• Title/Summary/Keyword: laminated shells

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Free Vibration of the Composite Laminated Cylindrical Shells Stiffened with the Axial Stiffeners (길이방향으로 보강된 복합재료 원통쉘의 자유진동)

  • Lee, Young-Shin;Kim, Young-Wann
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.20 no.7
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    • pp.2223-2233
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    • 1996
  • The analytical solutions for the free vibration of cross-ply laminated composite cyllindrical shell with axial stiffeners(stringers) are presented usint the energy method. The stiffeners are taken to be smeared over the surface of shell with the smeared stffener theory. The effect of the parameters such as the stacking sequences, the shell thichness, the shell radius-to stringer depth ratio, the stringer depth-to width ratio, the shell length-to radius ratio are studied. By comparison with the previously published experimental results and the analytical results for the stiffened isotropic cylindrical shell and the unstiffened orthotropic composite laminated cylindrical shell, it is shown that natural frequencies can be determined with adequate accuracy.

Analysis of impact response and damage in laminated composite cylindrical shells undergoing large deformations

  • Kumar, Surendra
    • Structural Engineering and Mechanics
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    • v.35 no.3
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    • pp.349-364
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    • 2010
  • The impact behaviour and the impact-induced damage in laminated composite cylindrical shell subjected to transverse impact by a foreign object are studied using three-dimensional non-linear transient dynamic finite element formulation. A layered version of 20 noded hexahedral element incorporating geometrical non-linearity is developed based on total Langragian approach. Non-linear system of equations resulting from non-linear strain displacement relation and non-linear contact loading are solved using Newton-Raphson incremental-iterative method. Some example problems of graphite/epoxy cylindrical shell panels are considered with variation of impactor and laminate parameters and influence of geometrical non-linear effect on the impact response and the resulting damage is investigated.

A Study on the Prediction of the Loaded Location of the Composite Laminated Shell by Using Neural Networks (신경회로망을 이용한 복합재료 원통쉘의 하중특성 추론에 관한 연구)

  • 명창문;이영신;류충현
    • Composites Research
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    • v.14 no.5
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    • pp.26-37
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    • 2001
  • After impact analysis of the composite cylindrical shells was performed. obtained outputs at 9 equally divided points of the shell were used as input patterns of the neural networks. Identification of impact loading characteristics was predicted simultaneously. Momentum backpropagation algorithm of neural networks which can modify the momentum coefficient and learning rate was developed and applied to identify the loading characteristics. Hidden layers of the backpropagation increased from 1 layer to 3 layers and trained the loading characteristics. Developed program with variable learning rate was converged close to real load characteristics under 1% error. Inverse engineering which identify the impact loading characteristics can be applicable to the composite laminated cylindrical shells with developed neural networks.

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Finite Element Analysis on Buckling Pressure of Composite Pressure Hull (복합재 내압선체의 좌굴압력에 관한 유한요소해석)

  • Cho, J.R.;Jung, H.Y.;Kwon, J.H.;Choi, J.H.;Cho, Y.S.
    • Proceedings of the Korean Society of Marine Engineers Conference
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    • 2005.11a
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    • pp.212-213
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    • 2005
  • The results of an experimental and analytical study of composite pressure hull on buckling pressure are presented for URN 300. We predicted the buckling and post buckling analysis of composite laminated cylindrical shell and panel under external compression by using ABAQUS/Standard[Ver 6.4]. To obtain nonlinear static equilibrium solutions for unstable problems, where the load-displacement response can exhibit the type of nonlinear buckling behavior, during periods of the response, the load and/or the displacement may decrease as the solution evolves, used the modified Riks method. Experiments were conducted to verify the validation of present analysis for cross-ply laminated shells. The shells considered in the study have four different lamination patterns, [${\pm}{\Theta}$/0/90]$_{14s}$,[${\pm}{\Theta}_{14}$/$0_{14}$/$90_{14}$],[${\pm}$45/0/90]$_{18s}$ and [/0/90]$_{18s}$. At the result of this study, the optimized ply orientation angle is $75^{\circ}$. The critical load from experiment is 69% of that of numerical analysis, because the fracture of matrix was generated before buckling. So URN 300 is not proper to use at the condition under high external pressure.

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Using 3D theory of elasticity for free vibration analysis of functionally graded laminated nanocomposite shells

  • R. Bina;M. Soltani Tehrani;A. Ahmadi;A. Ghanim Taki;R. Akbarian
    • Steel and Composite Structures
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    • v.52 no.4
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    • pp.487-499
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    • 2024
  • The primary objective of this study is to analyze the free vibration behavior of a sandwich cylindrical shell with a defective core and wavy carbon nanotube (CNT)-enhanced face sheets, utilizing the three-dimensional theory of elasticity. The intricate equations of motion for the structure are solved semi-analytically using the generalized differential quadrature method. The shell structure consists of a damaged isotropic core and two external face sheets. The distributions of CNTs are either functionally graded (FG) or uniform across the thickness, with their mechanical properties determined through an extended rule of mixture. In this research, the conventional theory regarding the mechanical effectiveness of a matrix embedding finite-length fibers has been enhanced by introducing tube-to-tube random contact. This enhancement explicitly addresses the progressive reduction in the tubes' effective aspect ratio as the filler content increases. The study investigates the influence of a damaged matrix, CNT distribution, volume fraction, aspect ratio, and waviness on the free vibration characteristics of the sandwich cylindrical shell with wavy CNT-reinforced face sheets. Unlike two-dimensional theories such as classical and the first shear deformation plate theories, this inquiry is grounded in the three-dimensional theory of elasticity, which comprehensively accounts for transverse normal deformations.

Refined nonlocal strain gradient theory for mechanical response of cosine FG-GRNC laminated nanoshells rested on elastic foundation

  • Mohamed A. Eltaher;A.A. Daikh;Amin Hamdi;Gamal S. Abdelhaffez; Azza M. Abdraboh
    • Advances in nano research
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    • v.17 no.4
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    • pp.335-350
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    • 2024
  • This paper investigates the mechanical behavior of a new type of functionally graded graphene-reinforced nanocomposite (FG-GRNC) doubly-curved laminated shells, referred to as cosine FG-GRNC. The study employs a refined higher-order shear deformation shell theory combined with a modified continuum nonlocal strain gradient theory. The effective Young's modulus of the GRNC shell in the thickness direction is determined using the modified Halpin-Tsai model, while Poisson's ratio and mass density are calculated using the rule of mixtures. The analysis includes two graphene-reinforced distribution patterns-FG-A CNRCs and FG-B CNRCs-along with uniform UD CNRCs. An enhanced Galerkin method is used to solve the governing equilibrium equations for the GRNC nanoshell, yielding closed-form solutions for bending deflection and critical buckling loads. The nanoshell is supported by an orthotropic elastic foundation characterized by three parameters. A detailed parametric analysis is performed to evaluate how factors such as the length scale parameter, nonlocal parameter, distribution pattern, GPL weight fraction, shell thickness, and shell geometry influence deflections and critical buckling loads.

On the fabrication of carbon fabric reinforced epoxy composite shell without joints and wrinkling

  • Vasanthanathan, A.;Nagaraj, P.;Muruganantham, B.
    • Steel and Composite Structures
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    • v.15 no.3
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    • pp.267-279
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    • 2013
  • This article describes a simple and cost effective fabrication procedure by using hand lay-up technique that is employed for the manufacturing of thin-walled axi-symmetric composite shell structures with carbon, glass and hybrid woven fabric composite materials. The hand lay-up technique is very commonly used in aerospace and marine industries for making the complicated shell structures. A generic fabrication procedure is presented in this paper aimed at manufacture of plain Carbon Fabric Reinforced Plastic (CFRP) and Glass Fabric Reinforced Plastic (GFRP) shells using hand lay-up process. This paper delivers a technical breakthrough in fabrication of composite shell structures without any joints and wrinkling. The manufacture of stiffened CFRP shells, laminated CFRP shells and hybrid (carbon/glass/epoxy) composite shells which are valued by the aerospace industry for their high strength-to-weight ratio under axial loading have also been addressed in this paper. A fabrication process document which describes the major processing steps of the composite shell manufacturing process has been presented in this paper. A study of microstructure of the glass fabric/epoxy composite, carbon fabric/epoxy composite and hybrid carbon/glass/fabric epoxy composites using Scanning Electron Microscope (SEM) has been also carried out in this paper.

Extension of a new tailoring optimisation technique to sandwich shells with laminated faces

  • Icardi, Ugo
    • Structural Engineering and Mechanics
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    • v.43 no.6
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    • pp.739-759
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    • 2012
  • The tailoring optimization technique recently developed by the author for improving structural response and energy absorption of composites is extended to sandwich shells using a previously developed zig-zag shell model with hierarchic representation of displacements. The in-plane variation of the stiffness properties of plies and the through-the thickness variation of the core properties are determined solving the Euler-Lagrange equations of an extremal problem in which the strain energy due to out-of-plane strains and stresses is minimised, while that due to their in-plane counterparts is maximised. In this way, the energy stored by unwanted out-of-plane modes involving weak properties is transferred to acceptable in-plane modes. As shown by the numerical applications, the critical interlaminar stress concentrations at the interfaces with the core are consistently reduced without any bending stiffness loss and the strength to debonding of faces from the core is improved. The structural model was recently developed by the author to accurately describe strain energy and interlaminar stresses from the constitutive equations. It a priori fulfills the displacement and stress contact conditions at the interfaces, considers a second order expansion of Lame's coefficients and a hierarchic representation that adapts to the variation of solutions. Its functional d.o.f. are the traditional mid-plane displacements and the shear rotations, so refinement implies no increase of the number of functional d.o.f. Sandwich shells are represented as multilayered shells made of layers with different thickness and material properties, the core being treated as a thick intermediate layer.

Relative static and dynamic performances of composite conoidal shell roofs

  • Bakshi, Kaustav;Chakravorty, Dipankar
    • Steel and Composite Structures
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    • v.15 no.4
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    • pp.379-397
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    • 2013
  • Conoidal shells are doubly curved stiff surfaces which are easy to cast and fabricate due to their singly ruled property. Application of laminated composites in fabrication of conoidal shells reduces gravity forces and mass induced forces compared to the isotropic constructions due to the high strength to weight ratio of the material. These light weight shells are preferred in the industry to cover large column free open spaces. To ensure design reliability under service conditions, detailed knowledge about different behavioral aspects of conoidal shell is necessary. Hence, in this paper, static bending, free and forced vibration responses of composite conoidal shells are studied. Lagrange's equation of motion is used in conjunction with Hamilton's principle to derive governing equations of the shell. A finite element code using eight noded curved quadratic isoparametric elements is developed to get the solutions. Uniformly distributed load for static bending analysis and three different load time histories for solution of forced vibration problems are considered. Eight different stacking sequences of graphite-epoxy composite and two different boundary conditions are taken up in the present study. The study shows that relative performances of different shell combinations in terms of static behaviour cannot provide an idea about how they will relatively behave under dynamic loads and also the fact that the points of occurrence of maximum static and dynamic displacement may not be same on a shell surface.

Dynamic Characteristics of Laminated Shells by Finite Strip Mehod (FSM에 의한 다층 원통쉘의 동적 특성에 관한 연구)

  • Park, Sungjin
    • Journal of the Society of Disaster Information
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    • v.11 no.4
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    • pp.534-541
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    • 2015
  • This study was presented how to interpret a laminated cylindrical shell having both ends supported condition are simple, and by identifying the three-dimensional stress characteristics. The governing equations were using the concept of finite element assuming the conversion into ordinary differential equations and partial differential equations by numerical analysis using the finite strip method. In particular, a function performed for the three-dimensional laminated cylindrical shell having a simple support condition were analyzed for the case composed of a specific function of the beam consisting of a trigonometric function. Layer material and layer thickness of a steel or concrete, the cylindrical length and the like by varying the parameters variously examine the effects of multi-layer cylindrical shell.