A micromechanics based predictive model for damage initiation in compressively loaded angle ply composite laminates

2000 ◽  
Author(s):  
Junghyun Ahn ◽  
Anthony Waas
Keyword(s):  
Predictive Model ◽  
Composite Laminates ◽  
Damage Initiation

Micromechanics-based predictive model for compressively loaded angle-ply composite laminates

AIAA Journal ◽  
2000 ◽  
Vol 38 ◽  
pp. 2299-2304
Author(s):  
Jung Hyun Ahn ◽  
Anthony M. Waas
Keyword(s):  
Predictive Model ◽  
Composite Laminates

Machine Learning Based Predictive Model for AFP-Based Unidirectional Composite Laminates

2020 ◽  
Vol 16 (4) ◽  
pp. 2315-2324 ◽  
Author(s):  
Chathura Wanigasekara ◽  
Ebrahim Oromiehie ◽  
Akshya Swain ◽  
B. Gangadhara Prusty ◽  
Sing Kiong Nguang
Keyword(s):  
Machine Learning ◽  
Predictive Model ◽  
Composite Laminates ◽  
Unidirectional Composite

Damage Characterization in Glass/Epoxy Composite Laminates under Normal and Oblique Planes of Cyclic Indentation Loading with AE Monitoring

2021 ◽  
Vol 79 (1) ◽  
pp. 61-77
Author(s):  
A Jayababu ◽  
V Arumugam ◽  
B Rajesh ◽  
C Suresh Kumar
Keyword(s):  
Compressive Strength ◽  
Acoustic Emission ◽  
Cyclic Loading ◽  
Composite Laminates ◽  
Epoxy Composite ◽  
Damage Resistance ◽  
Damage Initiation ◽  
Residual Compressive Strength ◽  
Cyclic Indentation ◽  
Indentation Damage

This work focuses on the experimental investigation of indentation damage resistance in different stacking sequences of glass/epoxy composite laminates under cyclic loading on normal (0°) and oblique (20°) planes. The stacking sequence, such as unidirectional [0]12, angle ply [±45]6S, and cross ply [0/90]6S, were subjected to cyclic indentation loading and monitoring by acoustic emission testing (AE). The laminates were loaded at the center using a hemispherical steel indenter with a 12.7 mm diameter. The cyclic indentation loading was performed at displacements from 0.5 to 3 mm with an increment of 0.5 mm in each cycle. Subsequently, the residual compressive strength of the post-indented laminates was estimated by testing them under in-plane loading, once again with AE monitoring. Mechanical responses such as peak load, absorbed energy, stiffness, residual dent, and damage area were used for the quantification of the indentation-induced damage. The normalized AE cumulative counts, AE energy, and Felicity ratio were used for monitoring the damage initiation and propagation. Moreover, the discrete wavelet analysis of acoustic emission signals and fast Fourier transform enabled the calculation of the peak frequency content of each damage mechanism. The results showed that the cross-ply laminates had superior indentation damage resistance over angle ply and unidirectional (UD) laminates under normal and oblique planes of cyclic loading. However, the conclusion from the results was that UD laminates showed a better reduction in residual compressive strength than the other laminate configurations.

scholarly journals Contact Behaviour of Composite Laminate under Quasi-Static Indentation Load

2013 ◽  
Vol 577-578 ◽  
pp. 545-548
Author(s):  
Z. Shen ◽  
Y.G. Xu ◽  
Andreas Chrysanthou
Keyword(s):  
Composite Laminates ◽  
Matrix Material ◽  
Substantial Reduction ◽  
Indentation Load ◽  
Contact Behavior ◽  
Damage Initiation ◽  
Indentation Force ◽  
Contact Behaviour ◽  
Static Indentation ◽  
Engineering Alloys

A viable solution to the ever-demanding weight-saving target in aerospace industry is the replacement of conventional engineering alloys with composite materials in primary structures. A major concern to the effective use of composite laminates is the substantial reduction in the compressive strength when the contact force has exceeded the delamination threshold load (DTL). This paper focuses on the study of the contact behavior of composite laminates under quasi-static indentation (QSI) forces. The effect of damage initiation and growth on contact behavior has been investigated via detailed assessment of the relation between the indentation force and the dent depth. Different phases corresponding to undamaged, local damage, global damage, and final failure of the laminate have been identified. A modification to the classical Hertz contact law has been proposed to account for the matrix material resistance to plastic deformation.

scholarly journals Palliatives for Low Velocity Impact Damage in Composite Laminates

2017 ◽  
Vol 2017 ◽  
pp. 1-16 ◽  
Author(s):  
Mubarak Ali ◽  
S. C. Joshi ◽  
Mohamed Thariq Hameed Sultan
Keyword(s):  
Composite Laminates ◽  
Impact Damage ◽  
Laminated Composites ◽  
Low Velocity Impact ◽  
Normal Operation ◽  
Fibre Reinforcement ◽  
Low Velocity ◽  
Velocity Impact ◽  
Damage Initiation ◽  
The Impact

Fibre reinforced polymer laminated composites are susceptible to impact damage during manufacture, normal operation, maintenance, and/or other stages of their life cycle. Initiation and growth of such damage lead to dramatic loss in the structural integrity and strength of laminates. This damage is generally difficult to detect and repair. This makes it important to find a preventive solution. There has been abundance of research dealing with the impact damage evolution of composite laminates and methods to mitigate and alleviate the damage initiation and growth. This article presents a comprehensive review of different strategies dealing with development of new composite materials investigated by several research groups that can be used to mitigate the low velocity impact damage in laminated composites. Hybrid composites, composites with tough thermoplastic resins, modified matrices, surface modification of fibres, translaminar reinforcements, and interlaminar modifications such as interleaving, short fibre reinforcement, and particle based interlayer are discussed in this article. A critical evaluation of various techniques capable of enhancing impact performance of laminated composites and future directions in this research field are presented in this article.

Material orthotropy effects on progressive damage analysis of open-hole composite laminates under tension

2017 ◽  
Vol 36 (20) ◽  
pp. 1473-1486 ◽  
Author(s):  
Song Zhou ◽  
Yi Sun ◽  
Boyang Chen ◽  
Tong-Earn Tay
Keyword(s):  
Composite Laminates ◽  
Damage Mechanics ◽  
Damage Model ◽  
Continuum Damage Mechanics ◽  
Tensile Loading ◽  
Progressive Damage ◽  
Cohesive Elements ◽  
Damage Initiation ◽  
Proposed Model ◽  
Open Hole

The sizes effects on the strengths of open-hole fibre-reinforced composite laminates subjected to tensile loading (OHT) have been investigated widely. However, little attention has been paid to the influence of material orthotropy. This paper presents a progressive damage model for the model failure of notched laminates under tensile loading based on continuum damage mechanics and cohesive elements. The effects of orthotropy on the failure of notched laminates with seven different ply sequences are investigated by our proposed model. The prediction results adopting the Hoffman and Pinho failure criterions to determine matrix damage initiation are compared with the results of experiments. Our proposed models are able to predict the strong influence of orthotropy on strengths of open-hole laminate under tension, and model using Pinho criterion can predict the open-hole tension strength most accurately.

Rapid Predicting the Impact Behaviors of Marine Composite Laminates

2015 ◽  
Vol 813 ◽  
pp. 19-27 ◽  
Author(s):  
Ang Qiu ◽  
Cheng Bi Zhao ◽  
You Hong Tang ◽  
Wei Lin
Keyword(s):  
Composite Laminates ◽  
Impact Damage ◽  
Computing Time ◽  
Fe Model ◽  
Cohesive Elements ◽  
Damage Initiation ◽  
Short Computing Time ◽  
Marine Engineering ◽  
Impact Energies ◽  
The Impact

There are challenges of using composite laminates in the marine engineering, i.e., composites are frequently suffering from the effects of impaction including wave impaction, ship or other objects hitting, missiles or bullets hitting and other especially conditions. It is significant to understand the impact behaviors of laminates, in this research, the impact responses of typical laminates are investigated numerically. The delamination responses among the plies and fibre and/or matrix damage responses within the plies are simulated to understand the impaction behaviours of laminates under impaction conditions. The impact damage of composite laminates in the form of intra-and/or inter-laminar cracking is modelled by using stress-based criteria for damage initiation, and fracture mechanics technique is used to capture its evolution. Interface cohesive elements are inserted between plies with appropriate mixed-mode damage laws to predict the delamination. A group of graphite fibre/epoxy laminates with impact energies of 5, 10, 15 and 20 J, respectively, are simulated with a full scale FE model and a simplified FE model respectively. Through comparing the simulation results with each other, we find out that the impact behaviors obtained in the simplified FE model is comparable to experiments with a short computing time, but the simplified model cannot represent the properties of laminate after impact.

Damage initiation and growth in composite laminates during open hole compression tests

2012 ◽  
Vol 21 (3) ◽  
pp. 209-220 ◽  
Author(s):  
Hiroshi Suemasu ◽  
Yosuke Naito ◽  
Katsuhisa Gozu ◽  
Yuichiro Aoki
Keyword(s):  
Composite Laminates ◽  
Compression Tests ◽  
Damage Initiation ◽  
Open Hole

Enabling damage detection: manufacturing composite laminates doped with dispersed triboluminescent materials

2011 ◽  
Vol 30 (22) ◽  
pp. 1869-1876 ◽  
Author(s):  
Tarik J. Dickens ◽  
Okenwa I. Okoli
Keyword(s):  
Tensile Strength ◽  
Health Monitoring ◽  
Composite Laminates ◽  
Curing Kinetics ◽  
Processing Parameters ◽  
In Situ Monitoring ◽  
Mechanical Agitation ◽  
Damage Initiation ◽  
Vacuum Infusion ◽  
Monitoring Technologies

Triboluminescent materials are being harnessed to address the gaps in current structural health monitoring systems. Their innate ability to emit light when stressed or broken makes them ideal candidates for the ubiquitous and in situ monitoring of structures. The increasing use of advanced composites in critical structures, where subsurface damage initiation may go unnoticed, further highlights the urgency in developing efficient online monitoring technologies. This work looked at the manufacturing of composite laminates that have been doped with various concentrations (0 to 10 %wt.) of a triboluminescent material (ZnS:Mn). Laminates were manufactured using a vacuum infusion process. Dispersing the ZnS:Mn particulates was cumbersome because their density was higher than the resin that caused settling during resin infusion. The dispersion of ZnS:Mn is critical to their use in the health monitoring of the host structure. As such, a method for mechanical agitation using a rotational vacuum infusion apparatus was developed employing centrifugal motion. The degree of dispersion in the resulting laminates was determined using scanning electron microscopy and the energy dispersive scanning feature of the electron microscope for elemental mapping. A quantitative metric was established by computations of the Euclidean distance of EDS mapping. Studies of the effect of ZnS:Mn concentration on the tensile strength of laminates showed that increasing the ZnS:Mn concentration reduced the tensile strength. Key processing parameters were studied, and determined that curing kinetics were not altered by ZnS:Mn inclusion.

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