Relevant bibliographies by topics / Interlaminar and intralaminar damage

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Interlaminar and intralaminar damage'

Author: Grafiati
Published: 7 April 2023

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Journal articles on the topic "Interlaminar and intralaminar damage"

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Keršienė, Neringa, and Antanas Žiliukas. "INTERLAMINAR AND INTRALAMINAR DAMAGE MECHANISMS OF IMPACT RESISTANT AIRCRAFT MATERIALS UNDER LOW‐ENERGY IMPACT." Aviation 10, no. 3 (September 30, 2006): 3–8. http://dx.doi.org/10.3846/16487788.2006.9635933.

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For low-velocity impact, drop‐weight impact tests performed by EADS (European Aeronautic Defence and Space Company) Corporate Research Center Germany have been carried out for 2‐D woven E‐Glass/epoxy composite systems to determine material response as a function of absorbed energy and damaged area. Nondestructive techniques like visual inspection and analysis of impact response of the woven fabric laminates at different energy levels are utilized to assess the initiation and progression of interlaminar and intralaminar damage. The dominant damage modes for woven reinforced composite systems were found to be matrix cracking with branching into the adjacent layers, intralaminar cracking by mixture of localized matrix shear and matrix/fibre interfacial debonding, front face indentation, and back face fibre damage. The use of woven fabrics as opposed to cross‐ply unidirectional prepreg tapes is specifically discussed from the point view of microstructure and property. In the case of low‐energy impact, damage resistance under impact loading of woven and multiaxial non‐crimp fabrics is presented and compared. The assumption that shear‐response dominated for woven reinforced composite systems was found to be in good agreement with the experimental results.
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Bruno, Domenico, Fabrizio Greco, and Paolo Lonetti. "Interaction Between Interlaminar and Intralaminar Damage in Fiber-Reinforced Composite Laminates." International Journal for Computational Methods in Engineering Science and Mechanics 9, no. 6 (September 30, 2008): 358–73. http://dx.doi.org/10.1080/15502280802365824.

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Li, N., P. H. Chen, and Q. Ye. "A damage mechanics model for low-velocity impact damage analysis of composite laminates." Aeronautical Journal 121, no. 1238 (March 6, 2017): 515–32. http://dx.doi.org/10.1017/aer.2017.6.

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ABSTRACTA method was developed to predict numerically the damage of composite laminates with multiple plies under low-velocity impact loading. The Puck criterion for 3D stress states was adopted to model the intralaminar damage including matrix cracking and fibre breakage, and to obtain the orientation of the fracture plane due to matrix failure. According to interlaminar delamination mechanism, a new delamination criterion was proposed. The influence of transverse and through-thickness normal stress, interlaminar shear stress and damage conditions of adjacent plies on delamination was considered. In order to predict the impact-induced damage of composite laminates with more plies quickly and efficiently, an approach, which can predict the specific damage of several plies in a single solid element, was proposed by interpolation on the strains of element integration points. Moreover, the proposed model can predict specific failure modes. A good agreement between the predicted delamination shapes and sizes and the experimental results shows correctness of the developed numerical method for predicting low-velocity impact damage on composite laminates.
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Liao, BB, and PF Liu. "Finite element analysis of dynamic progressive failure properties of GLARE hybrid laminates under low-velocity impact." Journal of Composite Materials 52, no. 10 (August 10, 2017): 1317–30. http://dx.doi.org/10.1177/0021998317724216.

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This paper aims to study dynamic progressive failure properties of glass fiber composite/aluminium hybrid laminates under low-velocity impact. Intralaminar damage models using Puck failure criteria and strain-based damage evolution laws for composite layers are implemented by developing finite element codes using ABAQUS-VUMAT (user dynamic material subroutine), the interface delamination is simulated by bilinear cohesive model in ABAQUS and the mechanical properties of aluminium layers are described using the Johnson-Cook model. Effects of different layer thickness and impact energy on the impact force–time/displacement curves of glass fiber composite/aluminium laminates under low-velocity impact are discussed. Besides, damage evolution behaviors of matrix and delamination interface are explored. Finally, energy dissipation mechanisms due to intralaminar dynamic progressive failure, interlaminar delamination of composite layers and plastic deformation of aluminium layers are studied. Relatively good agreement is obtained between experimental and numerical results.
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Duplessis Kergomard, Y., J. Renard, A. Thionnet, and C. Landry. "Intralaminar and interlaminar damage in quasi-unidirectional stratified composite structures: Experimental analysis." Composites Science and Technology 70, no. 10 (September 30, 2010): 1504–12. http://dx.doi.org/10.1016/j.compscitech.2010.05.006.

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Hassoon, Omar H., Mayyadah S. Abed, Jawad K. Oleiwi, and M. Tarfaoui. "Experimental and numerical investigation of drop weight impact of aramid and UHMWPE reinforced epoxy." Journal of the Mechanical Behavior of Materials 31, no. 1 (January 1, 2022): 71–82. http://dx.doi.org/10.1515/jmbm-2022-0008.

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Abstract Due to their characteristics such as weight/strength ratio and absorbed energy, the widespread use of composite materials in the last decades engorged the companies to exploit these materials invariant applications like the aerospace, automobile, and marine hull. However, there are some obstructs to the use of these materials that may constrain that. This came from the fact, that composite materials suffer from different damages modes that occur during loading and can be lead to catastrophic failure in their structure, such as intralaminar and interlaminar damage. Consequently, this motivated the researchers to study its behavior considering different damage modes and at different loading states. This work performed a finite element simulation using the Abaqus program of low-velocity drop impact for epoxy reinforced with Kevlar 49 and Ultra High Molecular Weight Polyethylene (UHMWPE) with different thicknesses and number of layers. A user-defined material VUMAT subroutine-based progressive damage model, and the Hashin failure criteria implemented in Abaqus Explicit finite element code had been utilized in this work. In Addition, the interlaminar damage models depend on the cohesive zone model (CZM). The numerical simulation results were compared with the experiments data to confirm the reliability of the numerical model.
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Zou, Z., S. R. Reid, S. Li, and P. D. Soden. "Modelling Interlaminar and Intralaminar Damage in Filament-Wound Pipes under Quasi-Static Indentation." Journal of Composite Materials 36, no. 4 (February 2002): 477–99. http://dx.doi.org/10.1177/0021998302036004539.

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BALZANI, CLAUDIO, and WERNER WAGNER. "NUMERICAL TREATMENT OF DAMAGE PROPAGATION IN AXIALLY COMPRESSED COMPOSITE AIRFRAME PANELS." International Journal of Structural Stability and Dynamics 10, no. 04 (October 2010): 683–703. http://dx.doi.org/10.1142/s0219455410003683.

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In the design phase of stringer-stiffened composite airframe panels, it is a key issue to exploit material reserves as far as possible to create lighter and safer aircraft. A recent approach is to apply postbuckling design — standard for metallic panels — also to composite parts. This work focusses on the development of a simulation procedure which accurately predicts the postbuckling response of composite panels while accounting for damage propagation. For this purpose we employ a robust shell element formulation which allows for arbitrary stacking sequences as well as a variable location of the reference plane. A ply discount model is incorporated to account for intralaminar damage growth. The cohesive zone approach is implemented in a so-called interface element to predict interlaminar damage growth, respective skin–stringer separation. The numerical model is validated via a numerical example with experimental evidence.
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Meon, M. S., N. H. Mohamad Nor, S. Shawal, J. B. Saedon, M. N. Rao, and K. U. Schröder. "On the Modelling Aspect of Low-Velocity Impact Composite Laminates." journal of Mechanical Engineering 17, no. 2 (July 15, 2020): 13–25. http://dx.doi.org/10.24191/jmeche.v17i2.15297.

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Composites suffer a degradation of structural stiffness due to various types of impact loading resulting in damage which is difficult to observe from the surface of the structure. The paper deals with the finite element model (FEM) to study the possible modelling procedures in low-velocity impact (LVI) and failure mechanism of carbon fiber reinforced polymer (CFRP) composite laminate of CCF300/epoxy and its structural responses. In finite element calculation, a proposed three-dimensional progressive damage model is used to determine the intralaminar damage, whereas the cohesive contact formulation is employed to analyse the interlaminar damage. The failure model performances are validated and verified based on different boundary conditions while maintaining the impact energy. Through simulation, the variation in boundary conditions significantly changes the structural responses and energy absorption of the laminates. It is hoped this study will be a great tool in determining the different composite impact scenarios.
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Townsend, Patrick, Juan Carlos Suárez, Paz Pinilla, and Nadia Muñoz. "Insertion of a Viscoelastic Layer to Reduce the Propagation of Energy by Vertical Impacts of Slamming in Planing Hull Vessels." Key Engineering Materials 889 (June 16, 2021): 65–70. http://dx.doi.org/10.4028/www.scientific.net/kem.889.65.

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For the design of vessels built by GFRP laminates, an insert with a viscoelastic layer is proposed to reduce the spread of damage produced by the vertical impact of the ship's bottom with the sea or slamming phenomenon. Using vertical drops-weight impact machine that reproduce the energy inferred to the panel during navigation, the propagation of the damage of OoA cured prepreg panels is studied comparing it with modified panels with insertion of viscoelastic layer. The use of acceleration data reading allows the benefits of viscoelastic modification during impact to be quantified through the developed formulation. The force, displacement and energy returned by the panel after impact have also been quantified, which does not become intralaminar and interlaminar damage. It is shown that under 40 joules of impact, the viscoelastic sheet has its best ability to return energy and above 130 joules it loses its capacity.
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Dissertations / Theses on the topic "Interlaminar and intralaminar damage"

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González, Juan Emilio Vicente. "Simulation of interlaminar and intralaminar damage in polymer-based composites for aeronautical applications under impact loading." Doctoral thesis, Universitat de Girona, 2011. http://hdl.handle.net/10803/22834.

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La aplicación de materiales compuestos de matriz polimérica reforzados mediante fibras largas (FRP, Fiber Reinforced Plastic), está en gradual crecimiento debido a las buenas propiedades específicas y a la flexibilidad en el diseño. Uno de los mayores consumidores es la industria aeroespacial, dado que la aplicación de estos materiales tiene claros beneficios económicos y medioambientales. Cuando los materiales compuestos se aplican en componentes estructurales, se inicia un programa de diseño donde se combinan ensayos reales y técnicas de análisis. El desarrollo de herramientas de análisis fiables que permiten comprender el comportamiento mecánico de la estructura, así como reemplazar muchos, pero no todos, los ensayos reales, es de claro interés. Susceptibilidad al daño debido a cargas de impacto fuera del plano es uno de los aspectos de más importancia que se tienen en cuenta durante el proceso de diseño de estructuras de material compuesto. La falta de conocimiento de los efectos del impacto en estas estructuras es un factor que limita el uso de estos materiales. Por lo tanto, el desarrollo de modelos de ensayo virtual mecánico para analizar la resistencia a impacto de una estructura es de gran interés, pero aún más, la predicción de la resistencia residual después del impacto. En este sentido, el presente trabajo abarca un amplio rango de análisis de eventos de impacto a baja velocidad en placas laminadas de material compuesto, monolíticas, planas, rectangulares, y con secuencias de apilamiento convencionales. Teniendo en cuenta que el principal objetivo del presente trabajo es la predicción de la resistencia residual a compresión, diferentes tareas se llevan a cabo para favorecer el adecuado análisis del problema. Los temas que se desarrollan son: la descripción analítica del impacto, el diseño y la realización de un plan de ensayos experimentales, la formulación e implementación de modelos constitutivos para la descripción del comportamiento del material, y el desarrollo de ensayos virtuales basados en modelos de elementos finitos en los que se usan los modelos constitutivos implementados.
The application of polymer-based composites reinforced by long fibers, called advanced Fiber Reinforced Plastic (FRP), is gradually increasing as a result of their good specific mechanical properties and increased flexibility of design. One of the largest consumers is the aerospace industry, since the application of these materials has clear economic and environmental benefits. When composites are to be used in structural components, a design development program is initiated, where a combination of testing and analysis techniques is typically performed. The development of reliable analysis tools that enable to understand the structure mechanical behavior, as well as to replace most, but not all, the real experimental tests, is of clear interest. Susceptibility to damage from concentrated out-of-plane impact forces is one of the major design concerns of structures made of advanced FRPs used in the aerospace industry. Lack of knowledge of the impact effects on these structures is a factor in limiting the use of composite materials. Therefore, the development of virtual mechanical testing models to analyze the impact damage resistance of a structure is of great interest, but even more, the prediction of the post-impact residual strength. In this sense, the present thesis covers a wide range of analysis of the low-velocity and large mass impact events on monolithic, flat, rectangular, polymer-based laminated composite plates with conventional stacking sequences. Keeping in mind that the main goal of this work is the prediction of the residual compressive strength of an impacted specimen coupon, a set of different tasks are performed in order to provide suitable tools to analyze the problem. Accordingly, the topics which are addressed in this thesis are: the analytical description of the impact, the design and the realization of an experimental test plan, the formulation and implementation of constitutive models for the description of the composite material behavior, and the assessment of the performance of virtual tests based on finite element models where the constitutive models are used.
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Sebaey, Abdella Tamer Ali Abdella. "Characterization and optimization of dispersed composite laminates for damage resistant aeronautical structures." Doctoral thesis, Universitat de Girona, 2013. http://hdl.handle.net/10803/98393.

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The main objective of the thesis is to assess the damage resistance and damage tolerance of the non-conventional dispersed laminates and compare the response with the conventional ones. However, part of the effort is spent on understanding the delamination behavior in multidirectional laminates. In the first part of the thesis, the delamination in multidirectional laminates is studied. The objective is to design a proper stacking sequence, capable of avoiding intralaminar damage (crack jumping), to enable the fracture toughness characterization under pure mode I. The result of this study shows that the higher the crack arm bending stiffness, the lower the tendency to crack jumping. This phenomenon is also studied experimentally and the same conclusion is drawn.
El principal objectiu de la tesi és valorar la resistència al dany i la tolerància al dany dels laminats no-convencionals dispersos i comparar la seva resposta amb la dels laminats convencionals. No obstant, part de l'atenció es dedica a comprendre el comportament de la delaminació en laminats multidireccionals. En la primera part de la tesi, s'analitza la delaminació en laminats multidireccionals. L'objectiu és dissenyar una seqüència d'apilament apropiada per evitar el dany intralaminar (migració de la delaminació) i permetre la caracterització de la tenacitat a la fractura en model. Els resultats d'aquests estudi mostren que a major rigidesa a flexió dels braços de l'esquerda, menor és la tendència a la migració de l'esquerda. Aquest aspecte també s'ha analitzat experimentalment, obtenint les mateixes conclusions.
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Akterskaia, Margarita [Verfasser]. "Global-local progressive failure analysis of composite panels including skin-stringer debonding and intralaminar damage / Margarita Akterskaia." Hannover : Gottfried Wilhelm Leibniz Universität Hannover, 2019. http://d-nb.info/1193177200/34.

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Maziz, Ammar. "Analyse des endommagements dans les pipes en matériaux composites." Electronic Thesis or Diss., Brest, École nationale supérieure de techniques avancées Bretagne, 2021. http://www.theses.fr/2021ENTA0019.

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La modélisation de l'endommagement des matériaux composites hybrides a joué un rôle important dans la conception des structures composites. Bien que des modèles numériques pour l'endommagement progressif des pipes en matériaux composites hybrides à enroulement filamentaire, tels que la fissuration matricielle, le délaminage et la rupture des fibres, aient été développés dans la littérature, des améliorations sont encore nécessaires. Cette thèse vise à développer des modèles d'endommagement adaptés à la prédiction du comportement dynamique et l'endommagement intra-laminaire et inter-laminaire dans les tubes en matériaux composites hybrides sous une pression interne, et soumis à un chargement dynamique tel que l'impact d'un objet externe. Les approches de la mécanique de la rupture et de la mécanique de l’endommagement ont été adoptées pour construire le modèle de dommages. Une analyse détaillée a été réalisée pour avoir une vue d'ensemble de tous les mécanismes d'endommagement jusqu'à la rupture finale. Des éléments cohésifs ont été implémentés dans les modèles bidimensionnels et tridimensionnels pour simuler l'initiation et la propagation d’endommagement interlaminaire (délaminage) dans les stratifiés. Une subroutine a été implémentée dans le code de calcul FE (Abaqus/Explicit) via une VUMAT afin de modéliser l’endommagement intralaminaire. Par la suite, des validations basées sur des corrélations essai/calcul sur des sous-systèmes et/ou des pièces réelles ont été effectuées. L'initiation des dommages est prédite sur la base des critères de rupture contrainte-déformation, tandis que la loi d'évolution des dommages est basée sur la dissipation de l'énergie de rupture. Le comportement non linéaire du matériau en cisaillement a également été pris en compte et validé par rapport aux résultats expérimentaux. Les prédictions montrent un excellent accord avec les observations expérimentales
Damage modelling of hybrid composite materials has played an important role in the design of composite structures. Although numerical models for the progressive damage of filament wound hybrid composite pipes such, matrix cracking, delamination, and fiber failure have been developed in the literature; there is still a need for improvement. This thesis aims to develop damage models suitable for predicting dynamic behaviour and intra-laminar and inter-laminar damage in hybrid composite tubes under internal pressure subjected to dynamic loading such as the impact of an external object. Fracture mechanics and continuum damage mechanics approaches were adopted to build the damage model. A detailed analysis was performed to have an overview of all the damage mechanisms until the final failure. Cohesive elements were inserted into the two-dimensional and three-dimensional models to simulate the initiation and propagation of matrix cracking and delamination in cross-layered laminates. The damage model was implemented in the FE code (Abaqus/Explicit) by a user-defined material subroutine (VUMAT). Subsequently, validations based on test/calculation correlations on real subsystems and/or parts were performed. Damage initiation was predicted based on the stress-strain failure criteria, while the damage evolution law was based on the dissipation of failure energy. The nonlinear behavior of the material in shear was also taken into account and validated against experimental/numerical results. The predictions show excellent agreement with the experimental observations
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Farge, Laurent. "Caractérisation de l'endommagement de matériaux composites stratifiés à l'aide de la mesure du déplacement par une méthode optique plein-champ." Thesis, Vandoeuvre-les-Nancy, INPL, 2009. http://www.theses.fr/2009INPL052N/document.

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Cette thèse résulte d’une collaboration entre le Pr Ayadi de l’Institut National Polytechnique de Lorraine et le Pr Varna de l’Université Technologique de Luleå. Depuis 2005, le Professeur Varna a développé une méthode originale qui permet d’obtenir l’ensemble des constantes thermoélastiques d’un stratifié endommagé à partir de deux paramètres : l’ouverture moyenne et le glissement moyen des lèvres des fissures, normalisés par rapport à la contrainte appliquée. Dans cette thèse, nous analysons le potentiel de l’interférométrie de speckle pour obtenir la mesure de ces deux grandeurs. Plus généralement, nous montrons l’utilité de la mesure du champ de déplacement pour caractériser le développement de l’endommagement dans les stratifiés. Le premier chapitre décrit l’endommagement qui peut affecter les matériaux composites stratifiés. L’objectif est de mettre en évidence les points particuliers pour lesquels la mesure du champ de déplacement pourrait apporter des informations originales. Dans le deuxième chapitre, le principe de l’interférométrie de speckle est exposé. Nous avons particulièrement insisté sur les raisons qui nous on conduit à choisir cette technique pour réaliser cette étude. Dans le troisième chapitre, nous présentons une étude expérimentale du potentiel de l’interférométrie de speckle pour caractériser les différentes formes d’endommagement qui peuvent apparaître dans un stratifié verre/époxyde . Enfin, dans le dernier chapitre, nous analysons expérimentalement le développement de l’endommagement dans un stratifié carbone/époxyde
This work results from a collaboration between Pr Ayadi (Institut Polytechnique de Lorraine) and Pr Varna (Technical University of Luleå). Since 2005, Pr Varna has developed an original method that allows for the determination of all the thermoelastic constants of a damaged laminate. The stiffness reduction is governed by two parameters: the average value of the opening and the average value of the sliding of the crack surfaces. These values are normalized with respect to the applied loading. In this work, the potential of speckle interferometry is analysed to obtain these two parameters. More generally, we show the usefulness of displacement field measurements to characterize damage development in laminates. The first chapter is dedicated to the damage that occurs in laminates. The main objective is to highlight the points for which displacement field measurements could bring interesting information. In the second chapter, the principle of speckle interferometry is described. The choice of this technique for the considered application is discussed and justified. In the third chapter, an experimental study of the potential of speckle interferometry is proposed to characterize the damage forms that occur in a glass/epoxy laminate. In the last chapter, the development of damage is experimentally analysed in a carbon/epoxy laminate
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Orifici, Adrian Cirino, and adrian orifici@student rmit edu au. "Degradation Models for the Collapse Analysis of Composite Aerospace Structures." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080619.090039.

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Iervolino, Onorio. "Enhanced impact resistance and pseudo plastic behaviour in composite structures through 3D twisted helical arrangement of fibres and design of a novel chipless sensor for damage detection." Thesis, University of Bath, 2017. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.723326.

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The future of the aerospace industry in large part relies on two factors: (i) development of advanced damage tolerant materials and (ii) development of advanced smart sensors with the ability to detect and evaluate defects at very early stages of component service life. Laminated composite materials, such as carbon fibre reinforced plastics (CFRP), have emerged as the materials of choice for increasing the performance and reducing the cost and weight of aircrafts, which leads to less fuel consumption and therefore lower CO2 emissions. However, it is well known that these materials exhibit fragile behaviour, poor resistance to impact damage caused by foreign objects and require a relatively slow and labour intensive manufacturing process. These factors prevent the rapid expansion of composite materials in several industrial sectors at the current time. Inspired by the use of rope throughout history and driven by the necessity of creating a lean manufacturing process for composites and enhancing their impact properties, the first part of this work has shown that enhanced damage tolerance and pseudo-ductile behaviour can be achieved with standard CFRP by creatively arranging the fibres into a 3D twisted helical configuration. Through an extensive experimental campaign a new method to arrange fibre reinforcement was presented and its effect investigated. The second part of this PhD work focused on developing a new smart sensor. A spiral passive electromagnetic sensor (SPES) for damage detection on CFRP and glass fibre reinforced plastics (GFRP) is presented in this work. A range of defect types in glass and carbon composite has been considered, such as delamination, perforated holes and cracks. Furthermore, throughout this work, the SPES has been exploited as a multi-sensing device allowing the ability to detect temperature and humidity variation, presence of ice and act as an anti/de-icing device.
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Ben, Kahla Hiba. "Models for bending stiffness in laminates with intralaminar and interlaminar damage." Thesis, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-44595.

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Books on the topic "Interlaminar and intralaminar damage"

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German, Janusz. Intralaminar damage in fiber-reinforced polymeric matrix laminates. Cracow: Cracow University of Technology, 2004.

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Illg, Walter. Effect of partial interlaminar bonding on impact resistance and loaded-hole behavior of graphite/epoxy quasi-isotropic laminates. Hampton, Va: Langley Research Center, 1986.

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Grami, Vahid, Salim M. Hayek, and Samer N. Narouze. Lumbar Transforaminal and Nerve Root Injections: Fluoroscopy. Oxford University Press, 2016. http://dx.doi.org/10.1093/med/9780199908004.003.0016.

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The transforaminal approach, compared with the interlaminar approach, allows injectate delivery directly at the target nerve root, placing greater amounts of medication at the location of the suspected pathology. The utility of selective nerve root injections includes blocking with local anesthetics specific nerve roots suspected of transmitting radicular symptoms. These diagnostic radicular blocks are often used for presurgical planning. The fluoroscopic-guided lumbar transforaminal epidural steroid injection approaches mentioned in this chapter have been described to safely and effectively deposit medication in the epidural space, adjacent to affected nerve roots transmitting pain signals. It is imperative that proper patient selection, physician training, thorough knowledge of anatomy, vigilance, and effective use of fluoroscopy and radiocontrast dye help to avoid catastrophic tissue damage and embolization.
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Book chapters on the topic "Interlaminar and intralaminar damage"

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Huchette, Cédric, Thomas Vandellos, and Frédéric Laurin. "Influence of Intralaminar Damage on the Delamination Crack Evolution." In Springer Aerospace Technology, 107–40. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-04004-2_5.

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Massabò, Roberta. "Effective Modeling of Interlaminar Damage in Multilayered Composite Structures Using Zigzag Kinematic Approximations." In Handbook of Damage Mechanics, 1–34. New York, NY: Springer New York, 2020. http://dx.doi.org/10.1007/978-1-4614-8968-9_91-1.

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Massabò, Roberta. "Effective Modeling of Interlaminar Damage in Multilayered Composite Structures Using Zigzag Kinematic Approximations." In Handbook of Damage Mechanics, 665–98. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-60242-0_91.

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Prinz, R. "Damage Rates for Interlaminar Failure of Fatigued CFRP Laminates." In Developments in the Science and Technology of Composite Materials, 189–94. Dordrecht: Springer Netherlands, 1990. http://dx.doi.org/10.1007/978-94-009-0787-4_23.

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Li, Lei, and Zhu Feng Yue. "Analysis of Interlaminar Stresses and Failure around Hole Edge for Composite Laminates under In-Plane Loading." In Fracture and Damage Mechanics V, 1027–30. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-413-8.1027.

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Shimamura, Y., A. Todoroki, and H. Kobayashi. "Intralaminar and Interlaminar Fracture Growth Simulation of Composite Plates Based on Finite Element Method by Using Plane Elements." In Design and Manufacturing of Composites, 149–53. New York: CRC Press, 2021. http://dx.doi.org/10.1201/9781003076131-28.

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Bilal Afzal, Muhammad. "Modeling of Damage Evolution of Fiber-Reinforced Composite Structure." In Safety and Risk Assessment of Civil Aircraft during Operation. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.93323.

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This chapter is the result of a study of many special disciplines, such as damage of matrix, cracking, interface, debonding, and fiber failure. A damage mechanics model is presented to characterize brittle failure in elastic fiber-reinforced composite materials. During the life of the aircraft, cracks and damage can occur in aviation structures that should be analyzed to determine the decrease in stiffness and resistance due to the presence of the cracks. Theoretical and numerical problems related to intralaminar and interlaminar failure modeling are very well discussed. The formulations of the constitutive models presented in this chapter support the Continuum Damage Mechanics (CDM) approach and enable the control of energy dissipation in relation to each failure mode, regardless of the refinement of the network and the orientation of the fracture plane. In context to CDM, internal thermodynamic irreversible damage variables are defined to quantify the damage concentration in relation to each possible failure mode and to predict the gradual reduction in stiffness for each bond layer. Numerical examples are provided to possibly explain the capabilities of the model.
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Isa, Tadashi, Masatoshi Kasai, and Richard Veale. "The Superior Colliculus." In Handbook of Brain Microcircuits, edited by Gordon M. Shepherd and Sten Grillner, 457–66. Oxford University Press, 2017. http://dx.doi.org/10.1093/med/9780190636111.003.0039.

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The superior colliculus (SC) is a midbrain center that integrates sensory input and transforms the information into a command signal to initiate behaviors, such as orienting to an object that attracts attention or escaping from a predator. It is a laminar structure composed of two primary layers: the superficial layer and the deeper layer. There are interactions between the layers, and there are also interactions within each layer. This chapter first summarizes recent studies on the intrinsic circuits in the SC, and discusses the neural circuits involved in these interlaminar and intralaminar interactions. Then, it describes how extrinsic GABAergic and cholinergic inputs to the SC modulate the activity of SC local circuits.
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Varandas, L. F., G. Catalanotti, A. Arteiro, António R. Melro, and B. G. Falzon. "Micromechanical modelling of interlaminar damage propagation and migration." In Multi-Scale Continuum Mechanics Modelling of Fibre-Reinforced Polymer Composites, 307–47. Elsevier, 2021. http://dx.doi.org/10.1016/b978-0-12-818984-9.00011-1.

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Forghani, A., M. Shahbazi, N. Zobeiry, A. Poursartip, and R. Vaziri. "An overview of continuum damage models used to simulate intralaminar failure mechanisms in advanced composite materials." In Numerical Modelling of Failure in Advanced Composite Materials, 151–73. Elsevier, 2015. http://dx.doi.org/10.1016/b978-0-08-100332-9.00006-2.

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Conference papers on the topic "Interlaminar and intralaminar damage"

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Özkaya, Özge, and Altan Kayran. "Nonlinear Static Aeroelastic Behavior of Composite Missile Fin with Interlaminar and Intralaminar Damage." In 2018 AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1449.

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MEYER, CHRISTOPHER S., BAZLE Z. HAQUE, DANIEL J. O’BRIEN, and OHN W. GILLESPIE, JR. "MICROMECHANICAL FINITE ELEMENT PREDICTION OF INTERLAMINAR TRACTION-SEPARATION LAWS USING J-INTEGRAL APPROACH." In Thirty-sixth Technical Conference. Destech Publications, Inc., 2021. http://dx.doi.org/10.12783/asc36/35941.

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Dynamic impact loading of woven composites leads to mesoscale damage such as interlaminar transverse cracks and intralaminar tow-tow delamination cracks. At the microscale, this damage may be modeled as fracture between [90/90] and [0/90] unidirectional composite laminates. Microscale finite element model (FEM) resolution of dynamic impact at structural length scale is intractable, but mesoscale FEM resolution is possible with current computational resources. However, mesoscale cohesive zone modeling of this damage requires appropriate tractionseparation laws. These laws are predicted in this work with fiber length-scaleresolved FEMs, which include residual stress, experimentally measured, ratedependent, nonlinear matrix behavior, and experimentally measured, computationally validated, rate-dependent fiber-matrix interface properties. The J-integral from elastoplastic fracture mechanics is computed under mode I and mode II loading and differentiated to determine the traction-separation laws.
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NIETO, ZACKERY, EDGAR AVALOS, VIPUL RANATUNGA, and ALEJANDRA CASTELLANOS. "ASSESSMENT ON THE CAPABILITIES OF ABAQUS AND LS-DYNA TO PREDICT THE BEHAVIOR OF LAMINATED COMPOSITES SUBJECTED TO LOW-VELOCITY IMPACTS." In Proceedings for the American Society for Composites-Thirty Seventh Technical Conference. Destech Publications, Inc., 2022. http://dx.doi.org/10.12783/asc37/36430.

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Composite materials have excellent in-plane mechanical properties. However, they have a low resistance to impact damage. Low-velocity impacts (LVI) produce barely visible impact damage (BVID) on the surface of the laminate but with the potential to produce significant internal damage, such as delamination and matrix cracking. Composite materials' impact damage evaluation still largely relies on experimental results rather than numerical simulations because of the material's multiple damage mechanisms. In an attempt to mitigate cost and time requirements for large-scale experimental studies, there have been significant strides toward enhancing computational simulations to incorporate and predict damage mechanisms observed in composite structures. However, current computational models have limitations in how they capture the impact response and damage spread in laminated composites. The present study compares the predictive capabilities of two commercially available software, ABAQUS and LS-Dyna, to assess their feasibility in capturing the impact response and damage spread on laminated composites. The computational responses will also be compared with the responses obtained experimentally. To the authors' best knowledge, there has not been any report in the literature that compares the predicting capabilities of these two softwares. IM7/977-3 graphite epoxy unidirectional laminates with a 32-ply layup [-45/0/45/90]4S were manufactured according to the ASTM D7136/D7136M-12. Drop weight impact tests were performed in an Instron CEAST 9350. The samples were subjected to LVI energies of 30 J. From each test, the contact force, displacement, velocity, energy and impact duration time were recorded to compare with the predicted responses from the computational models. To evaluate the internal damage area, nondestructive inspection (NDI) was performed on all the samples with X-ray. The objective is to compare the internal damage per layer of each experiment with the internal damage obtained from the ABAQUS and LS-Dyna computational models. For the ABAQUS model, the intralaminar damage (ply failure) model consisted of a continuum damage model, Hashin failure criterion, and a damage evolution model based on equivalent displacement. The interlaminar damage (delamination) was incorporated through a cohesive surface interaction with a bilinear traction-separation law. In the LS-Dyna model, MAT261 Laminated Fracture Daimler-Pinho material card was used as the intralaminar damage model. MAT261 is a continuum damage model with linear softening evolution based on fracture toughness. The interlaminar damage was incorporated through a Tiebreak contact algorithm with a bilinear traction-separation behavior. Preliminary studies have shown that the ABAQUS/Explicit model showed a good correlation with the experimental results in terms of contact force, impact duration time, and displacement. On the other hand, the LS-Dyna MAT261 material model underpredicted the contact force, impact duration time, and displacement. The extreme differences in the LS-Dyna simulation are attributed to MAT261’s algorithm requiring element deletion during the simulation to maintain stability. Therefore, the striker never rebounded and continued penetrating the laminate. Further impact energies will be explored with the ABAQUS computational model. For LS-Dyna, different venues need to be explored in calibration for MAT261’s material model to account for the element deletion’s energy loss or use a different material model.
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Tiano, Thomas, Margaret Roylance, Benjamin Harrison, and Richard Czerw. "Intralaminar Reinforcement for Biomimetic Toughening of Bismaleimide Composites Using Nanostructured Materials." In ASME 2005 International Mechanical Engineering Congress and Exposition. ASMEDC, 2005. http://dx.doi.org/10.1115/imece2005-81689.

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Many conventional composite materials are composed of multiple layers of continuous fiber reinforced resin produced by lamination of b-staged prepreg and subsequent cure. These materials exhibit very high strength and stiffness in the plane, dominated by the properties of the fibers. The Achilles heel of such composites is the interlaminar strength, which is dependent on the strength of the unreinforced resin, often leading to failure by delamination under load. Current methods for increasing the interlaminar shear strength of composites consist of inserting translaminar reinforcement fibers through the entire thickness of a laminated composite, such as z-pin technology developed by Foster-Miller [1]. While effective, this technique adds several processing steps, including ultrasonic insertion of the z-pins into the laminate, subsequently causing a significant cost increase to laminated composites. Described in this paper is a process utilizing single-walled carbon nanotubes (SWNTs) and vapor grown carbon nanofibers as reinforcing elements promoting interlaminar shear strength and toughness in carbon fiber/bismaleimide (BMI) resin composites. The resulting composites mimic the natural reinforcing mechanism utilized in insect cuticles. Three different methods of increasing the affinity of these carbon nanofillers for the BMI matrix were explored. The mechanical properties of these composites were assessed using end notch flexure testing. The results indicated that including nanofiller at the laminae interface could increase the interlaminar shear strength of carbon fiber/BMI composites by up to 58%. SEM micrographs revealed that the nanofiller successfully bridged the laminae of the composite, thus biomimicking the insect cuticle. Composite fabrication techniques developed on this program would have a wide variety of applications in space and aerospace structures including leading and trailing edges of aircraft wings.
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Goyal-Singhal, Vinay, Navin Jaunky, Eric Johnson, and Damodar Ambur. "Intralaminar and Interlaminar Progressive Failure Analyses of Composite Panels with Circular Cutouts." In 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-1745.

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VENKATESAN, KARTHIK RAJAN, and ADITI CHATTOPADHYAY. "Multiscale Analysis for Interlaminar and Intralaminar Reinforcement of Composite Laminates with Carbon Nanotube Architecture." In American Society for Composites 2019. Lancaster, PA: DEStech Publications, Inc., 2019. http://dx.doi.org/10.12783/asc34/31387.

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Mohite, Preetamkumar, Gilles Lubineau, Pierre Ladeveze, and Ana-cristina Galucio. "Validation of Intralaminar Behaviour of the Laminated Composites by Damage Mesomodel." In 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2422.

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Bedsole, Robert, and Hareesh Tippur. "Interlaminar and Intralaminar Dynamic Fracture Behaviors of CFRP: An Investigation Using Digital Image Correlation and High-Speed Photography." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0892.

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Ngabonziza, Yves, Claudia Boldrini, Benjamin Liaw, Jackie Li, and Feridun Delale. "Damage Self-Diagnosis in Carbon Fiber-Reinforced Composites Under Fatigue Loading." In ASME 2010 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. ASMEDC, 2010. http://dx.doi.org/10.1115/smasis2010-3870.

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An experimental study was conducted to sense interlaminar delamination in carbon-fiber composites utilizing inherent material piezoresistivity. Damage detection was carried out using discrete electrodes mounted on a Double Cantilever Beam (DCB) specimen. The DCB composite specimens were tested for fatigue interlaminar fracture. The traditional two-point probe and four-point probe technique were employed to measure the through-thickness electrical resistance change. Optical marker method was also used to detect interlaminar crack growth. The results show that the two-point probe measurements did not capture effectively the delamination propagation while the four-point probe measurement showed a promising sensing capability in terms of delamination propagation.
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HYDER, IMRAN, JOSEPH SCHAEFER, BRIAN JUSTUSSON, STEVE WANTHAL, FRANK LEONE, and CHERYL ROSE. "Assessment of Intralaminar Progressive Damage and Failure Analysis Methods Using an Efficient Evaluation Framework." In American Society for Composites 2017. Lancaster, PA: DEStech Publications, Inc., 2017. http://dx.doi.org/10.12783/asc2017/15405.

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