Three-Dimensional Effective Moduli of Symmetric Laminates

Chen, Hongji; Tsai, Stephen W.

doi:10.1177/002199839603000803

Cited by 19 publications

(11 citation statements)

References 5 publications

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“…Therefore, the effective engineering constants are usually used for the convenience of engineers in describing the mechanical behavior of the laminates. Sun et al [ 36 ] and Chen et al [ 62 ] presented a model for EPR for general thick laminates. However, only the extensional response was taken into consideration while the bending and bending-extension coupling characteristics of the laminates were neglected.…”

Section: Design Of Hybrid Laminate With Nprmentioning

confidence: 99%

Geometric Non-Linear Analysis of Auxetic Hybrid Laminated Beams Containing CNT Reinforced Composite Materials

et al. 2020

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In the current work, a novel hybrid laminate with negative Poisson’s ratio (NPR) is developed by considering auxetic laminate which is composed of carbon nanotube-reinforced composite (CNTRC) and fiber-reinforced composite (FRC) materials. The maximum magnitude of out-of-plane NPR is identified in the case of (20 F/20 C/−20 C/20 C) S laminate as well. Meanwhile, a method for the geometric non-linear analysis of hybrid laminated beam with NPR including the non-linear bending, free, and forced vibrations is proposed. The beam deformation is modeled by combining higher-order shear-deformation theory (HSDT) and large deflection theory. Based on a two-step perturbation approach, the asymptotic solutions of the governing equations are obtained to capture the linear and non-linear frequencies and load-deflection curves. Moreover, a two-step perturbation methodology in conjunction with fourth-order Runge–Kutta method is employed to solve the forced-vibration problem. Several key factors, such as CNT distribution, variations in the elastic foundation, and thermal stress, are considered in the exhaustive analysis. Theoretical results for some particular cases are given to examine the geometric non-linearity behavior of hybrid beam with NPR as well as positive Poisson’s ratio (PPR).

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Section: Design Of Hybrid Laminate With Nprmentioning

confidence: 99%

Geometric Non-Linear Analysis of Auxetic Hybrid Laminated Beams Containing CNT Reinforced Composite Materials

et al. 2020

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“…The 3d laminate model used is as defined in Chen, 1996 . Using the equations below, the 3D stiffness matrix of the whole laminate could be derived based on the stiffness matrix of the contributing laminas.…”

Section: D Modelmentioning

confidence: 99%

Prediction of Shape Distortions in Composite Wing Structures

makinde

Faria

Donadon

2018

Lat. Am. j. solids struct.

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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 model originally proposed by Svanberg and Holmberg is employed to predict the warpage of a wing planform. The model takes into account important mechanisms such as thermal expansion, resin shrinkage and frozen-in strains developed during curing cycles. The model was implemented into ABAQUS Finite Element code as a user subroutine UMAT. The macromechanical properties of each composite layer were predicted using a micromechanics based approach, implemented into MATLAB. Results show that wings with cross ply laminates with reducing thickness along the span experienced more warpage than quasi-isotropic laminates. Furthermore, for wings with equal thickness along the span, the results show that the quasi-isotropic laminates experienced more warpage than cross ply laminates. Lastly, the results show that wings with progressively reducing thickness experience twist that is varying from the wing root to the wing tip while wings with a constant thickness experience twist mainly at the centre of the wing

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“…For a symmetric laminate, the constitutive relationship when only thermal stresses are considered is given by (6) where ε xx , ε yy , and ε zz are the strains due to the temperature change; e ij C is the equivalent stiffness of the laminate [16]; and T xx , T yy , and T zz are given by:…”

Section: Spring-in Modelingmentioning

confidence: 99%

Sensitivity Analysis for the Spring-in of Composite Shells

Dong

2011

Advanced Composites Letters

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Composite materials are a class of engineering materials widely used in a wide range of industries. Spring-in is a common dimensional variation of composite shells. It is well known that spring-in is dependent on many factors e.g. the constituent properties and coefficients of thermal expansion (CTE). A sensitivity analysis on the spring-in is presented in this paper. The sensitivities of the spring-in to the constituent properties and CTE are studied by the Design of Experiments (DOE) and the Response Surface Method (RSM). It is shown that the spring-in is predominantly sensitive to the Poisson's ratio of the matrix and the transverse CTE of the fibres. The results can be used to estimate the uncertainty of the spring-in from the uncertainties of the constituent properties and CTE, which is potentially useful for the design of composite products with improved dimensional control.

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Three-Dimensional Effective Moduli of Symmetric Laminates

Cited by 19 publications

References 5 publications

Geometric Non-Linear Analysis of Auxetic Hybrid Laminated Beams Containing CNT Reinforced Composite Materials

Geometric Non-Linear Analysis of Auxetic Hybrid Laminated Beams Containing CNT Reinforced Composite Materials

Prediction of Shape Distortions in Composite Wing Structures

Sensitivity Analysis for the Spring-in of Composite Shells

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