Relation of Through-Thickness Ductility to Inclusion Prevalence, Matrix Toughness, and Matrix Strength

2009 ◽  
pp. 113-113-8
Author(s):  
DC Ludwigson
Keyword(s):  
Matrix Strength ◽  
Matrix Toughness

scholarly journals The participation ratios of cement matrix and latex network in latex cement co-matrix strength

2014 ◽  
Vol 53 (2) ◽  
pp. 309-317 ◽  
Author(s):  
Ahmed M. Diab ◽  
Hafez E. Elyamany ◽  
Ali Hassan Ali
Keyword(s):  
Cement Matrix ◽  
Matrix Strength

Bio-Inspired Laminates of Different Material Systems

2019 ◽  
Vol 87 (3) ◽  
Author(s):  
J. L. Liu ◽  
H. P. Lee ◽  
K. S. Lai ◽  
V. B. C. Tan
Keyword(s):  
Failure Mechanism ◽  
Peak Load ◽  
Material System ◽  
Fiber Reinforced ◽  
Fiber Damage ◽  
Out Of Plane ◽  
Matrix Toughness ◽  
Pitch Ratio ◽  
The Common ◽  
Fiber Reinforced Laminates

Abstract Helicoidal laminates mimicking the laminar structure of the exoskeleton of crustaceans have been reported to resist higher out-of-plane loads than the common cross-ply and quasi-isotropic fiber-reinforced laminates. Some have reported that smaller inter-ply angle improves strength of helicoidal laminates but others have reported the opposite. A few important material parameters that dictate the failure mechanism of helicoidal laminates have recently been proposed based on proof-of-concept carbon fiber-reinforced laminates, which is not the best material system to benefit from a helicoidal configuration. This study investigates the out-of-plane loading performance of helicoidal laminates with various inter-ply angles, ply thicknesses, and materials. Result shows that the failure mechanism is dictated by the competition between spiraling matrix split and delamination followed by fiber breakage regardless of the laminate material system. Spiraling matrix split resistance decreases as pitch (ratio of inter-ply angle to ply thickness) and matrix toughness decreases. This study provides guidelines for the optimization of helicoidal laminates. Coexistence of spiraling matrix split and fiber damage is often seen on the failed laminate with the highest peak load. The optimal inter-ply angle provides the optimal spiraling matrix split resistance; so, neither spiraling matrix split nor fiber/delamination damage becomes dominant. Since resistance to spiraling matrix split decreases as pitch or matrix toughness decreases, the optimal inter-ply angle will increase for laminates with weaker matrix or thicker plies and vice versa.

scholarly journals On the extent of fracture toughness transfer from 1D/2D nanomodified epoxy matrices to glass fibre composites

2020 ◽  
Vol 55 (11) ◽  
pp. 4717-4733 ◽  
Author(s):  
Nadiim Domun ◽  
Keith R. Paton ◽  
Bamber R. K. Blackman ◽  
Cihan Kaboglu ◽  
Samireh Vahid ◽  
...  
Keyword(s):  
Fracture Toughness ◽  
Boron Nitride ◽  
Glass Fibre ◽  
Mode I ◽  
Interlaminar Fracture Toughness ◽  
Gfrp Composites ◽  
Interlaminar Fracture ◽  
Gfrp Composite ◽  
The Matrix ◽  
Matrix Toughness

AbstractIn this study, the effects of adding nanofillers to an epoxy resin (EP) used as a matrix in glass fibre-reinforced plastic (GFRP) composites have been investigated. Both 1D and 2D nanofillers were used, specifically (1) carbon nanotubes (CNTs), (2) few-layer graphene nanoplatelets (GNPs), as well as hybrid combinations of (3) CNTs and boron nitride nanosheets, and (4) GNPs and boron nitride nanotubes (BNNTs). Tensile tests have shown improvements in the transverse stiffness normal to the fibre direction of up to about 25% for the GFRPs using the ‘EP + CNT’ and the ‘EP + BNNT + GNP’ matrices, compared to the composites with the unmodified epoxy (‘EP’). Mode I and mode II fracture toughness tests were conducted using double cantilever beam (DCB) and end-notched flexure (ENF) tests, respectively. In the quasi-static mode I tests, the values of the initiation interlaminar fracture toughness, $$ G_{\text{IC}}^{\text{C}} $$GICC, of the GFRP composites showed that the transfer of matrix toughness to the corresponding GFRP composite is greatest for the GFRP composite with the GNPs in the matrix. Here, a coefficient of toughness transfer (CTT), defined as the ratio of mode I initiation interlaminar toughness for the composite to the bulk polymer matrix toughness, of 0.68 was recorded. The highest absolute values of the mode I interlaminar fracture toughness at crack initiation were achieved for the GFRP composites with the epoxy matrix modified with the hybrid combinations of nanofillers. The highest value of the CTT during steady-state crack propagation was ~ 2 for all the different types of GFRPs. Fractographic analysis of the composite surfaces from the DCB and ENF specimens showed that failure was by a combination of cohesive (through the matrix) and interfacial (along the fibre/matrix interface) modes, depending on the type of nanofillers used.

Rotary Application of Low Matrix Strength Impregnated and TSP Cutter Bits to Unayzah Sandstone Drilling

2002 ◽  
Author(s):  
M. A. Simpson ◽  
A.H. Roed ◽  
H.A. Al-Shammari ◽  
Dirk Hoekstra
Keyword(s):  
Matrix Strength

Effect of Solution Treatment and Artificial Aging on the Work Hardening Characteristics of D357 Alloy Castings

2006 ◽  
Vol 519-521 ◽  
pp. 1865-1870 ◽  
Author(s):  
Murat Tiryakioğlu
Keyword(s):  
Work Hardening ◽  
Artificial Aging ◽  
Treatment Time ◽  
Solution Treatment ◽  
Particle Morphology ◽  
Model Parameters ◽  
Matrix Strength ◽  
Alloy Castings ◽  
Work Hardening Model ◽  
D357 Alloy

The effects of solution treatment time and artificial aging on the work hardening characteristics on Al-7%Si-0.6%Mg (D357) alloy castings were investigated. Four different solution treatment times at 540°C (1, 4, 16 and 64 hours) and six different artificial aging times at 160°C (0, 2.5, 5, 10, 20 and 40 hours) were used. Work hardening characteristics were investigated by Kocks-Mecking plots for each specimen. The effects of Si particle morphology (solution treatment) and matrix strength (aging) on Kocks-Mecking (Stage III) work hardening model parameters are discussed in the paper.

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