Optimization of pitch distance of kevlar thread stitching in chopped GFRP composite laminates

2020 ◽  
Author(s):  
R. Karthikeyan ◽  
M. K. Karthik ◽  
N. Elumalai ◽  
C. Suresh Kumar
Keyword(s):  
Composite Laminates ◽  
Gfrp Composite ◽  
Pitch Distance

scholarly journals The Effect of High Glass Fiber Content and Reinforcement Combination on Pulse-Echo Ultrasonic Measurement of Composite Ship Structures

2021 ◽  
Vol 9 (4) ◽  
pp. 379
Author(s):  
Sang-Gyu Lee ◽  
Daekyun Oh ◽  
Jong Hun Woo
Keyword(s):  
Glass Fiber ◽  
Composite Laminates ◽  
Composite Structures ◽  
Ultrasonic Waves ◽  
Ship Structures ◽  
Glass Fiber Reinforced ◽  
Gfrp Composite ◽  
Chopped Strand Mat ◽  
Composite Ship ◽  
Pulse Echo

Ship structures made of glass fiber-reinforced polymer (GFRP) composite laminates are considerably thicker than aircraft and automobile structures and more likely to contain voids. The production characteristics of such composite laminates were investigated in this study by ultrasonic nondestructive evaluation (NDE). The laminate samples were produced from E-glass chopped strand mat (CSM) and woven roving (WR) fabrics with different glass fiber contents of 30–70%. Approximately 300 pulse-echo ultrasonic A-scans were performed on each sample. The laminate samples produced from only CSM tended to contain more voids compared with those produced from a combination of CSM and WR, resulting in the relative density of the former being lower than the design value, particularly for high glass fiber contents of ≥50%. The velocity of the ultrasonic waves through the CSM-only laminates was also lower for higher glass fiber contents, whereas it steadily increased for combined CSM–WR laminates. Burn-off tests of the laminates further revealed that the fabric configuration of the combined CSM–WR laminates was of higher quality, prevented the formation of voids, and improved inter-layer bonding. These findings indicate that combined CSM–WR laminates should be used to achieve more accurate ultrasonic NDE of GFRP composite structures.

scholarly journals Creep effects on tension-tension fatigue behavior of angle-ply GFRP composite laminates

2019 ◽  
Vol 123 ◽  
pp. 144-156 ◽  
Author(s):  
A. Vahid Movahedi-Rad ◽  
Thomas Keller ◽  
Anastasios P. Vassilopoulos
Keyword(s):  
Composite Laminates ◽  
Fatigue Behavior ◽  
Gfrp Composite

Performances of different mill cutters in machining of GFRP Composite Laminates

2017 ◽  
Vol 4 (2) ◽  
pp. 2800-2805
Author(s):  
I.S.N.V.R. Prashanth ◽  
D.V. Ravi Shankar ◽  
M. Manjoor Hussain ◽  
D. Ramana Reddy
Keyword(s):  
Composite Laminates ◽  
Gfrp Composite

scholarly journals Constitutive Modelling for Anisotropic Damage in Woven E-Glass Reinforcements

2017 ◽  
Vol 11 (1) ◽  
pp. 9-21
Author(s):  
Ping Yang ◽  
Ying Tong
Keyword(s):  
Composite Laminates ◽  
Damage Model ◽  
Fixed Time ◽  
Constitutive Modelling ◽  
Anisotropic Damage ◽  
Material Damage ◽  
Lower Velocity ◽  
Damage Area ◽  
Gfrp Composite ◽  
Damage Process

It is easy for composite laminates to be damaged by relative lower velocity impact which could give rise to internal delamination that will strongly weaken the compressive strength of laminates. In order to predict the occurrence of matrix failure, the elastic-brittle behaviors of fiber-reinforced composites were modeled constitutively by an anisotropic damage model. The dynamic tensile testing was performed at a constant velocity of 2 mm/min until the sample broke to achieve the mechanical parameters of E-glass reinforcements. The elastic constitutive equation and the constitutive damage model were obtained on basis of the fundamental theory of mechanics about the orthotropic constitutive of reinforcements. The methodology for this constitutive model which is developed by Hashin considered both the effect of fiber and matrix failure. Then, the developed constitutive equations were incorporated into the FE (finite element) codes, ABAQUS, through the user subroutine module to simulate the process of projectile impacting GFRP composite laminates. The results show that the material deformation reaches a maximum at 24 μs, then occurs rebound with the increase of the time. The stress of reinforcements traverse section linearly increases outward from 0 MPa to 509.8 MPa. Material damage area increases with the prolonging of time, and for a fixed time, material damage gradually increases from the edges to the center and reaches a constant value of 1, which means the rupture of the damage process.

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