Active Control of Nonlinear Panel Flutter Using Aeroelastic Modes and Piezoelectric Actuators

Kim, Myoung-Hee; Huang, Jen-Kuang; Mei, Chuh

doi:10.2514/1.33803

Cited by 20 publications

(13 citation statements)

References 17 publications

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“…Li [17] designed the displacement and acceleration feedback control algorithms, to realize active flutter control of panel structure using the piezoelectric material. Kim [18] used the aeroelastic modes and self-induced actuators to control the panel flutter, and the location configuration based on the position feedback gain control and the Kalman filter gain method were optimized. Song [19] investigated active aeroelastic flutter control of supersonic composite laminated plate with the piezoelectric patches.…”

Section: Introductionmentioning

confidence: 99%

A unified Gram-Schmidt-Ritz formulation for vibration and active flutter control analysis of honeycomb sandwich plate with general elastic support

Lin¹,

Cao²

2018

J. vibroeng.

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An admissible function constructed by orthogonal polynomials is presented to investigate the vibration and active flutter control of Honeycomb sandwich plate with general elastic support in a supersonic airflow. The control strategies based on the displacement feedback and LQR method are applied by means of pasting the piezoelectric material on the surface of the plate structure. Employing the first-order piston theory to describe the aerodynamic loads, the governing equation of plate system with the piezoelectric actuator is established based on the Hamilton principle. The mode shapes are obtained using the admissible functions, which are a set of characteristic orthogonal polynomials generated directly by employing the Gram-Schmidt process, and the general elastic constraint is modeled using the artificial spring technology. The frequency and mode shape under different boundary are calculated by Rayleigh-Ritz method. The validity of the proposed approach is confirmed by comparing the results with those obtained from FEM and literatures. The phenomenon of mode jumping is observed with the increase of the aerodynamic pressure. The study of active control shows that, the increasement of displacement feedback gain improves the critical dynamic pressure.

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Section: Introductionmentioning

confidence: 99%

A unified Gram-Schmidt-Ritz formulation for vibration and active flutter control analysis of honeycomb sandwich plate with general elastic support

Lin¹,

Cao²

2018

J. vibroeng.

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“…Frampton et al (1996) researched the aeroelastic properties and active flutter control for linear panels in supersonic airflow using the piezoelectric actuators. Kim et al (2008) presented an effective controller based on aeroelastic modes to improve the aeroelastic flutter characteristics of composite laminated panels in supersonic airflow using the FEM. Nam et al (2000) studied the aeroelastic stability and active flutter suppression of smart composite wing with the effect of delamination.…”

Section: Introductionmentioning

confidence: 99%

Aerothermoelastic flutter analysis and active vibration suppression of nonlinear composite laminated panels with time-dependent boundary conditions in supersonic airflow

Chai

Song

et al. 2017

Journal of Intelligent Material Systems and Structures

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Aerothermoelastic flutter properties of nonlinear composite laminated panels in supersonic airflow are studied, and investigations on active flutter and aerothermal postbuckling suppression for the panels with time-dependent boundary conditions are also carried out using macro fiber composite actuator and sensor. The von Karman strain–displacement relation in conjunction with the supersonic piston theory is applied in structural modeling. Nonlinear dynamic equations of motion for the structural system are established using Hamilton’s principle and the assumed mode method. Frequency- and time-domain methods are used to investigate the aerothermoelastic characteristics and active flutter and aerothermal postbuckling suppression of the panels. Effects of aspect ratio and ply angle on the nonlinear aerothermoelastic behaviors are studied. The displacement feedback control is used to conduct the active flutter and postbuckling suppression. The nonlinear output controller consisting of a linear quadratic regulator and a nonlinear state estimator of extended Kalman filter is also used in designing the controller. Controlled vibration responses of the structural system under the two different controllers are compared. The results show that the developed linear quadratic regulator/extended Kalman filter controller is more effective than the displacement feedback control controller in flutter and postbuckling control of the panels with time-dependent boundary conditions in supersonic airflow.

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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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Active Control of Nonlinear Panel Flutter Using Aeroelastic Modes and Piezoelectric Actuators

Cited by 20 publications

References 17 publications

A unified Gram-Schmidt-Ritz formulation for vibration and active flutter control analysis of honeycomb sandwich plate with general elastic support

A unified Gram-Schmidt-Ritz formulation for vibration and active flutter control analysis of honeycomb sandwich plate with general elastic support

Aerothermoelastic flutter analysis and active vibration suppression of nonlinear composite laminated panels with time-dependent boundary conditions in supersonic airflow

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

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