A parametric study on supersonic flutter behavior of laminated composite skew flat panels

Singha, M.K.; Ganapathi, M.

doi:10.1016/j.compstruct.2004.04.018

Cited by 66 publications

(33 citation statements)

References 20 publications

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“…The studies on the supersonic flutter of laminated panels reveal that the flutter oscillation is a coupled mode flutter with high modes coalescence [3,8,19], which is different from the coupled mode flutter of isotropic panels possessing equal amounts of the first and second natural modes [1]. The effects of lay-up schedule, fiber orientation, flow direction, skew angle etc.…”

Section: Introductionmentioning

confidence: 96%

“…The effects of lay-up schedule, fiber orientation, flow direction, skew angle etc. on the flutter characteristics of laminated panels are investigated by many authors [2][3][4][5][6][7][8][9][10][11][12][13][16][17][18][19][20][21][22]. However, most of the studies are conducted for thin panels, to the authors' knowledge, the flutter analysis of thick or moderately thick laminated panels has not been reported in any major international journal.…”

Section: Introductionmentioning

confidence: 98%

“…Two good survey articles of panel flutter theories and tests are given by Dowell [1] and Mei et al [2]. Linear and nonlinear flutter behaviors of laminated panels are studied using the classical laminated plate theory (CLPT) by many authors [3][4][5][6][7][8][9][10]. The approximate methods, such as orthotropic theory [11] and anisotropic theory [12], are also employed in flutter analysis for laminated plates.…”

Section: Introductionmentioning

confidence: 99%

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Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

Xia

2011

Acta Mech Sin

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The influence of fiber orientation, flow yaw angle and length-to-thickness ratio on flutter characteristics of angle-ply laminated plates in supersonic flow is studied by finite element approach. The structural model is established using the Reissner-Mindlin theory in which the transverse shear deformation is considered. The aerodynamic pressure is evaluated by the quasi-steady first-order piston theory. The equations of motion are formulated based on the principle of virtual work. With the harmonic motion assumption, the flutter boundary is determined by solving a series of complex eigenvalue problems. Numerical study shows that (1) The flutter dynamic pressure and the coalescence of flutter modes depend on fiber orientation, flow yaw angle and length-to-thickness ratio; (2) The laminated plate with all fibers aligned with the flow direction gives the highest flutter dynamic pressure, but a slight yawing of the flow from the fiber orientation results in a sharp decrease of the flutter dynamic pressure; (3) The angle-ply laminated plate with fiber orientation angle equal to flow yaw angle gives high flutter dynamic pressure, but not the maximum flutter dynamic pressure; (4) With the decrease of length-to-thickness ratio, an adverse effect due to mode transition on the flutter dynamic pressure is found.

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Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

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Parametric study on supersonic flutter of angle-ply laminated plates using shear deformable finite element method

Xia

2011

Acta Mech Sin

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“…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.…”

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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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“…Although there are many works dealt with the stability of sheet structures which have composite materials, however, almost the previous publications, the authors have mainly applied finite element methods [1][2][3][4][5][6][7][8]. The main content of this paper is a dynamic analysis of sheet structure that has functionally graded materials under aerodynamic load.…”

Section: Introductionmentioning

confidence: 99%