Suppression of Thermal Postbuckling and Nonlinear Panel Flutter Motions Using Piezoelectric Actuators

Qin, Xianhui; Mei, Chuh; Huang, Jen-Kuang

doi:10.2514/1.28280

Cited by 28 publications

(14 citation statements)

References 16 publications

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“…New piezoelectric materials with ever-increasing values of e P (d 31 ) are being currently introduced (e.g., 180 10 12 mV 1 for PZT5A to 370 mV 1 10 12 for PZT5) [16]. The value of E p may be taken as 63 GPa for this family of materials.…”

Section: Selection Of Piezoelectric Materialsmentioning

confidence: 99%

Piezoelectric Control of a Partially Propped Cantilever Subjected to a Follower Force

Sunjung

Sridharan

2010

AIAA Journal

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A cantilever column carrying a compressive follower force and propped by a spring can become dynamically unstable by flutter or divergence depending upon spring stiffness. In this study, issues involved in the control of such a column by means of piezoelectric patches at the top and bottom surfaces of the column are studied. Attention is focused on negative feedback control with patch voltages proportional to the locally sensed bending strain rates. It is found such control is capable of significantly enhancing the critical load in the flutter range, such enhancement being limited often only by the limits on voltage developed across the patch of given thickness. In the range of spring stiffness corresponding to buckling failure, this control strategy is simply ineffective. A relatively light spring not only enhances the critical force significantly but also makes the control more effective. For prescribed limits on voltage across the patch, there is an optimal spring stiffness that results in the maximum of critical load and this lies in the flutter range of the spring stiffness. Softening nonlinearity reduces the critical loads in the range of transition from flutter to divergence and rounds off the sharpness of the drop in this range seen in the linear case. A partial patch spanning over half the length of the column from the fixed end is significantly more effective than a full patch in the flutter range. Nomenclature b = b P , width of the column section (width of piezoelectric patch) E = Young's modulus of the material of the host beam E P = Young's modulus of the piezoelectric material e P = piezoelectric constant H = depth of the column section G = control gain K 1 , K 3 = spring constants I = second moment of the area about the weaker axis L = length of the beam m = mass per unit length of the column N = number of harmonics in the Fourier series description P = axial (compressive) load P E = Euler buckling load of a column with pinned ends, 2 EI=L 2 P cr = critical load as determined from linear stability analysis P max = maximum load attained by the column for a give gain q o = uniformly distributed lateral load per unit length V = voltage across the piezoelectric patch V m = mth coefficient in the Fourier series representation of V v = lateral displacement of the column v m = mth coefficient in the Fourier series representation of v v m= v m =L 1 , 3 = nondimensional linear and nonlinear spring stiffnesses, respectively

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Section: Selection Of Piezoelectric Materialsmentioning

confidence: 99%

Piezoelectric Control of a Partially Propped Cantilever Subjected to a Follower Force

Sunjung

Sridharan

2010

AIAA Journal

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“…MFC actuator employs the interdigitated electrodes (Azzouz et al, 2001) with the direction of the field coinciding with the longitudinal direction and utilizes the high value of d 11 for the piezo-electric constant, e. The magnitude of Ee from Li et al, 2007 is 0.03457 N/mm V. The ratio Ee/E s e s = 1.22. The allowable electric field is taken as 2000 V per mm of electrode pitch (Li et al, 2007). (ii) PZT5A -a traditional monolithic isotropic piezo-ceramic composite -which responds to field s applied across the thickness in terms of d 31 (=d 32 = e).…”

Section: Selection Of Piezo-electric Materials Propertiesmentioning

confidence: 99%

“…(ii) PZT5A -a traditional monolithic isotropic piezo-ceramic composite -which responds to field s applied across the thickness in terms of d 31 (=d 32 = e). Ee (Li et al, 2007) = 0.01186 N/ mm V. This material may be used for panel control where the voltage demand is evidently less severe. The ratio Ee/E p e p = 0.42.…”

Section: Selection Of Piezo-electric Materials Propertiesmentioning

confidence: 99%

“…Literature on piezo-electric control of flutter, buckling and nonlinear response of plate structures is extensive and we can do no more than mention a few topics investigated in this field: enhancement of column flutter and buckling responses (Wang and Quek, 2002), geometrically nonlinear response of piezo-laminated plates (Rabinovitch, 2005), and active control of nonlinear supersonic panel flutter (Abdel-Motagaly et al, 2005;Li et al, 2007). This paper addresses the issues involved in the piezo-electric control of an ''optimally designed" stiffened panel -optimal in the sense the local and overall buckling loads under axial compression are rendered equal.…”

Section: Introductionmentioning

confidence: 99%

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Piezo-electric control of stiffened panels subject to interactive buckling

Sridharan

Kim

2009

International Journal of Solids and Structures

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a b s t r a c tThe paper examines the feasibility of piezo-electric control of stiffened plates carrying axial compression and subject to interaction of local and overall buckling. A simple control strategy involving piezo-electric patches along the tips of the stiffeners carrying equal and opposite electric fields to resist bending of the stiffeners was found to effectively counteract the adverse effects of mode interaction and imperfectionsensitivity. For the dynamic problem, this strategy needed to be supplemented with patches attached to the surfaces of the plate in the middle of the panel to damp out local buckling oscillations. Two panels were considered, these being scaled replicas of each other. This enabled an examination of the scaling laws of response with practical applications in view. The results demonstrate that the structural performance of optimally designed stiffened structures can be enhanced with minimal energy consumption by appropriately designed piezo-electric patch configuration.

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“…In the analysis, high-order triangular plate finite element is applied. 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.…”

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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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Suppression of Thermal Postbuckling and Nonlinear Panel Flutter Motions Using Piezoelectric Actuators

Cited by 28 publications

References 16 publications

Piezoelectric Control of a Partially Propped Cantilever Subjected to a Follower Force

Piezoelectric Control of a Partially Propped Cantilever Subjected to a Follower Force

Piezo-electric control of stiffened panels subject to interactive buckling

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

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