOLA
Keyword(s):  
Carbon Fiber ◽  
High Strength ◽  
Biaxial Stress ◽  
Fiber Reinforced Polymer ◽  
Aviation Industry ◽  
Strain Behavior ◽  
Reinforced Polymer ◽  
Fiber Reinforced Polymer Composites ◽  
Bulge Testing ◽  
Hydraulic Bulge

The use of carbon fiber reinforced polymer composites has increased with the increased need for high-strength, low-density materials, particularly in the aviation industry. Stretch broken carbon fiber (SBCF) is a form of carbon fiber created by the randomized breaking of aligned fibers in a tow at inherent flaw points, resulting in a material constituted of collimated fiber fragments longer than chopped fibers. While continuous carbon fibers possess desirable material properties, the limited formability prevents their wider adoption. SBCF composites exhibit pseudo-plastic deformation that can potentially enable the use of traditional metal forming techniques like stamping and press forming well established in mass production applications. To investigate the formability of SBCF composites prepared with either continuous or stretch broken Hexcel IM-7 12K fiber, impregnated with Huntsman RDM 2019-053 resin, hydraulic bulge testing was performed to explore the strain behavior under biaxial stress conditions at elevated temperature under atmospheric pressure. Initial results show better formability of SBCF compared to continuous fiber, characterized by the axisymmetric response to the applied stress.

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