Vibration Analysis of Thickness- and Width-Tapered Laminated Composite Beams Using Hierarchical Finite Element Method PDF Download

Author: Mohammad Amin Fazili
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Lin Chen
Publisher:
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Category :
Languages : en
Pages :

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Author: Amit K. Nigam
Publisher:
ISBN:
Category : Composite construction
Languages : en
Pages : 0

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The conventional finite element formulation has limitations in performing the dynamic analysis of composite beams. The discretization necessary for obtaining solutions with acceptable accuracy in the determination of dynamic response parameters leads to discontinuities in stress and strain distributions. The hierarchical finite element formulation provides us with the advantages of using fewer elements and obtaining better accuracy in the calculation of natural frequencies, displacements and stresses. The hierarchical finite element formulation for uniform and variable-thickness composite beams is developed in the present work. Two sub-formulations of hierarchical finite element method viz. polynomial and trigonometric sub-formulations have been developed. The efficiency and accuracy of the developed formulation are established in comparison with closed-form solutions for uniform composite beams. The static response of uniform composite beams is evaluated using the hierarchical finite element method. The dynamic response of variable-thickness composite beams is calculated based on the developed formulation. A detailed parametric study encompassing the influences of boundary conditions, laminate configuration, taper angle and the type of taper on the dynamic response of the beam is performed. The NCT-301 graphite-epoxy composite material is considered in the analysis and in the parametric study.

Author: Pooya Salajegheh
Publisher:
ISBN:
Category :
Languages : en
Pages :

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Author: Michael Hyer
Publisher: DEStech Publications, Inc
ISBN: 1605950513
Category : Technology & Engineering
Languages : en
Pages : 2760

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Author: Qing-Hua Qin
Publisher: Bentham Science Publishers
ISBN: 9814998559
Category : Mathematics
Languages : en
Pages : 357

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This reference explains hybrid-Trefftz finite element method (FEM). Readers are introduced to the basic concepts and general element formulations of the method. This is followed by topics on non-homogeneous parabolic problems, thermal analysis of composites, and heat conduction in nonlinear functionally graded materials. A brief summary of the fundamental solution based-FEM is also presented followed by a discussion on axisymmetric potential problems and the rotordynamic response of tapered composites. The book is rounded by chapters that cover the n-sided polygonal hybrid finite elements and analysis of piezoelectric materials. Key Features - Systematic presentation of 9 topics - Covers FEMs in two sections: 1) hybrid-Trefftz method and 2) fundamental FEM solutions - Bibliographic references - Includes solutions to problems in the numerical analysis of different material types - Includes solutions to some problems encountered in civil engineering (seepage, heat transfer, etc). This reference is suitable for scholars involved in advanced courses in mathematics and engineering (civil engineering/materials engineering). Professionals involved in developing analytical tools for materials and construction testing can also benefit from the methods presented in the book.

Author: Abolghassem Zabihollah
Publisher:
ISBN:
Category : Buckling (Mechanics)
Languages : en
Pages : 0

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Tapered composite beams are being used in various engineering applications such as helicopter yoke, robot arms and turbine blade in which the structure needs to be stiff at one location and flexible at another locations. Laminated tapered beams can be manufactured by terminating some plies at discrete locations. Different types of ply drop-off can be achieved depending on the application. Due to the variety of tapered composite beams and complexity of the analysis, no analytical solution is available at present and therefore finite element method has been used for the calculation of response. In the present thesis, the free vibration response and buckling of different types of tapered composite beams are analyzed first using conventional finite element formulation. Conventional finite element formulation requires a large number of elements to obtain acceptable results. In addition, continuity of curvature at element interfaces can not be guaranteed with the use of conventional formulation. As a result, stress distribution across the thickness is not continuous at element interfaces. In order to overcome these limitations, an advanced finite element formulation is developed in the present thesis for vibration and buckling analysis of tapered composite beams based on classical laminate theory and first-order shear deformation theory. The developed formulation is applied to the analysis of various types of tapered composite beams. The efficiency and accuracy of the developed formulation are established in comparison with available solutions, where applicable, as well as with the results obtained using conventional formulation. A detailed parametric study has been conducted on various types of tapered composite beams, all made of NCT/301 graphite-epoxy, in order to investigate the effects of boundary conditions, laminate configuration, taper angle, the ratio of the length of the thick section to the length of the thin section and the ratio of the height of the thick section, to the height of thin section.

Author: Pramod Kumar
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Doubly-tapered laminated composite beams provide a great opportunity to enhance capabilities such as high strength-to-weight ratio, high modulus-to-weight ratio, and design flexibility. Due to design tailoring capabilities, the use of doubly-tapered composite beams has increased in the automobile industry and aerospace industry. In the present thesis, the free and forced vibration analyses of the width-and-thickness-tapered, called herein as doubly-tapered, laminated composite beams are conducted considering different boundary conditions, taper configurations, and loadings. The exact and closed-form solutions for the mode shapes and natural frequencies of doubly-tapered composite beams could not be acquired because of the complexity of the corresponding partial differential equations. Therefore, the classical laminate theory and the one-dimensional laminated beam theory in combination with the Ritz method are used in evaluating the stiffness and mass matrices of the composite beam. The natural frequencies and the corresponding mode shapes are determined by solving the eigenvalue problem obtained using the Ritz method. The forced vibration analysis of the doubly-tapered composite beams subjected to the transverse periodic and non-periodic loadings is carried out by representing the periodic loading as the superposition of the harmonic components of various frequencies using the Fourier series expansion and by expressing the non-periodic pulse excitation as the superposition of two or more simpler functions for which solutions are easier to determine. The maximum deflection of the doubly-tapered composite beam in spatial and time coordinates is determined. Numerical and symbolic computations have been performed using MATLAB® software. The solutions to the free and forced vibration analyses of the composite beams are compared, with the solution available in the literature and with the solution based on the Finite Element Method obtained using ANSYS®, to demonstrate solution accuracy. The Rayleigh damping is considered to model the viscous damping of the composite beam. A detailed parametric study is carried out to investigate the influences of the loading components in the Fourier series expansion, loading type, period of the periodic loading, the rise and fall times of the non-periodic loadings, taper angle, width ratio, thickness ratio, laminate length, stacking sequence, and taper configuration on the forced response of the doubly-tapered composite beam considering different boundary conditions.

Author: Hasnet Eftakher Uddin Ahmed
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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Tapered composite beams formed by terminating or dropping-off some of the plies from primary structure are being used in various engineering applications since the mid-1980s. Because of their structural tailoring capabilities, damage tolerance and potential for creating significant weight savings in engineering applications such as helicopter yoke, robot arms and turbine blades, tapered composite beams have received much attention from engineers and researchers. Design of mechanical components using tapered composite beams requires a better understanding of their behavior on free and forced vibrations. In the present thesis, free and forced vibration analysis including the effects of axial force and damping of tapered composite beams is conducted using conventional, and higher-order finite elements and the Rayleigh-Ritz method. Composite beam samples are manufactured and tested for the determination of mechanical properties and damping loss factor. Conventional and higher- order finite element formulations are established based on classical laminate theory. Since conventional finite element has limitation in obtaining accurate results with fewer elements, higher-order finite element formulation is developed considering four degrees of freedom per node (deflection, rotation, curvature and gradient of curvature) to overcome that problem. Rayleigh-Ritz method is used to obtain solutions for different boundary conditions to validate the results obtained by finite element methods. A detailed parametric study is conducted to investigate the effects of boundary conditions, laminate configurations, taper configurations, taper angle, the ratio of the length of the thick section to the length of thin section, axial force, and damping. The NCT-301 graphite-epoxy composite material is used in the experimental work, analysis, and in the parametric study.

Author: Puneet Jagpaul
Publisher:
ISBN:
Category :
Languages : en
Pages : 0

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ABSTRACT Free Vibration Analyses of Stationary and Rotating Tapered Composite Beams with Delamination Puneet Jagpaul The exceptional engineering properties and customizability of the laminated composites have enabled their use in the design of the stationary and rotating tapered structures in the aerospace and energy sectors. The tailoring capabilities of the composite material can be used to stiffen the structure at one location while being flexible at other location and consequently reduce the weight, as required in specific applications such as helicopter rotor blade, windmill blade and turbine blade. The vibration characteristics (natural frequencies and mode shapes) of the stationary and rotating structures differ substantially and must be well identified in the design stage. The composite structures are prone to failures such as delamination and fiber-matrix debonding caused during their fabrication or in service, especially when used as blades and beams in various stationary and rotating applications. Delamination reduces the overall stiffness and the strength of the laminates, which may lead to local or sudden structural failures. The delaminated structure has reduced natural frequencies and exhibits different mode shapes than that of the intact structure. In the present thesis, the free vibration analyses of stationary and rotating tapered composite beams with delamination are conducted. The influence of the delamination on the vibration characteristics of the stationary and rotating tapered composite beams is comprehensively studied. The Finite Element Analysis tool ANSYS® is used to develop three-dimensional models of the intact and delaminated composite beams. The natural frequencies of the stationary and rotating intact cantilever composite beams are determined for uniform, thickness-tapered and doubly tapered beam profiles using modal analysis and the results are compared with the results available in the literature. The Mode-I and Mode-II delamination tests are performed on the numerical models of the double cantilever beam and end notch flexure test samples based on cohesive zone modeling and the results of the tests are verified with the available results. The critically stressed locations prone to delamination in the stationary and rotating composite beams are determined using the first-ply failure analyses based on Tsai-Wu failure criterion. The free vibration responses of the stationary and rotating composite beams with end and mid-span delaminations of different lengths and with different stacking sequences are obtained and they are verified wherever possible. The delamination length that has minimal effect on the first three natural frequencies of the uniform and thickness-tapered composite beams is determined and is found to be 5% of the total beam length. Higher modes should be investigated for the composite structures with smaller delamination. A basis for the non-destructive evaluation is suggested for the stationary thickness-tapered simply supported composite beams with end and mid-span delaminations. The influences of the delamination length, delamination location, fiber orientation angle, thickness-tapering, double tapering, layer reduction and taper angle on the free vibration response of the stationary and rotating delaminated composite beams are investigated for uniform, thickness-tapered and doubly tapered beam profiles through various parametric studies. The influences of the rotational velocity and hub radius on the natural frequencies of the rotating doubly tapered composite beams with delamination are thoroughly examined. The present thesis contributes towards the safe design of the composite structures. The studies performed are helpful for developing delamination detection techniques based on the free vibration response of tapered composite beams and can aid designers to model optimised tapered composite structures by considering the influences of delamination on their vibrational characteristics.