A new stiffened plate element for the analysis of arbitrary plates

Barik, Manoranjan; Mukhopadhyay, Madhujit

doi:10.1016/s0263-8231(02)00016-2

Cited by 57 publications

(20 citation statements)

References 21 publications

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“…In the present work, four different elements including two conventional and two super elements [2] have been used so as to predict the dynamic characteristics of stiffened panels. The formulation of the plate and stiffeners are both based on the first order shear deformation theories so it can be applicable to both thin and thick plates.…”

Section: Introductionmentioning

confidence: 99%

Vibration analysis of stiffened plates using finite element method

Hamedani

Khedmati

Azkat

2012

Lat. Am. j. solids struct.

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This paper presents the vibration analysis of stiffened plates, using both conventional and super finite element methods. Mindlin plate and Timoshenko beam theories are utilized so as to formulate the plate and stiffeners, respectively. Eccentricity of the stiffeners is considered and they are not limited to be placed on nodal lines. Therefore, any configuration of plate and stiffeners can be modeled. Numerical examples are proposed to study the accuracy and convergence characteristics of the super elements. Effects of various parameters such as the boundary conditions of the plate, along with orientation, eccentricity, dimensions and number of the stiffeners on free vibration characteristics of stiffened panels are studied.

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Section: Introductionmentioning

confidence: 99%

Vibration analysis of stiffened plates using finite element method

Hamedani

Khedmati

Azkat

2012

Lat. Am. j. solids struct.

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“…In order to match the beam element to Rogner-FoxSchmit rectangular element, the rate of torsion of the space beam is considered here [18,19]. In other words, one more degree , x x θ is added to each node of the general threedimensional beam element.…”

Section: Three-dimensional Beam Elementmentioning

confidence: 99%

Nonlinear flutter analysis of stiffened composite panels in supersonic flow

Yuan

Qiu

2010

Sci. China Phys. Mech. Astron.

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The flutter instability of stiffened composite panels subjected to aerodynamic forces in the supersonic flow is investigated. Based on Hamilton's principle, the aeroelastic model of the composite panel is established by using the von Karman large deflection plate theory, piston theory aerodynamics and the quasi-steady thermal stress theory. Then, using the finite element method along with Bogner-Fox-Schmit elements and three-dimensional beam elements, the nonlinear equations of motion are derived. The effect of stiffening scheme on the flutter critical dynamic pressure is demonstrated through the numerical example, and the nonlinear flutter characteristics of stiffened composite panels are also analyzed in the time domain. This will lay the foundation for design of panel structures employed in aerospace vehicles. panel flutter, piston theory, finite element method, quasi-steady thermal stress, critical dynamic pressure, stiffened composite panelThe thin-walled stiffened panel, a useful and popular form of structural component, has been widely used in the fields of aviation, shipbuilding and civil engineering. By using stiffened panels as primary structural components, light-weight and efficient structures can be obtained without considerable weight penalty. Also, composite material has been increasing employed in aircraft structures due to its light weight and high strength-toweight and high stiffness-to-weight ratio. Therefore, the thin-walled stiffened panel made by composite material has attracted much attention [1-5].Panel flutter is a self-excited, dynamic instability of thin plate structural components subjected to the combination of inertial force, elastic force and aerodynamic loading [6,7]. This aeroelastic phenomenon is often encountered in the operation of aircraft and missiles at supersonic speed. An excellent presentation of fundamental theories and physical understanding of panel flutter can be found in a review article [8] on the topic by Dowell, he has analyzed the phenomenon of panel flutter by using the governing partial differential equations in conjunction with the Galerkin's method. Olson [9] extended the finite element method to study the linear panel flutter problem. The finite element method is a powerful numerical tool for flutter analysis of isotropic and anisotropic panels with general geometry, applied loads, and boundary conditions. Gray [10] reported the nonlinear panel flutter of composite panels using LUM/ NTF frequency domain approach. Zhou [11] investigated nonlinear flutter of panel under aerodynamic heating with mutual understanding of power spectra and time responses. Azzouz [12] studied nonlinear flutter characteristics of two-dimensional and three-dimensional cylindrical panels under yawed supersonic flow. Recently, some researchers attend to investigating panel flutter control [13,14] and optimization of panel structures [15]. Unlike unstiffened panels, only a few studies on the flutter characteristics of stiffened laminated panels exist. Liao and Sun [16] researched the li...

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“…Finite element method is a common numerical approach. In additional to Ebel [2], who applied the finite element method to study buckling load for a diagonally stiffened rectangular panel, other researchers, such as Guo et al [4,5], Hatzidakis and Bernitsas [6] applied the finite element method to analyze buckling phenomena of the plates with parallel or orthogonal stiffening beams; Srivastava et al [7,8] formulated plate and stiffener elements for buckling and vibration analysis of stiffened plates subjected to various loads; Rikards et al [9] developed triangular finite element for buckling and vibration analysis of laminated composite stiffened plates; Barik and Mukhopadhyay [10] developed a four-noded stiffened plate element, which was claimed with the advantages of an isoparametric element, but without the disadvantage of shear-locking problem, for buckling and vibration analysis of stiffened thin plates with arbitrary shapes, etc.…”

Section: Introductionmentioning

confidence: 99%

A point receptance array approach for stiffened panel structures

Huang

2010

International Journal of Mechanical Sciences

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A new stiffened plate element for the analysis of arbitrary plates

Cited by 57 publications

References 21 publications

Vibration analysis of stiffened plates using finite element method

Vibration analysis of stiffened plates using finite element method

Nonlinear flutter analysis of stiffened composite panels in supersonic flow

A point receptance array approach for stiffened panel structures

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