Cross Ply
Mostrando 1-12 de 13 artigos, teses e dissertações.
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1. Prediction of Shape Distortions in Composite Wing Structures
Abstract Shape distortions and warpage are a major source of problems for composite manufacturers. These distortions are usually accompanied by built up residual stresses. They can deform a component so that it becomes useless. It also has the capability to reduce the strength of the structure. In this paper, the three-dimensional version of the constitutive
Lat. Am. j. solids struct.. Publicado em: 29/10/2018
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2. Reduced Order Modeling of Composite Laminates Through Solid-Shell Coupling
ABSTRACT: Composite laminates display a complex mechanical behavior due to their microstructure, with a through-thickness variation of the displacement and stress fields that depends on the fiber orientation in each layer. Aiming to develop reduced-order numerical models mimicking the real response of composite structures, we investigated the capability and
J. Aerosp. Technol. Manag.. Publicado em: 26/06/2017
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3. Bending, Vibration and Buckling of Laminated Composite Plates Using a Simple Four Variable Plate Theory
Abstract In the present study, a simple trigonometric shear deformation theory is applied for the bending, buckling and free vibration of cross-ply laminated composite plates. The theory involves four unknown variables which are five in first order shear deformation theory or any other higher order theories. The in-plane displacement field uses sinusoidal fu
Lat. Am. j. solids struct.. Publicado em: 2016-03
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4. Effects of CFRP retrofit on impact response of shear-deficient scaled reinforced concrete beams
An experimental procedure is carried out to investigate response features of semi-deep reinforced concrete (RC) beams with dominant static shear failure subjected to low-velocity impact dynamic load both in intact and retrofitted cases. Built specimens have scaled geometry and material properties preserving physical similarity with full-scale members and are
Lat. Am. j. solids struct.. Publicado em: 2015-01
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5. Thermal flexural analysis of cross-ply laminated plates using trigonometric shear deformation theory
Thermal stresses and displacements for orthotropic, two-layer antisymmetric, and three-layer symmetric square cross-ply laminated plates subjected to nonlinear thermal load through the thickness of laminated plates are presented by using trigonometric shear deformation theory. The in-plane displacement field uses sinusoidal function in terms of thickness co-
Lat. Am. j. solids struct.. Publicado em: 2013-09
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6. Flexural analysis of cross-ply laminated beams using layerwise trigonometric shear deformation theory
In the present work, a layerwise trigonometric shear deformation theory is used for the analysis of two layered (90/0) cross ply laminated simply supported and fixed beams subjected to sinusoidal load. The displacement field of the present theory consists of trigonometric sine function in terms of thickness coordinate to take into account the effect of trans
Lat. Am. j. solids struct.. Publicado em: 2013-07
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7. Impact properties of aluminium - glass fiber reinforced plastics sandwich panels
Aluminium - glass fiber reinforced plastics (GFRP) sandwich panels are hybrid laminates consisting of GFRP bonded with thin aluminum sheets on either side. Such sandwich materials are increasingly used in airplane and automobile structures. Laminates with varying aluminium thickness fractions, fiber volume fractions and orientation in the layers of GFRP were
Materials Research. Publicado em: 27/03/2012
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8. Charpy impact toughness of conventional and advanced composite laminates for aircraft construction
A weight-based analysis was made of the translaminar Charpy impact toughness performance of conventional and advanced composite materials for aircraft fabrication. The materials were carbon-epoxy (C-Ep) and hybrid fiber-metal TiGr (Titanium-Graphite) laminates. 5 mm-thick three-point bend specimens were tested over a temperature range of -70 to 180 ºC to re
Materials Research. Publicado em: 2009
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9. Mechanical performance of carbon-epoxy laminates. Part II: quasi-static and fatigue tensile properties
In Part II of this work, quasi-static tensile properties of four aeronautical grade carbon-epoxy composite laminates, in both the as-received and pre-fatigued states, have been determined and compared. Quasi-static mechanical properties assessed were tensile strength and stiffness, tenacity (toughness) at the maximum load and for a 50% load drop-off. In gene
Materials Research. Publicado em: 2006-06
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10. Mechanical performance of carbon-epoxy laminates. Part I: quasi-static and impact bending properties
In Part I of this study, quasi-static and impact bending properties of four aeronautical grade carbon-epoxy laminates have been determined and compared. Materials tested were unidirectional cross-ply (tape) and bidirectional woven textile (fabric) carbon fiber lay-up architectures, impregnated with standard and rubber-toughened resins, respectively, giving r
Materials Research. Publicado em: 2006-06
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11. Influence of an odd structure in cross ply tires. / Influência da estrutura ímpar em pneus de lonas cruzadas (cross-ply).
The tire is the only bond between the vehicle and the ground, is it that transmits all the power and load, and guarantees the driven and conduction of the automobile. The resistant structure of a tire is one of the most important factors for the efficiency, type of application and security. Knowing these parameters is the primary condition to design a tire.
Publicado em: 2006
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12. Análise de falha em laminados cross-ply pelo método dos elementos finitos
Este trabalho trata do problema da determinacao das tensoes que surgem nas bordas livres de compositos laminados simetricos de fita unidirecional de carbono/epoxi sujeitos a uma extensao uniformelongitudinal e a um carregamento termico ocasionado pela temperaturade cura. Utilizou-se uma formulacao baseada no metodo dos elementos finitos que leva em conta um
IBICT - Instituto Brasileiro de Informação em Ciência e Tecnologia. Publicado em: 01/01/1995