Finite element analysis and design of control system with feedback output using piezoelectric sensor/actuator for panel flutter suppression

Moon, Seong Hwan

doi:10.1016/j.finel.2006.04.001

Cited by 29 publications

(22 citation statements)

References 19 publications

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“…Based on the authors' knowledge, regarding previous studies in FSI problems with orthotropic piezoelectric materials, only piezoelectric and structural governing equations are solved, and the uid ow is considered a pressure load [5] or calculated by the piston theory [6][7][8][9]. Therefore, uid structure interaction was not taken into account.…”

Section: Introductionmentioning

confidence: 99%

Fluid–structure interaction analysis of a piezoelectric flexible plate in a cavity filled with a fluid

2016

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Abstract. This study presents a numerical analysis of uid-structure interaction, the structure of which is a exible piezoelectric material. Piezoelectric materials are widely used in aero-elasticity and turbomachinery elds for vibration, utter, and noise control. In this work, a FSI benchmark is revised to contain the piezoelectric materials. The in uence of piezoelectricity on the oscillation of the structure and uid ow is considered. For validation, two benchmark problems are solved and the results of the present code are compared with those of previous work. Current results show that the piezoelectric behavior of a plate signi cantly in uences the oscillation of the plate and the uid ow properties.

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Section: Introductionmentioning

confidence: 99%

Fluid–structure interaction analysis of a piezoelectric flexible plate in a cavity filled with a fluid

2016

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“…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%

“…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%

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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“…The FEM was used in the modeling of equation of motion. Moon et al [16,17] studied the active optimal flutter control of composite panels using the FEM. Xue and Mei [18] carried out a study on the flutter behaviors of two-dimensional nonlinear panels with thermal effect using the FEM.…”

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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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Finite element analysis and design of control system with feedback output using piezoelectric sensor/actuator for panel flutter suppression

Cited by 29 publications

References 19 publications

Fluid–structure interaction analysis of a piezoelectric flexible plate in a cavity filled with a fluid

Fluid–structure interaction analysis of a piezoelectric flexible plate in a cavity filled with a fluid

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

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

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