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.

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 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.

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.

Bio-inspired composite laminate design with improved out-of-plane strength and ductility

2021 ◽  
Vol 144 ◽  
pp. 106362
Author(s):  
A. Melaibari ◽  
A. Wagih ◽  
Muhammad Basha ◽  
A.M. Kabeel ◽  
G. Lubineau ◽  
...  
Keyword(s):  
Composite Laminate ◽  
Out Of Plane ◽  
Laminate Design ◽  
Composite Laminate Design ◽  
Strength And Ductility

The Effect of Stitching on Compression Behavior of Stiffened Composite Panels

2001 ◽  
Author(s):  
Sung S. Suh ◽  
H. Thomas Hahn ◽  
Nanlin Han ◽  
Jenn-Ming Yang
Keyword(s):  
Beneficial Effect ◽  
Compression Behavior ◽  
Stiffened Panels ◽  
Shell Elements ◽  
Stitch Density ◽  
Stiffened Composite Panels ◽  
Out Of Plane ◽  
Post Buckling ◽  
Post Impact ◽  
Good Agreement

Abstract Failure of stiffened panels under compression is preceded by buckling of their skin and hence is affected by the presence of out-of-plane stresses. One of the promising methods of preventing premature delamination is stitching. The present paper discusses the effect of such stitching on compression behavior of blade-stiffened panels that were fabricated from plain weave AS4/3501-6 through resin film infusion process. Kevlar 29 yarn was used at a stitch density of 9.92 stitches per cm2. Some of the panels were damaged by drop-weight impact before compression testing. For comparison purposes unstitched panels with the same materials and dimensions were also tested under the same loading conditions. Stitching resulted in a 10% improvement in strength in the absence of any intentional damage. The beneficial effect of stitching was most obvious when the panels were impacted on a flange: a 50% improvement was observed in post-impact strength. However, stitching could not prevent stiffener from failure when impacted directly. Thus stitching had no beneficial effect when impact occurred on a stiffener. A buckling and post-buckling analysis was carried out using 3-D shell elements on the Abaqus. Predictions were in fairly good agreement with the experimental data.

scholarly journals Influence of Gradual Damage on the Structural Dynamic Behaviour of Composite Rotors: Experimental Investigations

Materials ◽  
2018 ◽  
Vol 11 (12) ◽  
pp. 2421 ◽  
Author(s):  
Angelos Filippatos ◽  
Maik Gude
Keyword(s):  
Mechanical Properties ◽  
Composite Structures ◽  
Dynamic Behaviour ◽  
Experimental Investigations ◽  
Catastrophic Failure ◽  
Structural Dynamic ◽  
Delamination Growth ◽  
Reinforced Composite ◽  
Out Of Plane ◽  
Effective Mechanical Properties

Fibre-reinforced composite structures subjected to complex loads exhibit gradual damage behaviour with the degradation of the effective mechanical properties and changes in their structural dynamic behaviour. Damage manifests itself as a spatial increase in inter-fibre failure and delamination growth, resulting in local changes in stiffness. These changes affect not only the residual strength but, more importantly, the structural dynamic behaviour. In the case of composite rotors, this can lead to catastrophic failure if an eigenfrequency coincides with the rotational speed. The description and analysis of the gradual damage behaviour of composite rotors, therefore, provide the fundamentals for a better understanding of unpredicted structural phenomena. The gradual damage behaviour of the example composite rotors and the resulting damage-dependent dynamic behaviour were experimentally investigated under propagating damage caused by a combination of out-of-plane and in-plane loads. A novel observation is the finding that a monotonic increase in damage results in a non-monotonic frequency shift of a significant number of eigenfrequencies.

scholarly journals The effects of voids in quasi-static indentation of resin-infused reinforced polymers

2019 ◽  
Vol 53 (28-30) ◽  
pp. 4399-4410
Author(s):  
SM Sisodia ◽  
DJ Bull ◽  
AR George ◽  
EK Gamstedt ◽  
MN Mavrogordato ◽  
...  
Keyword(s):  
Static Loading ◽  
Tomographic Imaging ◽  
Transverse Cracks ◽  
Reinforced Polymers ◽  
Delamination Growth ◽  
Out Of Plane ◽  
Static Indentation ◽  
Carbon Fibre Reinforced Polymers ◽  
Air Pockets ◽  
Delamination Cracks

The focus of this study is the influence of voids on the damage behaviour in quasi-static loading of resin-infused carbon fibre-reinforced polymers. Experimental results are presented for quasi-static loading in combination with high-resolution tomographic imaging and statistical analysis (homology of pores or voids and induced cracks). Three distinct mechanisms were observed to control delamination growth in the presence of sharp and blunt voids. Delamination cracks interact with the supporting yarns, especially in combination with air pockets trapped in the resin in the form of long, sharp voids. This resulted in crack growth that coalesces with delamination cracks from neighbouring yarn-voids during increased out-of-plane load–displacement, with almost no presence of intralaminar transverse cracks. This highlights the benefits and drawbacks of the supporting yarn during out-of-plane loading.

Evaluation of Interfacial Fatigue Strength of Hard Coating by Using Repeated Laser Shock Adhesion Test

2019 ◽  
Author(s):  
Kohei Kanamori ◽  
Yusaku Saito ◽  
Akio Yonezu
Keyword(s):  
Laser Irradiation ◽  
Adhesion Strength ◽  
Laser Shock ◽  
Adhesion Test ◽  
Heat Treated ◽  
Interface Delamination ◽  
Out Of Plane ◽  
Plane Displacement ◽  
Strength And Durability ◽  
Pulsed Laser Irradiation

Abstract This study aims to evaluate the adhesion strength and durability of hard coatings in a non-contact manner by using Laser Shock Adhesion Test (LaSAT). Both heat-treated and as-plated (non-heat-treated) Ni-P coatings deposited on carbon steel substrate by electroless plating method were prepared as specimens for this study. LaSAT uses strong elastic waves induced by pulsed laser irradiation in order to apply tensile stress to the coating/substrate interface so that interface delamination occurs. The out-of-plane displacement is also measured simultaneously by using a laser ultrasonic interferometer, and the interface delamination is detected by the change of the out-of-plane displacement waveform. Furthermore, computation of the elastic wave propagation using Finite Difference Time Domain (FDTD) is carried out to estimate the interfacial tensile stress. In addition, the adhesion durability is investigated by repetitive pulsed laser irradiation, and the relationship between the adhesion strength and the number of laser irradiation cycles until delamination was obtained. Finally, we discussed the effects of heat treatment on the adhesion strength and durability. This method of LaSAT is a quick measurement for the adhesion durability, and then it may shed some light on quality control of surface coating.

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