Effects of hysteretic and aerodynamic damping on supersonic panel flutter of composite plates

Koo, Kyo-Nam; Hwang, Woo-Seok

doi:10.1016/s0022-460x(03)00514-5

Cited by 47 publications

(26 citation statements)

References 13 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: 97%

“…The Mindlin plate elements are used extensively to study the thermal buckling, nonlinear flutter response and flutter suppression of laminated plates [15][16][17]. Besides the Reissner-Mindlin theory, various shear deformation laminate theories, such as the first-order shear deformation theory (FSDT) considering the variation of the membrane displacement with the thickness, and the high-order shear deformation theories (HSDT) allowing for the warping in the ply are extended to panel flutter analysis in recent years [18][19][20][21][22]. The comparison among these theories is referred to Reddy and Arciniega [23].…”

Section: Introductionmentioning

confidence: 99%

“…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: 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: 97%

Section: Introductionmentioning

confidence: 99%

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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“…Kobayashi [5] has adopted two order liner modes as the Galerkin function and investigated the panel flutter response. In reference [6] the piston theory of supersonic flow and Von Karman nonlinear strain-displacement relations were employed to analyze the flutter of panel, and the critical flutter flow velocity (or dynamic pressure), limit cycle and chaotic response were studied. Yuen and Lau [7] used the harmonic balance method to study the flutter and post-buckling response of the simply supported panel.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear dynamics analysis of a two-dimensional thin panel with an external forcing in incompressible subsonic flow

Yang

2011

Nonlinear Dyn

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Based on the potential theory of incompressible flow and the energy method, a two-dimensional simply supported thin panel subjected to external forcing and uniform incompressible subsonic flow is theoretically modeled. The nonlinear cubic stiffness and viscous damper in the middle of the panel is considered. Transformation of the governing partial differential equation to a set of ordinary differential equations is performed through the Galerkin method. The stability of the fixed points of the panel system is analyzed. The regions of different motion types of the panel system are investigated in different parameter spaces. The rich dynamic behaviors are presented as bifurcation diagrams, phase-plane portraits, Poincaré maps and maximum Lyapunov exponents based on carefully numerical simulations.

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“…Li et al [14] studied the flutter and thermal postbuckling suppression of a large amplitude nonlinear panel using the FEM. Koo and Hwang [15] performed a study of flutter characteristics for composite panels with structural damping. The FEM was used in the modeling of equation of motion.…”

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confidence: 99%

Investigations on the flutter properties of supersonic panels with different boundary conditions

Song

2013

Int. J. Dynam. Control

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Aeroelastic characteristics of supersonic panels with different boundary conditions are analyzed. The classical thin plate theory is used in the structural modeling. The unsteady aerodynamic pressure is evaluated using the supersonic piston theory. To formulate the governing equation of motion for the aeroelastic structural system, Hamilton's principle is carried out. The assumed mode method (AMM) and the finite element method are used to obtain the discrete equation of motion. Frequency-domain method is conducted to analyze the aeroelastic performances of the panel with different boundary conditions. The special flutter properties of panels with elastically restrained boundary condition are also investigated. The accuracy of the AMM in the flutter analysis of panels with different constraints is researched. Aeroelastic characteristics of the panels with different boundary conditions are also investigated.

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Effects of hysteretic and aerodynamic damping on supersonic panel flutter of composite plates

Cited by 47 publications

References 13 publications

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

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

Nonlinear dynamics analysis of a two-dimensional thin panel with an external forcing in incompressible subsonic flow

Investigations on the flutter properties of supersonic panels with different boundary conditions

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