Log in

Relevant bibliographies by topics / Ply damage / Journal articles

Journal articles on the topic 'Ply damage'

To see the other types of publications on this topic, follow the link: Ply damage.

Author: Grafiati

Published: 4 June 2021

Last updated: 2 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'Ply damage.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

TOHGO, Keiichiro, Yuji SUGIYAMA, and Kazutomo KAWAHARA. "Ply-Cracking Damage and Nonlinear Deformation of CFRP Cross-Ply Laminate." JSME International Journal Series A 45, no. 4 (2002): 545–52. http://dx.doi.org/10.1299/jsmea.45.545.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Fuller, J. D., and M. R. Wisnom. "Pseudo-ductility and damage suppression in thin ply CFRP angle-ply laminates." Composites Part A: Applied Science and Manufacturing 69 (February 2015): 64–71. http://dx.doi.org/10.1016/j.compositesa.2014.11.004.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Prato, Alessia, Marco Longana, Ambreen Hussain, and Michael Wisnom. "Post-Impact Behaviour of Pseudo-Ductile Thin-Ply Angle-Ply Hybrid Composites." Materials 12, no. 4 (February 15, 2019): 579. http://dx.doi.org/10.3390/ma12040579.

Full text

Abstract:

This work experimentally explores the post-impact behaviour of thin-ply angle-ply pseudo-ductile carbon fibre laminates subjected to tensile load. Indentation and low-speed impact tests were performed on standard tensile test specimens. Non-destructive tests were used to investigate the damage propagation. Digital Image Correlation (DIC) was adopted to detect the strain distribution during tensile tests. Post-damage pseudo-ductile behaviour was retained in angle-ply hybrid composites subjected to tensile loading conditions.

APA, Harvard, Vancouver, ISO, and other styles

4

Aoki, Ryoma, Ryo Higuchi, Tomohiro Yokozeki, Kazuyuki Aoki, Shigekazu Uchiyama, and Toshio Ogasawara. "Damage-mechanics mesoscale modeling of composite laminates considering diffuse and discrete ply damages: Effects of ply thickness." Composite Structures 277 (December 2021): 114609. http://dx.doi.org/10.1016/j.compstruct.2021.114609.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

NODA, Junji, Tomonaga OKABE, Nobuo TAKEDA, and Masao SHIMIZU. "Damage Process of GFRP Cross-ply Laminates." Transactions of the Japan Society of Mechanical Engineers Series A 70, no. 698 (2004): 1364–69. http://dx.doi.org/10.1299/kikaia.70.1364.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

TOHGO, Keiichiro, Yuji SUGIYAMA, and Kazutomo KAWAHARA. "Ply-Cracking Damage and Nonlinear Deformation of CFRP Cross-Ply Laminate(Composite 2)." Proceedings of the Asian Pacific Conference on Fracture and Strength and International Conference on Advanced Technology in Experimental Mechanics 2.01.03 (2001): 633–38. http://dx.doi.org/10.1299/jsmeatemapcfs.2.01.03.0_633.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

YAMADA, Kohei, Satoru YAMAMOTO, Manato KANESAKI, Masaaki NISHIKAWA, Naoki MATSUDA, Kazumasa KAWABE, and Masaki HOJO. "Effect of Ply Thickness on Impact Damage Modes of Thin-ply CFRP Laminates." Journal of the Japan Society for Composite Materials 46, no. 1 (January 15, 2020): 21–30. http://dx.doi.org/10.6089/jscm.46.21.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Onkar, Amit K. "Nonlinear buckling analysis of damaged laminated composite plates." Journal of Composite Materials 53, no. 22 (February 28, 2019): 3111–26. http://dx.doi.org/10.1177/0021998319833446.

Full text

Abstract:

An updated Lagrangian-based nonlinear finite element method is developed to study the buckling behavior of damaged laminated composite plates under uniaxial compression. In this study, material imperfections are treated as existing static damage and a continuum damage mechanics-based approach is used to model such imperfections. The laminated plate is modeled as a set of elementary layers bonded together by matrix-rich elastic interface. This allows to model different modes of damage present at both elementary ply level and interply interface separately. A layerwise plate model is used to model both elementary ply and interface layers of the laminate. The effect of different forms of existing static damage on the limit point loads and the corresponding displacements of laminated plates are studied. It is observed that for the chosen modes and size of the damaged regions, the limit point load does not change much as compared to the undamaged plate. However, the deformed shapes show significant changes and some very interesting phenomena like local wrinkling behaviour of the damaged region is observed. The effect of ply orientation along with different modes of damage on the limit points and the corresponding deformed shapes of laminated plates are also discussed.

APA, Harvard, Vancouver, ISO, and other styles

9

Onodera, Sota, and Tomonaga Okabe. "Analytical model for determining effective stiffness and mechanical behavior of polymer matrix composite laminates using continuum damage mechanics." International Journal of Damage Mechanics 29, no. 10 (July 26, 2020): 1512–42. http://dx.doi.org/10.1177/1056789520939624.

Full text

Abstract:

The present paper proposes a new analytical model for predicting the effective stiffness of composite laminates with fiber breaks and transverse cracks. The model is based on continuum damage mechanics and the classical laminate theory. We derived damage variables describing stiffness reduction due to fiber breaks and its maximum value during ultimate tensile failure from the global load-sharing model. Furthermore, a simplified analytical model is presented for obtaining two damage variables for a cracked ply subjected to transverse tensile loading or in-plane shear loading. This model was developed assuming that the displacement field of the longitudinal direction can be expressed in the form of a quadric function by loosening the boundary condition for the governing differential equation. For verifying the developed model, the elastic constants of damaged composite laminates were predicted for cross-ply and angle-ply laminates and compared with the finite element analysis results. As for the appropriate expression of the effective elastic stiffness matrix of the damaged ply, we verified four types of effective compliance/stiffness matrices including the Murakami, Yoshimura, Li, and Maimí models. We found the Maimí model to be the most appropriate among these four models. Moreover, we successfully simplified the expressions for damage variables in the complicated infinite series obtained in our previous study. We also proved that this could contribute toward improving the accuracy of our analysis. After verifying the present model, the stress–strain response and failure strength of carbon- or glass-fiber-reinforced plastic cross-ply laminates were predicted using Maimí’s compliance model and the simplified damage variables.

APA, Harvard, Vancouver, ISO, and other styles

10

TOHGO, Keiichiro, Kenji AKIZUKI, and Yuji SUGIYAMA. "Ply Cracking Damage Theory and Damage Behavior in CFRP Cross-poly Laminates." Transactions of the Japan Society of Mechanical Engineers Series A 64, no. 621 (1998): 1160–67. http://dx.doi.org/10.1299/kikaia.64.1160.

Full text

APA, Harvard, Vancouver, ISO, and other styles

11

Rebière, Jean-Luc. "Partial Strain Energy Release Rate for Study Matrix Cracking Evolution in Composite Cross-Ply Laminates." Advanced Composites Letters 24, no. 3 (May 2015): 096369351502400. http://dx.doi.org/10.1177/096369351502400301.

Full text

Abstract:

Matrix cracking is generally the first observed damage in composite laminates. The stress field distribution in the damaged cross ply laminates is analysed through an approach which uses several hypotheses to simplify the damage state. The proposed cracking criterion involves the respective partial part of the 0° and 90° layers to the damage process. The initiation of transverse and longitudinal cracking mechanisms is predicted.

APA, Harvard, Vancouver, ISO, and other styles

12

Li, Hong Peng, Fang Lue Huang, Jin Hai Hu, and Ying Jun Lv. "Impact Damage Research of Composite Laminates with AL Ply." Advanced Materials Research 710 (June 2013): 186–90. http://dx.doi.org/10.4028/www.scientific.net/amr.710.186.

Full text

Abstract:

The composite material has been widely used in aircraft structures. But this kind of material has some shortage such as poor impact resistance, low residual compressive strength, which have a negative influence on the performance of aircraft structures. In this paper, simulations of low-velocity impact and compression process of composite laminates with AL ply has been done. Finite element software ABAQUS/Explicit has been adopted to simulate the 3.5J impact and compression. A certain number of composite laminates with different thickness of AL ply has been tested, equal weight traditional composite laminates also been simulated as comparison. The simulation results show that AL ply with certain thickness can improve the residual compressive strength.

APA, Harvard, Vancouver, ISO, and other styles

13

Pieniak, D. "Initiation and Tolerance of Macro-Damage of First Ply (FBF) in a Process of Damaging of Hybrid Multi-Ply Structures Due to Reinforcement Archtecture." Advances in Materials Science 18, no. 2 (June 1, 2018): 77–91. http://dx.doi.org/10.1515/adms-2017-0034.

Full text

Abstract:

AbstractThe objective of this paper was study and analysis of damaging process of multi-ply structure applied in dentistry. The aim was to analyze and experimentally evaluate tolerance of macro-damage of first ply (FPF - first ply failure) of multi-ply composite. A studied structure of composite makes a carrying structure for dental applications e.g. adhesive bridges. Influence of reinforcement structure on the residual carrying capacity of the studied multi-ply materials has been demonstrated. It has been shown that the type of fiber and fiber ribbon architecture play a major role in strength of studied reinforcements. Structures included in the study differ by the moment of macro-damage occurrence, carrying capacity and residual stiffness.

APA, Harvard, Vancouver, ISO, and other styles

14

McCartney, L. N. "Physically based damage models for laminated composites." Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications 217, no. 3 (July 1, 2003): 163–99. http://dx.doi.org/10.1177/146442070321700301.

Full text

Abstract:

The computing power that is available for engineering calculation continues to grow at a dramatic pace. Engineers in industry want to have seamless models that can be used to design across the scale range from atoms to structures, including simulation of the manufacturing process. A limited aspect of this wish is the requirement to deal effectively with the progressive growth of microstructural damage in composites and its effect on both property degradation and the catastrophic failure event. This paper reviews progress that is being made at the National Physical Laboratory (NPL) with the development and validation of physically based damage growth models for laminated composites. The review includes: (a) prediction of undamaged ply properties determined from the properties of the fibre and the matrix, with emphasis on comparison of analytical models with each other, and with finite and boundary element solutions; (b) discussion of various stress transfer models, and their validation, that have been developed for application to the prediction of the properties of composite laminates having ply crack damage; (c) prediction of ply cracking in multiple-ply cross-ply laminates subject to triaxial loading (without shear) and bending; (d) prediction of ply cracking in general symmetric laminates subject to combined triaxial loading and in-plane shear loading; (e) consideration in a damage mechanics context of progressive ply crack formation in general symmetric laminates subject to thermal residual stresses and general in-plane loading, where an important new methodology is described that results from attempting to develop a continuum damage model from a physically based discrete ply cracking model based on energy concepts; (f) discussion of how the models might be integrated into finite element analysis (FEA) systems to enable strain softening in structures to be adequately modelled. The paper also includes statements concerning the status of the various models in relation to alternative approaches, and to model validation.

APA, Harvard, Vancouver, ISO, and other styles

15

Biswas, S., P. K. Datta, and C. D. Kong. "Static and dynamic instability characteristics of curved laminates with internal damage subjected to follower loading." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 225, no. 7 (May 17, 2011): 1589–600. http://dx.doi.org/10.1177/0954406211399977.

Full text

Abstract:

This article deals with the study of vibration, buckling, and dynamic instability characteristics in damaged cross-ply and angle-ply curved laminates under uniform, uniaxial follower loading, using finite element approach. First-order shear deformation theory is used to model the doubly curved panels and is formulated according to Sandars' first approximation. Damage is modelled using an anisotropic damage formulation. Analysis is carried out on plate and three types of curved panels to obtain vibration, buckling, and dynamic instability (flutter) behaviour. The effect of damage on natural frequency, critical buckling load, flutter load, and flutter frequency is studied. The results show that the introduction of damage influences the flutter characteristics of panels more profoundly than the free-vibration or buckling characteristics. The results also indicate that, compared to undamaged panels, heavily damaged panels show steeper deviations in stability characteristics than mildly damaged ones.

APA, Harvard, Vancouver, ISO, and other styles

16

Karthick, Subramani, and Prosun Kumar Datta. "Dynamic Instability Characteristics of Thin Plate Like Beam with Internal Damage Subjected to Follower Load." International Journal of Structural Stability and Dynamics 15, no. 03 (March 8, 2015): 1450048. http://dx.doi.org/10.1142/s0219455414500485.

Full text

Abstract:

This study investigates the vibration, buckling and dynamic instability characteristics of damaged cross-ply and angle-ply laminated plate like beam under follower loading using the finite element approach. The damage is anisotropic in nature and parametrically incorporated into the composite using the concept of reduction in stiffness. It has been observed that damage shows a strong orthogonality and in general deteriorates the vibration and buckling characteristics. For follower type of loading, analysis is carried out on plate like beam structure to obtain the flutter characteristics. The effects of damage and its location on flutter characteristics are studied. The desirable position of damage on the plate like beam structure based on different stability behavior is discussed. The results show that flutter is observed as primary modes of instability when damaged plate like beam is subjected to follower loads. The behavior of flutter characteristics for different damaged parameters is discussed.

APA, Harvard, Vancouver, ISO, and other styles

17

Tian, Z., and S. R. Swanson. "Residual Tensile Strength Prediction on a Ply-by-Ply Basis for Laminates Containing Impact Damage." Journal of Composite Materials 26, no. 8 (August 1992): 1193–206. http://dx.doi.org/10.1177/002199839202600807.

Full text

APA, Harvard, Vancouver, ISO, and other styles

18

TOHGO, Keiichiro, Yuji SUGIYAMA, and Kenji AKIZUKI. "Ply-Cracking Damage Theory for Cross-Ply Laminate and Its Application to Finite Element Method." Transactions of the Japan Society of Mechanical Engineers Series A 65, no. 639 (1999): 2230–37. http://dx.doi.org/10.1299/kikaia.65.2230.

Full text

APA, Harvard, Vancouver, ISO, and other styles

19

TOHGO, Keiichiro, Yuji SUGIYAMA, and Kenji AKIZUKI. "Ply-Cracking Damage Theory for Cross-Ply Laminate and Its Application to Finite Element Method." JSME International Journal Series A 44, no. 2 (2001): 282–90. http://dx.doi.org/10.1299/jsmea.44.282.

Full text

APA, Harvard, Vancouver, ISO, and other styles

20

Belingardi, Giovanni, Ermias Gebrekidan Koricho, and Alem Tekalign Beyene. "Characterization and damage analysis of notched cross-ply and angle-ply fabric GFRP composite material." Composite Structures 102 (August 2013): 237–49. http://dx.doi.org/10.1016/j.compstruct.2013.03.006.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

Geng, Xiaoliang, Fanfan Ji, Jiu Wang, Wang Dou, Peiyan Wang, and Zhufeng Yue. "Experimental and numerical investigations of compression stability of stiffened composite panel with ply interleaving." Journal of Composite Materials 51, no. 26 (February 20, 2017): 3647–56. http://dx.doi.org/10.1177/0021998317692397.

Full text

Abstract:

A novel composite layup technique (ply interleaving) is proposed to satisfy the extraordinary needs in aircraft structure design. Buckling experiments and corresponding simulations with different configurations are carried out to study the mechanical properties of the stiffened panel with this ply layout and get a suitable numerical prediction method. A ply-by-ply-based modeling technique is applied to characterize the real discontinuity in each ply. Additionally, the relationship between the macroscopic buckling and damage evolution is investigated by the comparative analyses of experiments and simulations. The investigations show the following results: the panel with ply interleaving has a considerable anti-buckling capability besides its flexible layout; both adhesive layer damage and lamina damage should be included in the simulation for obtaining reliable solution; the panel would buckle while adhesive layer damage occurs between stiffeners and skin, which initiates firstly in the ply interleaving zone and then expands to the surrounding area; internal damage of each ply also originates around discontinuities then develops rapidly, leading to the panel failure. The prediction results of buckling and failure show good agreements with the experimental results, so the suggested simulation technique is verified to be an effective method to study the mechanical behavior of the composite plate with preset discontinuities.

APA, Harvard, Vancouver, ISO, and other styles

22

Zheng, Yu Fang, Yi Ming Fu, and Kai Qi. "Nonlinear Free Vibration for Cross-Ply Laminated Damaged Plates with Piezoelectric Actuators." Key Engineering Materials 324-325 (November 2006): 479–82. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.479.

Full text

Abstract:

On the basis of the anisotropic damage theory and piezoelectric theory, the nonlinear free vibration governing equations for cross-ply laminated damaged plates with piezoelectric actuators are established. The Galerkin procedure furnishes an infinite system of equations for time functions which are solved by the method of harmonic balance. In the numerical results, the influences of damage parameters and piezoelectric effect on the nonlinear amplitude-frequency response curves of the laminated plates are discussed, which results reveal the inherent features about the coupled mechanics and electricity.

APA, Harvard, Vancouver, ISO, and other styles

23

Benbelaid, S., B. Bezzazi, and A. Bezazi. "Cross-Ply Laminates under Static Three-Point Bending: A Numerical Development Model." Key Engineering Materials 498 (January 2012): 42–54. http://dx.doi.org/10.4028/www.scientific.net/kem.498.42.

Full text

Abstract:

This paper considers damage development mechanisms in cross-ply laminates using an accurate numerical model. Under static three points bending, two modes of damage progression in cross-ply laminates are predominated: transverse cracking and delamination. However, this second mode of damage is not accounted in our numerical model. After a general review of experimental approaches of observed behavior of laminates, the focus is laid on predicting laminate behavior based on continuum damage mechanics. In this study, a continuum damage model based on ply failure criteria is presented, which is initially proposed by Ladevèze. To reveal the effect of different stacking sequence of the laminate; such as thickness and the interior or exterior disposition of the 0° and 90° oriented layers in the laminate, an equivalent damage accumulation which cover all ply failure mechanisms has been predicted. However, the solution algorithm using finite element analysis which implements progressive failure analysis is summarized. The results of the numerical computation have been justified by the previous published experimental observations of the authors.

APA, Harvard, Vancouver, ISO, and other styles

24

Sebaey, T. A., E. V. González, C. S. Lopes, N. Blanco, and J. Costa. "Damage resistance and damage tolerance of dispersed CFRP laminates: Effect of ply clustering." Composite Structures 106 (December 2013): 96–103. http://dx.doi.org/10.1016/j.compstruct.2013.05.052.

Full text

APA, Harvard, Vancouver, ISO, and other styles

25

Liu, Wei, Hongying Zhang, Haoyu Feng, Miao Hu, and Zishan Chen. "Effect of fiber architecture on the residual strength of laminate glass fiber-reinforced polymer composites after impact." Advanced Composites Letters 29 (January 1, 2020): 2633366X1989791. http://dx.doi.org/10.1177/2633366x19897919.

Full text

Abstract:

Glass fiber-reinforced polymer (GFRP) composites are widely applied in automotive and shipbuilding industry. However, impact damage is unavoidable to the composites during production or service, and the evaluation of performance degradation after impact is necessary. The architecture of the fiber preform shows significant influence on the impact damage behavior of GFRP. The present work focused on the influence of preform structure on damage evolution and residual load-bearing capability of the composites. The microstructure and the residual strength after the impact of GFRP with plain-weave preform structure and cross-ply preform structure have been investigated, respectively. The low velocity impact primarily caused matrix cracking and delamination, but unobvious fiber failure to GFRP. More impact-damaged plies were detected in cross-ply composites than plain-weave composites after impact. It indicated that plain-weave preform structure owes better impact damage shielding capability. However, the GFRP with plain-weave preform structure exhibited better impact resistant ability under low impact energy but less residual strength under high impact energy, compared with the GFRP with cross-ply preform structure. The interaction between the warp and weft fibers made the plain-weave composites absorbing more energy in a single ply, which was the reason for the plain-weave composites to exhibit excellent damage shielding performance but poor residual strength under high impact energy.

APA, Harvard, Vancouver, ISO, and other styles

26

Kumazawa, Hisashi, Hirotaka Hayashi, Ippei Susuki, and Takao Utsunomiya. "Damage and permeability evolution in CFRP cross-ply laminates." Composite Structures 76, no. 1-2 (October 2006): 73–81. http://dx.doi.org/10.1016/j.compstruct.2006.06.011.

Full text

APA, Harvard, Vancouver, ISO, and other styles

27

Takeda, Nobuo, Shinji Ogihara, and Akira Kobayashi. "Microscopic fatigue damage progress in CFRP cross-ply laminates." Composites 26, no. 12 (December 1995): 859–67. http://dx.doi.org/10.1016/0010-4361(95)90879-5.

Full text

APA, Harvard, Vancouver, ISO, and other styles

28

LADEVEZE, P., and E. LEDANTEC. "Damage modelling of the elementary ply for laminated composites." Composites Science and Technology 43, no. 3 (1992): 257–67. http://dx.doi.org/10.1016/0266-3538(92)90097-m.

Full text

APA, Harvard, Vancouver, ISO, and other styles

29

Yang, W., and J. P. Boehler. "Micromechanics modelling of anisotropic damage in cross-ply laminates." International Journal of Solids and Structures 29, no. 10 (1992): 1303–28. http://dx.doi.org/10.1016/0020-7683(92)90240-t.

Full text

APA, Harvard, Vancouver, ISO, and other styles

30

Zheng, Kaidong, Dongfeng Cao, Haixiao Hu, Yundong Ji, and Shuxin Li. "Mechanical Properties of Thin-Ply Composites Based on Acoustic Emission Technology." Materials 14, no. 4 (February 15, 2021): 913. http://dx.doi.org/10.3390/ma14040913.

Full text

Abstract:

Compared with standard-ply composites, thin-ply composites exhibit a superior mechanical performance under various operating conditions due to their positive size effects. Thin-ply laminate failure modes, including matrix initial damage (MID), matrix failure (MF), and fiber failure (FF), have been distinguished through a systematic acoustic emission (AE) signals analysis combined with scanning electron microscopy (SEM). First, the characteristic frequencies of various failure modes are identified based on unidirectional laminates ([90] 68 and [0] 68). Then, according to the identified frequencies corresponding to distinctive damage modes, four lay-up sequences (02[[90m/0m]ns]02, m = 1, 2, 4, 8, n × m = 16) with a constant total thickness are designed, and the effects of the number of identical plies in the laminate thickness on the damage evolution characteristics and the damage process under uniaxial tension loads are dynamically monitored. The obtained results indicate that the characteristic frequency ranges for MID, MF, and FF are identified as 0–85 kHz, 165–260 kHz, and 261–304 kHz, respectively. The thickness of identical plies has a significant effect on onset damage. With the decrease of the number of identical plies (i.e., m in the stacking sequences), the thin-ply laminates exhibit the initiation of damage suppression effects and crack propagation resistance.

APA, Harvard, Vancouver, ISO, and other styles

31

Tan, J. L. Y., V. S. Deshpande, and N. A. Fleck. "Prediction of failure in notched carbon-fibre-reinforced-polymer laminates under multi-axial loading." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 374, no. 2071 (July 13, 2016): 20150273. http://dx.doi.org/10.1098/rsta.2015.0273.

Full text

Abstract:

A damage-based finite-element model is used to predict the fracture behaviour of centre-notched quasi-isotropic carbon-fibre-reinforced-polymer laminates under multi-axial loading. Damage within each ply is associated with fibre tension, fibre compression, matrix tension and matrix compression. Inter-ply delamination is modelled by cohesive interfaces using a traction-separation law. Failure envelopes for a notch and a circular hole are predicted for in-plane multi-axial loading and are in good agreement with the observed failure envelopes from a parallel experimental study. The ply-by-ply (and inter-ply) damage evolution and the critical mechanisms of ultimate failure also agree with the observed damage evolution. It is demonstrated that accurate predictions of notched compressive strength are obtained upon employing the band broadening stress for microbuckling, highlighting the importance of this damage mode in compression. This article is part of the themed issue ‘Multiscale modelling of the structural integrity of composite materials’.

APA, Harvard, Vancouver, ISO, and other styles

32

Wu, X., J. D. Fuller, and M. R. Wisnom. "An investigation into fatigue behaviour and damage progression in pseudo-ductile thin-ply angle-ply laminates." Composites Part A: Applied Science and Manufacturing 149 (October 2021): 106518. http://dx.doi.org/10.1016/j.compositesa.2021.106518.

Full text

APA, Harvard, Vancouver, ISO, and other styles

33

Dzenis, Yu A., and S. P. Joshi. "Damage Induced Anisotropy in Laminates." Advanced Composites Letters 2, no. 3 (May 1993): 096369359300200. http://dx.doi.org/10.1177/096369359300200303.

Full text

Abstract:

A damage evolution model developed by the authors is utilized to study the effect of damage induced anisotropy on constitutive behavior and failure strength of laminates. It is shown that extension-shear coupling coefficients of the in-plane stiffness matrix radically change due to unequal damage accumulation in plies with opposite orientation under shear loading. This, in general, causes significant reduction in laminate shear strength. The angle-ply orientation and presence of zero degree plies in a laminate have a notable effect on damaged induced anisotropy.

APA, Harvard, Vancouver, ISO, and other styles

34

Todoroki, Akira, Masahito Ueda, and Yoshinobu Shimamura. "Damage Monitoring of Thick CFRP Beam Using Electrical Impedance Changes." Key Engineering Materials 353-358 (September 2007): 1298–301. http://dx.doi.org/10.4028/www.scientific.net/kem.353-358.1298.

Full text

Abstract:

Electrical resistance change method has been applied to monitor a delamination crack of a thin CFRP laminate. For a thick CFRP laminate, multiple delamination cracks are made with many matrix cracks, and the electric current in the thick CFRP laminate may not flow in the thickness direction due to the strong orthotropic electrical conductivity. The present study employs an electric impedance change method for the identification of damage location and dimension of the damaged area; applicability of the method is investigated experimentally using thick beam-type specimens fabricated from cross-ply laminates of 36 plies. After making the damage, electrical impedance was decreased. A residual stress relief model was proposed to explain the decrease. From the measured electrical impedance changes, the relationships between the electrical impedance changes and damages are obtained by means of response surfaces. The response surfaces estimated the damage location and dimension of the damaged area exactly even for the thick CFRP laminates. The electrical impedance change method can be used as an appropriate sensor for measurement of residual stress relief due to damages of thick CFRP laminates.

APA, Harvard, Vancouver, ISO, and other styles

35

Jalalvand, Meisam, Hossein Hosseini-Toudeshky, and Bijan Mohammadi. "Numerical modeling of diffuse transverse cracks and induced delamination using cohesive elements." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 227, no. 7 (September 19, 2012): 1392–405. http://dx.doi.org/10.1177/0954406212460974.

Full text

Abstract:

This article is devoted to the modeling of spread kind of damages such as matrix cracking and induced delamination in symmetric and asymmetric cross-ply laminates of composite materials using cohesive elements. For matrix crack modeling, parallel rows of cohesive elements are used between every row of 2D elements in 90° layers. Delamination is also modeled by cohesive elements at the 90°/0° interface. Since matrix cracking is a diffuse kind of damage mechanism, application of cohesive elements is not straightforward, and special techniques are necessary to resolve the modeling difficulties. For this purpose, two techniques of “bisecting” and “random distribution of strength of cohesive elements” are proposed here. Both techniques are applied to various symmetric laminates of [0/903]s and [90n/0]s (n = 1 to 3). The predicted stiffness and damage progresses from both techniques are in good agreement with the experimental results. Then, asymmetric cross-ply laminates of [90n/0] (n = 1 to 3) are analyzed to show the capability of this method in progressive damage analyses. The proposed method is less restricted in comparison with available micromechanical methods and is able to predict damage initiation, propagation and damage-mode transition for any symmetric and asymmetric cross-ply sequence. Therefore, this method can be used for development of “in-plane damage” of constitutive laws especially when specimens are subjected to complex loading and boundary conditions.

APA, Harvard, Vancouver, ISO, and other styles

36

Wei, Wu Guo. "Static Tensile Properties Simulation of Plane Woven-Reinforced Laminates with Hole Damage." Advanced Materials Research 936 (June 2014): 2017–23. http://dx.doi.org/10.4028/www.scientific.net/amr.936.2017.

Full text

Abstract:

According to the structural difference between the unidirectional and the bidirectional laminate ply, the traditional 3-D (three-dimensional) Hashin failure criteria and the corresponding stiffness degradation rules were amended for damage tolerance simulation analysis of plane woven-reinforced laminates. Based on 3-D finite element technique, a secondary development was carried out on ANSYS software platform, a cumulative damage model was established, and the simulation analysis program for damage tolerance analysis of plane woven-reinforced laminates with hole damage was developed by use of APDL (ANSYS Parametric Design Language). In order to study the influence of different hole diameters on damage tolerance of plane woven-reinforced laminates, two kinds of G803/BMP316 plane woven-reinforced laminates with different hole diameters were selected as the analysis and verification object, and residual tensile strength and damage extension process of the damaged laminates were predicted and analyzed in the simulation. The simulations results are close to the experimental results, and visually present the situation of damage extension in each ply. It provides an effective tool for the damage tolerance analysis of plane woven-reinforced laminates with hole damage.

APA, Harvard, Vancouver, ISO, and other styles

37

Luo, Xiang Cheng, Tao Zhang, and Qing Shan Wang. "Ply Thickness’ Effect on Composite Laminate under Low-Velocity Impact." Advanced Materials Research 989-994 (July 2014): 74–78. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.74.

Full text

Abstract:

Based on the two-dimensional Hashin failure criteria and the introduction of material degradation damage factor, low-speed impact model of composite laminated plate was established by ABAQUS with fiber and matrix’s failure modes being taken into consideration. The mode is verified by referring to Karakuzu test. Next, it analyzes single ply thickness’ effect on laminated plate’s response and damaged under low-velocity impact. The result shows that with the thickness increasing, impact contact time and laminated plate impact point’s deflection displacement reduce, while the impact force and volatile shocks are more obvious.

APA, Harvard, Vancouver, ISO, and other styles

38

Cherniaev, Aleksandr, Svetlana Pavlova, Aleksandr Pavlov, and Valeriy Komarov. "Prediction of Load-Bearing Capacity of Composite Parts with Low-Velocity Impact Damage: Identification of Intra- and Inter-Ply Constitutive Models." Applied Mechanics 1, no. 1 (March 6, 2020): 59–78. http://dx.doi.org/10.3390/applmech1010005.

Full text

Abstract:

Assessments of residual load-carrying capacity are often conducted for composite structural components that have received impact damage. The availability of a verified simulation methodology can provide significant cost savings when such assessments are required. To support the development of a reliable and accurate simulation methodology, this study investigated the predictive capabilities of a stacked solid-shell finite element model of a cylindrical composite component with a damage mechanics-based description of the intra-ply material response and a cohesive contact model used for simulation of the inter-ply behavior. Identification of material properties for the model was conducted through mechanical characterization. Special attention was paid to understanding the influence of non-physical parameters of the intra- and inter-ply material models on predicting compressive failure load of damaged composite cylinders. Calibration of the model conducted using the response surface methodology allowed for identifying rational values of the non-physical parameters. The results of simulations with the identified and calibrated finite element model showed reasonable correlation with experimental data in terms of the predicted failure loads and post-impact and post-failure damage modes. The investigated modeling technique can be recommended for evaluating the residual load-bearing capacity of flat and curved composite parts with impact damage working under the action of compressive loads.

APA, Harvard, Vancouver, ISO, and other styles

39

Donadon, Maurício V., Sérgio Frascino M. de Almeida, Mariano A. Arbelo, and Alfredo R. de Faria. "A Three-Dimensional Ply Failure Model for Composite Structures." International Journal of Aerospace Engineering 2009 (2009): 1–22. http://dx.doi.org/10.1155/2009/486063.

Full text

Abstract:

A fully 3D failure model to predict damage in composite structures subjected to multiaxial loading is presented in this paper. The formulation incorporates shear nonlinearities effects, irreversible strains, damage and strain rate effects by using a viscoplastic damageable constitutive law. The proposed formulation enables the prediction of failure initiation and failure propagation by combining stress-based, damage mechanics and fracture mechanics approaches within an unified energy based context. An objectivity algorithm has been embedded into the formulation to avoid problems associated with strain localization and mesh dependence. The proposed model has been implemented into ABAQUS/Explicit FE code within brick elements as a userdefined material model. Numerical predictions for standard uniaxial tests at element and coupon levels are presented and discussed.

APA, Harvard, Vancouver, ISO, and other styles

40

Chen, Yong, Bao Jun Pang, and Wei Zheng. "Elastic Ply Damage Mechanics Modeling of Glass/Epoxy Laminated Composite." Advanced Materials Research 683 (April 2013): 176–81. http://dx.doi.org/10.4028/www.scientific.net/amr.683.176.

Full text

Abstract:

In order to establish an elastic damage model for S2-glass/epoxy composite and identify the input parameters, in-plane behaviour of the composite including tensile, compression and tensile shear were investigated through series of tests. Concerning no plasticity, a simple elastic ply damage mechanics model for this composite was characterized based on Continuum Damage Mechanics Model (CDM) and the input parameters were obtained. The model was then implemented into ABAQUS/EXPLICT and the results show the model can capture most of the in-plane behaviour of the composite material.

APA, Harvard, Vancouver, ISO, and other styles

41

Saito, Hiroshi, Hiroki Takeuchi, and Isao Kimpara. "Experimental Evaluation of the Damage Growth Restraining in 90° Layer of Thin-ply CFRP Cross-ply Laminates." Advanced Composite Materials 21, no. 1 (February 1, 2012): 57–66. http://dx.doi.org/10.1163/156855112x629522.

Full text

APA, Harvard, Vancouver, ISO, and other styles

42

Wagih, A., P. Maimí, N. Blanco, S. M. García-Rodríguez, G. Guillamet, R. P. Issac, A. Turon, and J. Costa. "Improving damage resistance and load capacity of thin-ply laminates using ply clustering and small mismatch angles." Composites Part A: Applied Science and Manufacturing 117 (February 2019): 76–91. http://dx.doi.org/10.1016/j.compositesa.2018.11.008.

Full text

APA, Harvard, Vancouver, ISO, and other styles

43

NDDA, Junji, Tomonaga OKABE, Nobuo TAKEDA, and Masao SHIMIZU. "Damage Process of [90/0]s GFRP Cross-ply Laminates." Journal of the Japan Society for Composite Materials 31, no. 3 (2005): 112–19. http://dx.doi.org/10.6089/jscm.31.112.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Wharmby, A. W., and F. Ellyin. "Damage growth in constrained angle-ply laminates under cyclic loading." Composites Science and Technology 62, no. 9 (July 2002): 1239–47. http://dx.doi.org/10.1016/s0266-3538(02)00075-1.

Full text

APA, Harvard, Vancouver, ISO, and other styles

45

Kastritseas, C., P. A. Smith, and J. A. Yeomans. "Damage characterisation of thermally shocked cross-ply ceramic composite laminates." Journal of Materials Science 41, no. 3 (February 2006): 951–62. http://dx.doi.org/10.1007/s10853-006-6594-8.

Full text

APA, Harvard, Vancouver, ISO, and other styles

46

Aymerich, F., C. Pani, and P. Priolo. "Damage response of stitched cross-ply laminates under impact loadings." Engineering Fracture Mechanics 74, no. 4 (March 2007): 500–514. http://dx.doi.org/10.1016/j.engfracmech.2006.05.012.

Full text

APA, Harvard, Vancouver, ISO, and other styles

47

Kortschot, M. T., and C. J. Zhang. "Characterization of composite mesostructures and damage by de-ply radiography." Composites Science and Technology 53, no. 2 (January 1995): 175–81. http://dx.doi.org/10.1016/0266-3538(95)00016-x.

Full text

APA, Harvard, Vancouver, ISO, and other styles

48

Arteiro, A., G. Catalanotti, J. Xavier, and P. P. Camanho. "Large damage capability of non-crimp fabric thin-ply laminates." Composites Part A: Applied Science and Manufacturing 63 (August 2014): 110–22. http://dx.doi.org/10.1016/j.compositesa.2014.04.002.

Full text

APA, Harvard, Vancouver, ISO, and other styles

49

Edlund, Ulf, and Pieter Volgers. "A composite ply failure model based on continuum damage mechanics." Composite Structures 65, no. 3-4 (September 2004): 347–55. http://dx.doi.org/10.1016/j.compstruct.2003.11.010.

Full text

APA, Harvard, Vancouver, ISO, and other styles

50

ATIKAH, Zulkifli NUR, M. J. MOHAMMAD FIKRY, Masaru IRITA, and Shinji OGIHARA. "Damage Behavior in Angle-Ply CFRP Laminates with Fiber Discontinuity." Proceedings of the Materials and processing conference 2020.28 (2020): 113. http://dx.doi.org/10.1299/jsmemp.2020.28.113.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!