Finite element flutter analysis of laminated composite panels

Chowdary, T.V.R.; Parthan, S.; Sinha, Prabhat Kumar

doi:10.1016/0045-7949(94)90200-3

Cited by 18 publications

(6 citation statements)

References 9 publications

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“…Table 1 shows the flutter limits, that are, dimensionless critical dynamic pressure parameters (cr) and dimensionless critical flutter frequencies (f) for square (a/b=1) and rectangular plates (a/b = 1/2) with various edge boundary conditions. The results of the square flat panel (a/b = 1) were compared with the boundary conditions S-S-S-S and C-C-C-C with reference [4,8]. In the case of simply supported (S-S-S-S) and fixed (C-C-C-C) panels, the flutter frequency (f) is found to exist between the first and second natural frequencies and is nearer to the second natural frequency.…”

Section: Comparison Of Fe Results With Flat Panel (R Tends To )mentioning

confidence: 99%

“…They noticed that increasing the interior pressure improves the aero-elastic controllability of conical shells. The panel flutter study of layered composite panels and shells have been carried out utilising 8-node isoparametric finite elements(FE) [8].…”

Section: Introductionmentioning

confidence: 99%

“…The QR method is employed for the solution of complex eigenvalue problems. Square flat plate flutter solutions are proffered for limited elastic edge boundary conditions [4,8,21] using the FE approach.…”

Section: Introductionmentioning

confidence: 99%

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Panel Flutter Numerical Study of Thin Isotropic Flat Plates and Curved Plates with Various Edge Boundary Conditions

Pany

2023

Politeknik Dergisi

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In this article, supersonic panel flutter analysis of flat plates and curved plates with different edge boundary conditions are studied, using efficient, high precision triangular shallow shell finite elements. The fluid on the underside of the plate was is assumed to be stationary. The linear piston theory can be applied to the top surface of the plate. The linear piston theory was used to evaluate the aerodynamic loads. The solution of a complex eigenvalue problem was formulated according to Hamilton’s principle. Lagrange’s equation of motion was obtained using standard methods for finding eigenvalues. Current finite element analysis ignores aerodynamic damping. For panels, the theory of thin and small deformed shells was taken into account. To validate the developed finite element code, the results of a square and rectangular flat-panels with simply supported edges (S-S-S-S), a square plate with four fixed edges (C-C-C-C), and a square plate with the length side clamps (C-S-C-S) were compared with the published data. The flutter results of other edge boundary conditions (S-C-S-C, C-S-C-S, and C-C-C-C) for square and rectangular flat panels are evaluated for which literature data is limited. It has been found that the fixed condition in the cross-flow direction (S-C-S-C) has a significant effect on the critical flutter pressure parameters and flutter frequencies. Further, to study the aforementioned effect, the current finite element (FE) has been extended to curved plates with S-C-S-C(constrained in the cross-flow direction and exposed to supersonic flow), SS-S-S boundary conditions to find flutter results.

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Section: Comparison Of Fe Results With Flat Panel (R Tends To )mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Panel Flutter Numerical Study of Thin Isotropic Flat Plates and Curved Plates with Various Edge Boundary Conditions

Pany

2023

Politeknik Dergisi

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“…Ketter (1967) considers orthotropicity in an arbitrary direction, subject to various boundary 1192 B. KORBAHTI and E. UZAL conditions. Liao and Sun (1993) and Chowdary et al (1994) use the finite element method to treat laminated plates, i.e., plates consisting of several layers of orthotropic materials with varying directions of orthotropicity, while Vijay and Durvasula (1998) use the Galerkin method. It should be noted here that while the Galerkin and finite element methods are closely related, papers using the Galerkin method normally consider base functions defined on the whole of the plate.…”

Section: Introductionmentioning

confidence: 99%

Vibrations of an Anisotropic Plate Under Fluid Flow in a Channel

Körbahti

Uzal

2007

Journal of Vibration and Control

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An analytical solution is given for the eigenfrequencies of the vibrations of a generally orthotropic plate placed in a rigid channel of rectangular cross section through which fluid flows. The fluid flow, assumed to be inviscid, compressible and non-steady, is modeled using a linearized potential equation. The plate is simply supported along the channel and extends indefinitely1 its vibrations are also assumed to be linear. The resulting system of partial differential equations are simplified assuming a travelling wave mode along the plate. The problem is reduced to a single integro-differential equation and solved analytically to obtain an algebraic eigenvalue equation relating travelling wavespeed to wavelength and the velocity of fluid flow. It is found that, for the case of a composite plate within a duct, placing the strengthening fibers perpendicular to flow direction increases the minimum velocity at which the unstable oscillations will occur in most cases.

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“…As an aeroelastic research problem, it includes linear and nonlinear stability and dynamic response, dynamics of systems with random parameters, [6], and interactions between static and dynamic instabilities in the presence of in-plane loads and thermal effects, [7] and [8]. Panel flutter has been used to study applications of composite materials, [9] and [10], and transverse shear effects, [11]. Most of the studies, however, are confined to rectangular panels.…”

Section: Introductionmentioning

confidence: 99%

Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

Elnomrossy

Mehanna

1999

International Conference on Aerospace Sciences and Aviation Tec

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The equivalent plate modeling formulation of composite wings, described in Part One, is extended in this paper to include the explicit analytic expressions for terms of the mass and aerodynamic matrices. Analytic sensitivities of the mass and aerodynamic matrices with respect to panel shape, thickness and fiber orientations are derived. Before proceeding in the study of analytic sensitivities using the derived expressions, the accuracy of its panel flutter analysis was numerically tested for simply supported panels of trapezoidal and skewed shape, of isotropic and composite materials and variable fiber orientations. The nondimensional critical dynamic pressure and critical frequency of flutter are compared with the results of finite element flutter analysis of composite skew panels by Chowdary, T.V.R. and al given in "Computers and Structures", (1996). The correlation of the results is good for moderate in-plane loading. Accuracy of the approximations is studied for the integration with nonlinear programming/approximation concept aeroelastic design synthesis methodology.

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Finite element flutter analysis of laminated composite panels

Cited by 18 publications

References 9 publications

Panel Flutter Numerical Study of Thin Isotropic Flat Plates and Curved Plates with Various Edge Boundary Conditions

Panel Flutter Numerical Study of Thin Isotropic Flat Plates and Curved Plates with Various Edge Boundary Conditions

Vibrations of an Anisotropic Plate Under Fluid Flow in a Channel

Analytic Sensitivities in Composite Wing-Shape Ynthesis Part Two: Panel Flutter Constraints

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