Relevant bibliographies by topics / Angle-ply laminated composites

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

Academic literature on the topic 'Angle-ply laminated composites'

Author: Grafiati
Published: 4 June 2021
Last updated: 14 February 2022

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Journal articles on the topic "Angle-ply laminated composites"

1

Al-Madani, Ramadan A., M. Jarnaz, K. Alkharmaji, and M. Essuri. "Finite Element Modeling of Composites System in Aerospace Application." Applied Mechanics and Materials 245 (December 2012): 316–22. http://dx.doi.org/10.4028/www.scientific.net/amm.245.316.

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The characteristics of composite materials are of high importance to engineering applications; therefore the increasing use as a substitute for conventional materials, especially in the field of aircraft and space industries. It is a known fact that researchers use finite element programs for the design and analysis of composite structures, use of symmetrical conditions especially in complicated structures, in the modeling and analysis phase of the design, to reduce processing time, memory size required, and simplifying complicated calculations, as well as considering the response of composite structures to different loading conditions to be identical to that of metallic structures. Finite element methods are a popular method used to analyze composite laminate structures. The design of laminated composite structures includes phases that do not exist in the design of traditional metallic structures, for instance, the choice of possible material combinations is huge and the mechanical properties of a composite structure, which are anisotropic by nature, are created in the design phase with the choice of the appropriate fiber orientations and stacking sequence. The use of finite element programs (conventional analysis usually applied in the case of orthotropic materials) to analysis composite structures especially those manufactured using angle ply laminate techniques or a combination of cross and angle ply techniques, as well considering the loading response of the composite structure to be identical to that of structures made of traditional materials, has made the use of, and the results obtained by using such analysis techniques and conditions questionable. Hence, the main objective of this paper is to highlight and present the results obtained when analyzing and modeling symmetrical conditions as applied to commercial materials and that applied to composite laminates. A comparison case study is carried out using cross-ply and angle-ply laminates which concluded that, if the composition of laminate structure is pure cross-ply, the FEA is well suited for predicting the mechanical response of composite structure using principle of symmetry condition. On the other hand that is not the case for angle-ply or mixed-ply laminate structure.
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Mathison, S. R., M. J. Pindera, and C. T. Herakovich. "Nonlinear Response of Resin Matrix Laminates Using Endochronic Theory." Journal of Engineering Materials and Technology 113, no. 4 (October 1, 1991): 449–55. http://dx.doi.org/10.1115/1.2904125.

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The nonlinear response of laminated, resin matrix fibrous composites is modeled using orthotropic endochronic theory. The theory is formulated in terms of elastic constants and endochronic parameters characterizing the linear and nonlinear response, respectively, of unidirectional composites. All constants and parameters can be determined from normal (tension and/or compression) and shear tests on unidirectional and off-axis specimens. The nonlinear constitutive response relations for the unidirectional lamina are presented and the procedure for determining constants and parameters from test is described. The results are then used to predict the nonlinear response of unidirectional laminae and angle-ply laminates. Comparison between theory and experiment for compression loading of AS4/3502 graphite-epoxy, angle-ply laminates shows excellent correlation.
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Wang, Yuan Ruo, and Tsu-Wei Chou. "Three-Dimensional Transient Interlaminar Thermal Stresses in Angle-Ply Composites." Journal of Applied Mechanics 56, no. 3 (September 1, 1989): 601–8. http://dx.doi.org/10.1115/1.3176134.

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This paper studies the three-dimensional transient interlaminar thermal stresses in elastic, angle-ply laminated composites due to sudden changes in the thermal boundary conditions. The transient temperature field and transient interlaminar thermal stresses of the laminate are obtained by solving the heat conduction equation and by a zeroth-order perturbation analysis of the equilibrium equations, respectively. Numerical results for a four-layer angle-ply laminate have shown that the interlaminar normal stress near the free edge is significantly higher than that in the interior region and it increases rapidly with the fiber volume fraction.
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Kim, K. S., and C. S. Hong. "Delamination Growth in Angle-Ply Laminated Composites." Journal of Composite Materials 20, no. 5 (September 1986): 423–38. http://dx.doi.org/10.1177/002199838602000502.

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Murakami, H. "A Mixture Theory for Wave Propagation in Angle-Ply Laminates, Part 1: Theory." Journal of Applied Mechanics 52, no. 2 (June 1, 1985): 331–37. http://dx.doi.org/10.1115/1.3169049.

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In an effort to construct a continuum model with microstructure for elastic angle-ply laminates, an asymptotic mixture theory with multiple scales is presented in this two-part paper. The theory, which is in the form of a binary mixture, can simulate wave propagation in linearly elastic laminated composites with orthotropic lamina. Reissner’s new variational principle has been adopted to avoid the numerous solution procedures of microstructure boundary value problems (MBVP’s), which are required to find mixture properties in terms of the geometrical and material properties of the two constituents of the composite. For the special case of isotropic lamina the variational approach yields the same results as those derived by the asymptotic mixture theory with multiple scales [10] which requires the solution of the MBVP’s. The advantage of the variational approach over the alternative is that it makes the application of the technique feasible to wave propagation in fiber-reinforced and particulate composites. The application of the mixture model to angle-ply laminates is deferred to the second part of the paper, which also contains a study of dispersion of time harmonic waves in angle-ply laminates.
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Wu, Mengjin, Ruosi Yan, Zhihui Xia, Bao Shi, Sainan Wei, Wei Zhang, and Lixia Jia. "Characterization of mechanical properties of stab-resistant angle-ply flexible composites." Journal of Engineered Fibers and Fabrics 15 (January 2020): 155892502093555. http://dx.doi.org/10.1177/1558925020935554.

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In this study, we fabricated para-aramid flexible angle-ply-laminated hybrid composites based on weft-knitted reinforcements. Here, four kinds of weft-knitted reinforcements with rib, interlock, punto di roma, and two-thread fleecy were prepared using para-aramid spun yarn. They were then compounded with silicone rubber and waterborne polyurethane–acrylate using the coating method. The layers were angle-plied to produce stab-resistant, weft-knitting-reinforced, flexible laminated hybrid composites. Tensile and tearing strengths of the para-aramid-knitted reinforcements were investigated. Relevant response analyses were chosen to evaluate the influence of three independent variables, including weft-knitted structures, matrix types, and ply orientations. The results showed that the mechanical properties of the composites were dependent on weft-knitted structures and matrix types. The fabric with high strength and the degree in approximate isotropy of stress in all composites was most suited for the reinforcement of the flexible stab-resistant composite. The optimum design with the best stab-resistant property was punto di roma/waterborne polyurethane–acrylate with a ply orientation angle of [0°/0°/0°/0°]. The interlaminar adhesion of flexible stab-resistant composite based on waterborne polyurethane–acrylate can be improved by increasing the surface roughness of fabric structure or modifying its surface.
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Kalita, Kanak, M. Ramachandran, Pramod Raichurkar, Sneha D. Mokal, and Salil Haldar. "Free Vibration Analysis of Laminated Composites by a Nine Node Isoparametric Plate Bending Element." Advanced Composites Letters 25, no. 5 (September 2016): 096369351602500. http://dx.doi.org/10.1177/096369351602500501.

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Composite laminates are being widely used in engineering industry primarily due to their high strength-to-weight ratio. Considerable research has been carried out to understand the static and dynamic behaviour of laminated composite plates. There is much demand for developing efficient finite element codes which can predict the dynamic responses of laminated structures at affordable computational cost. In this paper a nine node isoparametric plate bending element has been used for free vibration analysis of laminated composite plate. The first-order shear deformation theory (FSDT) has been incorporated in the element formulation. Composite plates with different side-to-thickness ratio (a/h), ply orientations and number of layers have been analysed. Based on comparison with literature data, we propose that the present formulation is capable of yielding highly accurate results. Laminated composites with central cut-outs are also studied. Novel data is reported for skew laminated composites. It is found that the natural frequency increases with the increase in skew angle (a) and decreases with increase in aspect ratio (b/a) and thickness (h).
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Dey, Sudip, and Amit Karmakar. "Effect of Location of Delamination on Free Vibration of Cross-Ply Conical Shells." Shock and Vibration 19, no. 4 (2012): 679–92. http://dx.doi.org/10.1155/2012/726986.

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Location of delamination is a triggering parameter for structural instability of laminated composites. In this paper, a finite element method is employed to determine the effects of location of delamination on free vibration characteristics of graphite-epoxy cross-ply composite pre-twisted shallow conical shells. The generalized dynamic equilibrium equation is derived from Lagrange's equation of motion neglecting Coriolis effect for moderate rotational speeds. The formulation is exercised by using an eight noded isoparametric plate bending element based on Mindlin's theory. Multi-point constraint algorithm is utilized to ensure the compatibility of deformation and equilibrium of resultant forces and moments at the delamination crack front. The standard eigen value problem is solved by applying the QR iteration algorithm. Finite element codes are developed to obtain the numerical results concerning the effects of location of delamination, twist angle and rotational speed on the natural frequencies of cross-ply composite shallow conical shells. The mode shapes are also depicted for a typical laminate configuration. Numerical results obtained from parametric studies of both symmetric and anti-symmetric cross-ply laminates are the first known non-dimensional natural frequencies for the type of analyses carried out here.
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Kanasogi, R. M., and M. C. Ray. "Active Constrained Layer Damping of Smart Skew Laminated Composite Plates Using 1–3 Piezoelectric Composites." Journal of Composites 2013 (June 5, 2013): 1–17. http://dx.doi.org/10.1155/2013/824163.

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This paper deals with the analysis of active constrained layer damping (ACLD) of smart skew laminated composite plates. The constraining layer of the ACLD treatment is composed of the vertically/obliquely reinforced 1–3 piezoelectric composites (PZCs). A finite element model has been developed for accomplishing the task of the active constrained layer damping of skew laminated symmetric and antisymmetric cross-ply and antisymmetric angle-ply composite plates integrated with the patches of such ACLD treatment. Both in-plane and out-of-plane actuations by the constraining layer of the ACLD treatment have been utilized for deriving the finite element model. The analysis revealed that the vertical actuation dominates over the in-plane actuation. Particular emphasis has been placed on investigating the performance of the patches when the orientation angle of the piezoelectric fibers of the constraining layer is varied in the two mutually orthogonal vertical planes. Also, the effects of varying the skew angle of the substrate laminated composite plates and different boundary conditions on the performance of the patches have been studied. The analysis reveals that the vertically and the obliquely reinforced 1–3 PZC materials should be used for achieving the best control authority of ACLD treatment, as the boundary conditions of the smart skew laminated composite plates are simply supported and clamped-clamped, respectively.
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Valot, E., P. Vannucci, and G. Verchery. "Complete In-plane Elastic Characterisation under Tensile Tests of Angle-Ply Laminates Composed of Polymer-Matrix Layers." Polymers and Polymer Composites 10, no. 7 (October 2002): 483–92. http://dx.doi.org/10.1177/096739110201000701.

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In this paper we present a new strategy to completely characterise the in-plane elastic properties of a large range of angle-ply laminates using only unidirectional tests. We consider laminates having the same number of identical plies in the α and – α directions. This new method uses some preceding results found by Verchery for orthotropic laminates, namely the conditions of existence of a specific direction ω, in which the shear-extension coupling is null. The characterisation of the laminate is then made using the results of three tensile tests: two in the orthotropy axes, and the third one in the ω direction, in order to have always a pure one-dimensional state of stress. We show that for the most common unidirectional fibre-reinforced materials, the angle ω is, in most cases, close to the α direction of the fibres. This result permits a complete experimental characterisation of the laminate, which then does not need any a priori knowledge of the elastic properties of the elementary layer. In addition, it provides a simple method to verify the predictions of the laminate behaviour obtained by the Classical Laminated Plate Theory (CLPT) when the elementary layer is completely known. The paper ends with numerical examples and with the results of some experimental tests.
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Dissertations / Theses on the topic "Angle-ply laminated composites"

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Timarci, Taner. "Vibrations of composite laminated cylindrical shells." Thesis, University of Nottingham, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.283227.

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Khatibzadeh, Marziyeh. "The strength of angle-ply laminates and composites with misaligned fibres." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1997. http://www.collectionscanada.ca/obj/s4/f2/dsk2/ftp01/MQ29381.pdf.

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Majeed, Majed A. "Deformations of In-plane Loaded Unsymmetrically Laminated Composite Plates." Diss., Virginia Tech, 2005. http://hdl.handle.net/10919/26309.

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This study focuses on the response of flat unsymmetric laminates to an inplane compressive loading that for symmetric laminates are of sufficient magnitude to cause bifurcation buckling, postbuckling, and secondary buckling behavior. In particular, the purpose of this study is to investigate whether or not the concept of bifurcation buckling is applicable to unsymmetric laminates. Past work by other researchers has suggested that such a concept is applicable for certain boundary conditions. The study also has as an objective the determination of the response of flat unsymmetric laminates if bifurcation buckling does not occur. The finite-element program ABAQUS is used to obtain results, and a portion of the study is devoted to becoming familiar with the way ABAQUS handles such highly geometrically nonlinear problems, particularly for composite materials and particularly when instabilities and dynamic behavior are involved. Familiarity with the problem, in general, and with the use of ABAQUS, in particular, is partially gained by considering semi-infinite unsymmetrically laminated cross- and angle-ply plates, a one-dimensional problem that can be solve in closed form and with ABAQUS by making the appropriate approximations for the infinite geometry. In this portion of the study it is found that semi-infinite cross-ply laminates with clamped boundary conditions and semi-infinite angle-ply plates with simple-support boundary conditions remain flat under a compressive load until the load magnitude reaches a certain level, at which time the out-of-plane deflection become indeterminate, essentially an eigenvalue problem as encountered with classic bifurcation buckling analyses. Obviously, a linear analysis of such problems would not reveal this behavior and, in fact, there are other revealed significant differences between the predictions of linear and nonlinear analyses. Transversely-loaded and inplane-loaded finite isotropic plates are studied by way of semi-closed form Rayleigh-Ritz-based solutions and ABAQUS in a step to approaching the problem with unsymmetric laminates. A method to investigate the unloading behavior of postbuckled finite isotropic plates is developed that reveal multiple plate configurations in the postbuckled region of the response, and this method is then extended to the study of finite inplane-loaded unsymmetric laminates. To that end, two specific laminates, a symmetric and an unsymmetric cross-ply laminates, and a variety of boundary conditions are used to study the response of inplane-loaded unsymmetric laminates. The symmetric laminate is included to provide a familiar baseline case and a means of comparison. Plates with all four edges clamped and a variety of inplane boundary conditions are studied. Of course the symmetric cross-ply laminate exhibits bifurcation behavior, and when the tangential displacement on the loaded edges and the normal displacement on the unloaded edges are restrained, secondary buckling behavior occurs. For the unsymmetric cross-ply laminate, bifurcation buckling behavior does not occur unless the tangential displacement on the loaded edges and the normal displacement on the unloaded edges are restrained, or the tangential displacement on the loaded edges and the normal displacement on the unloaded edges are free. If either of these conditions are not satisfied, the unsymmetric cross-ply laminate exhibits what could be termed 'near-bifurcation' behavior. In all cases rather complex behavior occurs for high levels of inplane load, including asymmetric postbuckling and secondary buckling behavior. For clamped loaded edges and simply-supported unloaded edges, bifurcation buckling behavior does not occur unless the tangential displacement on the loaded edges and the normal displacement on the unloaded edges are restrained. For this case, rather unusual asymmetric bifurcation and associated limit point behavior occur, as well as secondary buckling. This is a very interesting boundary condition case and is studied further for other unsymmetric cross-ply laminates, including the use of a Rayleigh-Ritz-based solution in attempt to quantify the problem parameters responsible for the asymmetric response. The overall results of the study have led to an increased understanding of the role of laminate asymmetry and boundary conditions on the potential for bifurcation behavior, on the response of the laminate for loads beyond that level.
Ph. D.
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Burns, Stephen W. "Compressive failure of notched angle-ply composite laminates: three-dimensional finite element analysis and experiment." Thesis, Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/104298.

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Mathison, Steve Richard. "Nonlinear analysis for the response and failure of compression- loaded angle-ply laminates with a hole." Thesis, Virginia Tech, 1987. http://hdl.handle.net/10919/45819.

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The objective of this study was to determine the effect of nonlinear material behavior on the response and failure of unnotched and notched angle-ply laminates under uniaxial compressive loading. The endochronic theory was chosen as the constitutive theory to model the AS4/3502 graphite-epoxy material system.

Three-dimensional finite element analysis incorporating the endochronic theory was used to determine the stresses and strains in the laminates. An incremental/iterative initial strain algorithm was used in the finite element program. To increase computational efficiency, a 180° rotational symmetry relationship was utilized and the finite element program was vectorized to run on a super computer. Laminate response was compared to experiment revealing excellent agreement for both the unnotched and notched angle-ply laminates. Predicted stresses in the region of the hole were examined and are presented, comparing linear elastic analysis to the inelastic endochronic theory analysis.

A failure analysis of the unnotched and notched laminates was performed using the quadratic tensor polynomial. Predicted fracture loads compared well with experiment for the unnotched laminates, but were very conservative in comparison with experiments for the notched laminates.


Master of Science
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Wagih, Abdallah Abdel Hady Ahmed. "Response of composite laminates under out-of-plane loading." Doctoral thesis, Universitat de Girona, 2018. http://hdl.handle.net/10803/620794.

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The objective of the thesis is to provide scaling tool predicting the response of composite structures under out-of-plane loading by testing small coupons. This global objective cannot be achieved without understanding the damage mechanisms and their sequences in composite laminates under out-of-plane loading. The objective of the thesis is achieved by considering three different sub-objectives. The first sub-objective is focusing on understanding the damage mechanisms and their sequences in composite laminates made of different ply thicknesses. The second sub-objective focuses on understanding the influence of the laminate design parameters, mismatch angle between plies and ply thickness, on the response of composite laminates under out-of-plane loading.In the third sub-objective, the contact problem of a stiff spherical indenter with a composite plate was simulated with a 2D axisymmetric model implemented on a commercial software.Finally, the scaling tool to predict the response of composite structures under out-ofplane loading is implemented in two steps
El objectiu d’aquesta tesi és el d’aconseguir una eina d’escalat fiable per a predir la resposta d’estructures de compòsit sota càrregues fora del pla mitjançant l’assaig de petites provetes. L’objectiu s’ha assolit considerant tres sub-objectius diferents. El primer sub-objectiu es centra en comprendre els mecanismes de dany i la seva seqüència en laminats de material compost fets amb làmines de diferent gruix.El segon sub-objectiu es centra en comprendre la influència dels paràmetres de disseny dels laminats, angle de desfasament entre capes i gruix de capa, en la resposta de compòsits laminats a càrregues fora del pla.En el tercer sub-objectiu es va simular el problema del contacte entre un indentador esfèric rígid i una placa de compòsit mitjançant un model axisimètric 2D implementat en un programari comercial.Finalment, l’eina d’escalat per a la predicció de la resposta d’estructures de material compost sota càrregues fora del pla s’implementa en dos passos
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Gnoli, Daniel. "Studio di profili tubolari in FRP: omogeneizzazione e modello trave equivalente." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Il seguente elaborato di tesi nasce con lo scopo di valorizzare l’utilizzo di tubi cavi in materiale composito, principalmente in ambito offshore, poiché caratterizzati da un’elevata efficienza strutturale e soprattutto da un eccellente resistenza alla corrosione. In merito a questo, si fornisce un metodo alternativo atto a velocizzare e permettere la progettazione di essi senza l’utilizzo di un laborioso modello 3D agli elementi finiti. Lo studio effettuato, oltre ad ampliare la conoscenza sul comportamento dei tubolari, consiste nel calcolare i coefficienti della matrice di rigidezza tramite una semplice formulazione analitica. Quest’ultima, valida per la maggior parte degli schemi di laminazione, sfrutta il metodo di omogeneizzazione della sezione di Sun et al. e la formulazione di Eulero-Bernoulli per ottenere i coefficienti di rigidezza di un materiale isotropo. Si è constatato come attraverso il modello equivalente beam-frame 3D conseguito sia possibile ottenere valori dei coefficienti della matrice di rigidezza con errori minori del 5% rispetto a quelli definiti tramite il modello shell 3D agli elementi finiti. Per lo studio affrontato si sono considerati i laminati Cross-Ply, Angle-Ply, bilanciati e non, e laminati con configurazione particolare, ovvero, laminati con variazione angolare delle fibre tra gli strati molto piccola e laminati con materiali compositi fortemente ortotropi tali da generare valori di poisson negativi o molto elevati a seconda dello schema di laminazione. Si è cercato, infine, di dare una visione più concreta dell’argomento trattato illustrando un impiego plausibile, ovvero quello del ponteggio in ambito offshore. Grazie alla Gruppo Cosmi S.p.a. e alla Seico compositi S.r.l. è stato possibile effettuare un confronto a livello economico e gestionale tra i "tubi innocenti" tradizionali in acciaio e quelli in materiale composito valorizzando l’utilizzo di quest’ultimi.
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Zhang, D., J. Ye, and Dennis Lam. "Free-Edge and Ply Cracking Effect in Angle-Ply Laminated Composites Subjected to In-Plane Loads." 2007. http://hdl.handle.net/10454/5890.

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This paper presents a semianalytical method for the prediction of interlaminar stresses and displacements near the free edges and ply cracks in general angle-ply laminates subjected to biaxial extensions and/or in plane shear deformation. The method is based on a state space representation of the three-dimensional equations of elasticity. Numerical solutions are obtained by using layer refinement in the through thickness direction and Fourier series expansion in the other directions. By this approach, an angle-ply laminate may be composed of an arbitrary number of monoclinic layers and each layer may have different material property and thickness. This method guarantees continuous fields of all interlaminar stresses across interfaces between material layers. Numerical results are compared with those obtained from other methods. It is found that the theory provides a satisfactory approximation to the stress singularities near the free edges and ply cracks. Numerical solutions for antisymmetric laminates under extension and general laminates under shearing are new in the literature and can be used as benchmarks for validating new models.
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Lin, Pei Kuang, and 林培寬. "Failure Modes Analysis of Composites Angle Ply Laminates." Thesis, 1996. http://ndltd.ncl.edu.tw/handle/00427064632565743782.

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Books on the topic "Angle-ply laminated composites"

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Kellas, Sotiris. Scaling effects in angle-ply laminates. Hampton, Va: Langley Research Center, 1992.

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Daniel, Isaac M. High strain rate properties of angle-ply composite laminates. [Washington, DC]: National Aeronautics and Space Administration, 1991.

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Khatibzadeh, Marziyeh. The strength of angle-ply laminates and composites with misaligned fibres. Ottawa: National Library of Canada = Bibliothèque nationale du Canada, 1999.

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John, Morton, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Scaling effects in angle-ply laminates. [Washington, D.C.?]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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John, Morton, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Scaling effects in angle-ply laminates. [Washington, D.C.?]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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United States. Army Aviation Research and Technology Activity. and Langley Research Center, eds. Local delamination in laminates with angle ply matrix cracks. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

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Book chapters on the topic "Angle-ply laminated composites"

1

Filho, Antonio Carvalho. "Total Strains in ± 55 Angle-Ply Laminates." In Durability of Industrial Composites, 75–84. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor &: CRC Press, 2018. http://dx.doi.org/10.1201/9780429441813-6.

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Filho, Antonio Carvalho. "Total Strains in ± 70 Angle-Ply Laminates." In Durability of Industrial Composites, 85–101. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor &: CRC Press, 2018. http://dx.doi.org/10.1201/9780429441813-7.

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Tauchert, T. R., and N. N. Huang. "Thermal Buckling of Symmetric Angle-ply Laminated Plates." In Composite Structures 4, 424–35. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3455-9_33.

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Reiss, Robert, and S. Ramachandran. "Maximum Frequency Design of Symmetric Angle-ply Laminates." In Composite Structures 4, 476–87. Dordrecht: Springer Netherlands, 1987. http://dx.doi.org/10.1007/978-94-009-3455-9_37.

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Hirano, Yoichi. "Extension-Twist Coupling of Two-Layered Angle-Ply Laminates." In Composite Structures, 445–57. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3662-4_34.

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Werner, B. T., J. D. Schaefer, and I. M. Daniel. "Deformation and Failure of Angle-Ply Composite Laminates." In Experimental Mechanics of Composite, Hybrid, and Multifunctional Materials, Volume 6, 167–71. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-00873-8_19.

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Zhu, Chendi, and Jian Yang. "Vibration Analysis of Harmonically Excited Antisymmetric Cross-Ply and Angle-Ply Laminated Composite Plates." In Vibration Engineering for a Sustainable Future, 129–35. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-48153-7_17.

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Vassilopoulos, Anastasios P. "Creep/fatigue/relaxation of angle-ply GFRP composite laminates." In Fatigue Life Prediction of Composites and Composite Structures, 99–134. Elsevier, 2020. http://dx.doi.org/10.1016/b978-0-08-102575-8.00004-8.

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Khalil, M., E. Bakhiet, and A. El-Zoghby. "ON SIMULTANEOUS FAILURE OF CROSS-PLY AND ANGLE-PLY COMPOSITE LAMINATES." In Current Advances in Mechanical Design and Production VII, 281–92. Elsevier, 2000. http://dx.doi.org/10.1016/b978-008043711-8/50029-5.

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10

Kashtalyan, M., and C. Soutis. "Analysis of delamination in laminates with angle-ply matrix cracks." In Structural Integrity and Durability of Advanced Composites, 479–512. Elsevier, 2015. http://dx.doi.org/10.1016/b978-0-08-100137-0.00019-5.

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Conference papers on the topic "Angle-ply laminated composites"

1

Aly-Hassan, Mohamed S., Yuka Kobayashi, Asami Nakai, and Hiroyuki Hamada. "Tensile and Shear Properties of Biaxial Flat Braided Carbon/Epoxy Composites With Dispersed Carbon Nanofibers in the Matrix." In ASME 2008 2nd Multifunctional Nanocomposites and Nanomaterials International Conference. ASMEDC, 2008. http://dx.doi.org/10.1115/mn2008-47057.

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In laminated flat braided composites there are no fibers through the thickness direction except at the edges due to the fiber continuity of the braiding technique. A delamination along the interlaminar planes can be propagated because of the lack of fibers in the Z- or third-direction to the composite. The delamination initiates essentially as a result of arising the stresses concentrations around the transverse or matrix cracks that appear due to the mismatch of the thermal expansion coefficients of the fibers and matrix during the fabrication process. The delamination renders low interlaminar composite properties and represents a fundamental weakness of laminated flat braided composites especially with increasing the braiding angle, and thus minimizes the shear stress transfer. In this research, laminated flat braided carbon fabrics were performed via flattening tubular braided fabrics with braiding angle of ±45° by applying carefully compressive loads laterally on the tubular fabrics. Then, carbon fiber reinforced epoxy matrix composites were fabricated from the above-mentioned biaxial fabrics with and without uniformly dispersed carbon nanofibers throughout the epoxy matrix. Three loading percentages of carbon nanofibers (specifically, 0.5, 1, and 2 wt%) were dispersed in the matrix of the composites to enhance the matrix and interlaminar/inter-ply properties. The influence of matrix and interlaminar properties improvements on the in-plane tensile and shear response of the laminated flat braided composites was clarified via conducting of ±45° laminates tensile tests. The experimental results of tensile tests revealed that the tensile and in-plane shear properties as well as the fracture behavior of the composites are substantially influenced by the incorporation of the dispersed carbon nanofibers in the matrix of the composites. A pulsed thermography technique was used to inspect the occurrence of the delamination after the fracture under tensile loadings. The thermal wave image and logarithmic temperature-time curves of the pulsed thermography inspection illustrated that the composites with dispersed carbon nanofibers rendered higher interlaminar properties than that of composites without nanofibers. The main conclusion of this research can be summarized that dispersion of carbon nanofibers through the epoxy matrix of laminated flat braided composites is not only enhanced the matrix properties but also improved the interphase morphology between the composite plies that maximized the stress transfer of the composites. In other words, the fabricated braided composites with braiding angle of ±45° are predominantly by both of matrix and interlaminar properties.
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Aly-Hassan, Mohamed S., Yuka Kobayashi, Asami Nakai, Hiroyuki Hamada, and Hiroshi Hatta. "Mechanical Properties and Fracture Mechanism of CF Flat Braided Composites With Dispersed Carbon Nanofibers in the Matrix." In ASME 2008 International Manufacturing Science and Engineering Conference collocated with the 3rd JSME/ASME International Conference on Materials and Processing. ASMEDC, 2008. http://dx.doi.org/10.1115/msec_icmp2008-72017.

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In this research, laminated flat braided carbon fabrics were performed via flattening tubular braided fabrics with braiding angle of ±45° by applying carefully compressive loads laterally on the tubular fabrics. Then, carbon fiber reinforced epoxy matrix composites were fabricated from the above-mentioned biaxial fabrics with and without uniformly dispersed carbon nanofibers throughout the epoxy matrix. Three loading percentages of carbon nanofibers (specifically, 0.5, 1, and 2 wt%) were dispersed in the matrix of the composites to enhance the matrix and interlaminar/inter-ply properties. The influence of matrix and interlaminar properties improvements on the in-plane tensile and shear response of the laminated flat braided composites was clarified via conducting of ±45° laminates tensile tests. The experimental results of tensile tests revealed that the tensile and in-plane shear properties as well as the fracture behavior of the composites are substantially influenced by the incorporation of the dispersed carbon nanofibers in the matrix of the composites. A pulsed thermography technique was used to inspect the occurrence of the delamination after the fracture under tensile loadings. The thermal wave image and logarithmic temperature-time curves of the pulsed thermography inspection illustrated that the composites with dispersed carbon nanofibers rendered higher interlaminar properties than that of composites without nanofibers. The main conclusion of this research can be summarized that dispersion of carbon nanofibers through the epoxy matrix of laminated flat braided composites not only enhanced the matrix properties but also improved the interphase morphology between the composite plies that maximized the stress transfer of the composites.
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3

Ameri Sianaki, Abolfazl, Brian Evans, Vamegh Rasouli, Reem Roufail, and Gordon Stewart. "Effect of Embedded Electric Sensor on the Structural Strength of Filament Wound Hybrid Composite." In ASME 2014 33rd International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/omae2014-23069.

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Filament wound composites (FWC) consist of multiple layers of carbon/glass fibres within an epoxy matrix at different angles of orientation to achieve required mechanical properties. The type of hybrid composite and method of fabrication may be tailored to develop a smart pipe with embedded sensors for use in mineral exploration drill pipe applications. Experimental work and numerical simulations were performed in order to understand the effect of the filament angle-ply and how embedded sensors altered the overall mechanical structure strength of the angle-ply composite. Numerical analysis was performed using Hypersizer, to understand the stress distribution on each of the laminated layers, their angles, and the presence of a sensor on the strength of the composite’s structure. The experimental work was carried out to validate the numerical analysis results. Experiments on two specimens are reported in this study, being with and without an embedded sensor. Eight plies were fabricated with the characteristic angle-ply of filament, wound in a rhomboid pattern. Due to the electrical conductivity of carbon fibre, the sensors’ performance was anticipated to deteriorate. Consequently a hybrid structure was designed. Glass fibre was wrapped around the sensors for isolation and the glass fibre, along with the sensors were then embedded in the carbon fibre filament wound structure. The fabricated hybrid specimens were then subjected to simple tensile tests in the lab. The mechanical strength of both specimens, with and without sensors, was compared to determine the effect of embedding the sensor within this hybrid composite.
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Luersen, M. A., C. A. Steeves, and P. B. Nair. "Optimisation of a Laminated Composite Cylindrical Shell With Curvilinear Fibre Paths Using a Surrogate-Based Approach." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-36285.

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Conventional design and manufacturing techniques of fibre-reinforced laminated materials keep the fibre orientation angle constant within each ply. However, with the development of advanced tow-placement technology it is now feasible to produce composites with curved fibres. This offers more flexibility to tailor the mechanical properties and improve the performance of laminated structures. In this paper, fibre path optimisation of a laminated cylindrical shell is studied. Curvilinear variations for the fibre orientations are adopted in the circumferential and longitudinal directions of the shell. In order to reduce the computational cost a surrogate-based optimisation strategy is proposed to pursue the optimum design. The laminated shell is subjected to bending and torsion loads and the maximum displacement magnitude is minimised while a constraint on the buckling load is imposed. Numerical studies are presented for two cases. First, only circumferential variation in the fibre orientations is considered. Then, circumferential and longitudinal variations are assumed.
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Guo, Xiang-Ying, Wei Zhang, and Qian Wang. "Nonlinear Vibration Response Analysis on a Composite Plate Reinforced With Carbon Nanotubes." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-85856.

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In order to compare nonlinear vibration response of the different enabled materials in the matrix of composites, the nonlinear vibrations of a composite plate reinforced with carbon nanotubes (CNT) are studied. In this paper, the carbon nanotubes are supposed to be long fibers. The nonlinear governing partial differential equations of motion for the composite rectangular thin plate are derived by using the Reddy’s third-order shear deformation plate theory, the von Karman type equation and the Hamilton’s principle. Then, the governing equations get reduced to ordinary differential equations in thickness direction with variable coefficients and these are solved by the Galerkin method. The case of 1:1 internal resonance is considered. The asymptotic perturbation method is employed to obtain the four-dimensional averaged equations. The numerical method is used to investigate the periodic and chaotic motions of the composite rectangular thin plate reinforced with carbon nanotubes. The results of numerical simulation demonstrate that there exist different kinds of periodic and chaotic motions of the composite plate under certain conditions. At last, the nonlinear vibration responses of the plate are compared with the same responses of angle-ply composite laminated plates.
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Vignoli, Lucas L., and Jaime T. P. de Castro. "NOTCHED STRENGTH OF SYMMETRIC ANGLE-PLY LAMINATES." In Brazilian Conference on Composite Materials. Pontifícia Universidade Católica do Rio de Janeiro, 2018. http://dx.doi.org/10.21452/bccm4.2018.03.03.

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7

Chuang, Shui-Nan. "Probabilistic Analysis for the Mechanical Properties of Cross-Ply Fiber-Reinforced Composite Laminate." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-13060.

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A probabilistic micromechanics model had been developed for the unidirectional fiber-reinforced composite material design screening. In which, we used the predicted mechanical properties of IM-7 carbon fiber from the existing IM-7/5250-4 composite material system together with the observed 977-3 matrix mechanical properties to predict the probability density functions for the mechanical properties of IM-7/977-3 unidirectional composite. To include the material design in the structural design process, we had extended the probabilistic analysis to predict the probability density functions for the off-axis mechanical properties. The angle-ply and cross-ply laminates have been used extensively in aerospace structural designs. It is logical to extend the probabilistic analysis to predict the probability density functions for the mechanical properties of the laminated composite. We had provided the probabilistic analysis for a symmetric regular angle-ply laminate of IM-7/5250-4 composite laminate. In this report, we will focus on the probabilistic analysis of symmetric and anti-symmetric regular cross-ply laminates of IM-7/5250-4 fiber-reinforced composite with odd-number plies parallel to and even-number plies perpendicular to the laminate principal axes. These probabilistic micromechanics models provide a design-screening tool to help material producers to eliminate the unnecessary time-consuming and costly material fabrications and to reduce the numbers of testing to a minimum but enough to verify the model prediction. They also provide a structural analysis tool to help the structural designer to manage the structural and material uncertainties during the structural design process. And consequently, it provides a means to accelerate the insertion of materials into AF productions.
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Haynes, Robert A., and Erian A. Armanios. "Hygrothermally Stable Extension-Twist Coupled Laminates With Bending-Twist Coupling." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-40014.

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The necessary and sufficient conditions for hygrothermal curvature stability of laminated composite plates have been derived in a prior publication and shown to be material independent. From within these conditions, various couplings are being investigated to determine any improvements over previously known optima. Extension-twist and bending-twist coupling have been investigated in previous work, and significant improvements over the previous state-of-the-art are demonstrated. In this work, the combined effect of extension-twist and bending-twist couplings is investigated to determine the level of twist achievable with a single laminate. Hygrothermal stability is taken to be a constraint. Results for laminates consisting of five through ten plies are presented. A Monte Carlo simulation investigates the robustness of the six-ply laminate to errors in ply angle stacking sequence.
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Yarborough, Christina N., Emily M. Childress, and Richard K. Kunz. "Shape Recovery and Mechanical Properties of Shape Memory Composites." In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-66477.

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As the need for deployable space structures continues to increase, a deeper understanding of the mechanical properties and the responses of shape memory composites will be needed. Past research efforts have been focused on woven (0/90) carbon fiber composites which limit the shape memory capabilities due to the brittle nature of this fiber. The current work not only utilizes a synthetic fiber which allowed for a greater versatility in the composite, but also investigates the effects of angle plies and fiber volume fraction on the attainable bend ratio of the laminates. Four types of laminates were made to test the effects of laminate thickness, angle-plies, and fiber volume fraction. The specimens from these laminates were placed in both bending and tensile tests to investigate the effect of the fiber reinforcement on the polymer’s stiffness, strength and recovery. Testing revealed that the thicker specimens demonstrated improved recovery over the thinner samples, and that the angle-ply specimens recovered better than the (0/90) specimens. The recovery of the (0/90) specimens was improved by increasing the fiber volume fraction. Most significantly, the specimens were able to achieve smaller bend ratios than in previous studies without fiber microbuckling or fiber breakage. The tensile test data revealed that the bending cycles had little to no affect on the material properties of the composite. Only the modulus of the 5-ply (0/90) was seen to slightly decrease as the bending ratio decreased.
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Xu, Jianlong, and Bhavani V. Sankar. "Prediction of Gas Permeability Through Multiple-Ply Composite Laminates." In ASME 2006 International Mechanical Engineering Congress and Exposition. ASMEDC, 2006. http://dx.doi.org/10.1115/imece2006-13690.

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Polymer matrix composites are candidate materials for cryogenic tanks for Crew Exploration Vehicles and Crew Launch Vehicles planned by NASA for future space missions. However gas leakage through microcracks and delaminations remains as a critical problem that needs to be solved. In the present work, gas permeability mechanism through multiple ply laminates is investigated. Different from the through matrix cracks in cross ply laminates, stitch cracks are observed in angle-ply laminates during experimentation. Stacking sequences [0/θn/90]s are investigated. From experimental observations presented in the literature, stitch cracks seem to develop in angle plies depending on the value of θ and n. A representative volume element (RVE) is analyzed by three-dimensional finite element method (FEM). Two methods are used to calculate the energy release rate: three-dimensional J-integral by ABAQUS 6.5™ and strain energy difference of RVEs before and after crack propagation. Based on energy release rate, the mechanisms and other parameters that control the creation and propagation of stitch cracks are investigated. The results will lead to the development of a relation between loads and the number of stitch cracks and their lengths. The permeation model is based on Darcy's law for porous materials. By integrating Darcy's law in the thickness direction of the composite laminate, the gas permeability can finally be expressed in terms of crack densities and crack opening displacements (COD). Three-dimensional FE analyses will be performed to find out COD for a given crack density and crack length. The results for gas permeability obtained through the simulations will be compared to the experimental results of cross ply laminates from previous work to understand the effects of laminate configuration on gas permeability.
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Reports on the topic "Angle-ply laminated composites"

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Hoppel, Christopher P., and Steven J. De Teresa. Effect of an Angle-Ply Orientation on Compression Strength of Composite Laminates. Fort Belvoir, VA: Defense Technical Information Center, June 1999. http://dx.doi.org/10.21236/ada368034.

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