Stiffness Reduction in Composite Laminates due to Transverse Matrix Cracks

1995 ◽  
pp. 301-312 ◽  
Author(s):  
G. N. Praveen ◽  
J. N. Reddy
Keyword(s):  
Composite Laminates ◽  
Matrix Cracks ◽  
Stiffness Reduction

A Damage Model Containing Delamination in Composite Laminates

2006 ◽  
Vol 324-325 ◽  
pp. 43-46
Author(s):  
Yu Pu Ma ◽  
Xin Zhi Lin ◽  
Qing Fen Li ◽  
Zhen Li
Keyword(s):  
Composite Laminates ◽  
Damage Model ◽  
Laminated Composite ◽  
Shear Lag ◽  
Analysis Model ◽  
Transverse Cracks ◽  
Transverse Cracking ◽  
Stiffness Reduction ◽  
Laminated Composite Materials ◽  
Modulus Reduction

When stress is high, delaminate damage can be induced by transverse cracks. A complete parabolic shear-lag damage model containing delamination induced by transverse cracks is therefore proposed and applied to predict the stiffness reduction by transverse cracking in cross-ply laminated composite materials. The predictions of the complete parabolic shear-lag analysis model, the incomplete parabolic shear-lag analysis model, and the complete parabolic shear-lag damage model containing delamination proposed in this paper have been compared. Results show that the young’s modulus reduction values obtained by our analysis model are better agreement with the experimental ones than other models.

scholarly journals Stiffness Reduction of Composite Laminates under Combined Cyclic Stresses

2001 ◽  
Vol 10 (3) ◽  
pp. 096369350101000 ◽  
Author(s):  
T. P. Philippidis ◽  
A. P. Vassilopoulos
Keyword(s):  
Normal Stress ◽  
Composite Laminates ◽  
Failure Modes ◽  
Low Cycle Fatigue ◽  
Cyclic Stress ◽  
Fibre Direction ◽  
Cyclic Stresses ◽  
Stiffness Reduction ◽  
Stress States ◽  
Modulus Reduction

Stiffness reduction due to fatigue of a [0/(±45)2/0]T Glass/Polyester (GRP) laminate under combined cyclic stress is investigated in this experimental study. Stress states combining all three components of in-plane stress tensor are induced by uniaxially testing specimens cut off-axis at various angles from the principal material coordinate system. Modulus reduction is related to the various failure modes exhibited under different states of combined stress. It is verified that shear and transverse normal stress induce more severe stiffness degradation compared to stress states where normal stress in the main fibre direction is dominant. For every loading condition and stress state, it is observed in general that stiffness decrease is more pronounced under lower stress levels than these inducing low cycle fatigue.

Surface Replication: A Reliable Method of Detecting Matrix Cracks in Composite Laminates

1981 ◽  
Vol 3 (1) ◽  
pp. 35 ◽  
Author(s):  
TT Chiao ◽  
KL Reifsnider ◽  
GP Sendeckyj ◽  
RJ Morgan ◽  
PL Lien ◽  
...  
Keyword(s):  
Composite Laminates ◽  
Reliable Method ◽  
Matrix Cracks

A Bayesian framework for fatigue life prediction of composite laminates under co-existing matrix cracks and delamination

2018 ◽  
Vol 187 ◽  
pp. 58-70 ◽  
Author(s):  
Matteo Corbetta ◽  
Claudio Sbarufatti ◽  
Marco Giglio ◽  
Abhinav Saxena ◽  
Kai Goebel
Keyword(s):  
Fatigue Life ◽  
Composite Laminates ◽  
Life Prediction ◽  
Bayesian Framework ◽  
Fatigue Life Prediction ◽  
Matrix Cracks

A finite element analysis of impact damage in composite laminates

2012 ◽  
Vol 116 (1186) ◽  
pp. 1331-1347 ◽  
Author(s):  
Y. Shi ◽  
C. Soutis
Keyword(s):  
Finite Element ◽  
Composite Laminates ◽  
Damage Model ◽  
Low Velocity Impact ◽  
Shear Behaviour ◽  
Cohesive Elements ◽  
Fibre Direction ◽  
Element Analysis ◽  
Internal Damage ◽  
Matrix Cracks

AbstractIn this work, stress-based and fracture mechanics criteria were developed to predict initiation and evolution, respectively, of intra- and inter-laminar cracking developed in composite laminates subjected to low velocity impact. The Soutis shear stress-strain semi-empirical model was used to describe the nonlinear shear behaviour of the composite. The damage model was implemented in the finite element (FE) code (Abaqus/Explicit) by a user-defined material subroutine (VUMAT). Delamination (or inter-laminar cracking) was modelled using interface cohesive elements and the splitting and transverse matrix cracks that appeared within individual plies were also simulated by inserting cohesive elements between neighbouring elements parallel to the fibre direction in each single layer. A good agreement was obtained when compared the numerically predicted results to experimentally obtained curves of impact force and absorbed energy versus time. A non-destructive technique (NDT), penetrant enhanced X-ray radiography, was used to observe the various damage mechanisms induced by impact. It has been shown that the proposed damage model can successfully capture the internal damage pattern and the extent to which it was developed in these carbon fibre/epoxy composite laminates.

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