Flutter control of an adaptive composite panel

Suleman, Afzal; Venkayya, V. B.

doi:10.2514/6.1994-1744

Cited by 9 publications

(2 citation statements)

References 2 publications

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“…Ha et al (1991) defined the composite element in an 8-node, 32-degree-of-freedom brick element. Detwiller et al (1994) and Suleman and Venkayya (1994) defined the piezoelectric layer in 2D composite elements in which the electric potential is an element quantity. The work presented in this paper combines the 3D features of the piezoelectric layer as defined by Ha et al (1991) with the simplicity of the quadrilateral elements developed by Detwiller et al (1994) and Suleman and Venkayya (1994) to produce a composite quadrilateral element with a solid piezoelectric layer.…”

Section: Introductionmentioning

confidence: 99%

A comparison of active, passive and hybrid damping in structural design

Veley¹,

Rao

1996

Smart Mater. Struct.

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The QUAD4 element found in ASTROS is modified to include piezoelectric layers and a viscoelastic layer. These features are developed and combined to allow for active damping using piezoelectrics, passive damping using constrained layer damping (CLD) and hybrid damping in the form of active constrained layer damping (ACLD). These features are implemented in the QUAD4 element as additional layers in the composite layup definition. The development of these features are presented and the integrity of the implementation is validated by comparing with results found in the literature. A patch placement process is developed which allows the damping treatment to move on the structure and to distort its shape so as to improve the damping characteristics of the design. The structure and damping treatment are simultaneously designed for minimum weight with constraints on the frequency and damping ratio. Both beam and plate structures are used to illustrate this concept. A proportional-derivative controller is used for the active control of the beam and the linear quadratic regulator (LQR) is used to design the active controller for the plates.

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Section: Introductionmentioning

confidence: 99%

A comparison of active, passive and hybrid damping in structural design

Veley¹,

Rao

1996

Smart Mater. Struct.

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“…Heeg [11] conducted an experimental study for flutter suppression of a beam model and demonstrated the application of piezoelectric materials for flutter suppression. Suleman and Venkayya [12] developed a finite-element formulation for flutter suppression of the composite panel with a piezoelectric actuator/sensor. They used first-order piston theory for unsteady aerodynamics and compared the results of the static and dynamic analysis with the experimental results.…”

Section: Introductionmentioning

confidence: 99%

Optimal sizing and placement of piezo-actuators for active flutter suppression

Nam

Kim

Weisshaar³

1996

Smart Mater. Struct.

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The purpose of this work is to design an active control system for flutter suppression of a laminated plate wing model using segmented piezo-actuators. We describe investigations pertaining to the optimal size, thickness and locations of piezo-actuators on a laminated plate-wing structure for flutter suppression. The analysis for the laminated composite wing model is conducted by the Ritz solution technique, which represents the displacement on the plate in terms of power series in spanwise and chordwise directions. The active control system design for flutter suppression requires the equation of motion to be expressed in a linear time-invariant state-space form. The doublet-lattice method is used to compute unsteady aerodynamic forces, which are approximated as the transfer functions of the Laplace variable by the minimum-state method combined with an optimization technique. To design the control system, linear quadratic regulator theory with output feedback is considered in this study. The feedback control gains are obtained by solving coupled nonlinear matrix equations via numerical optimization routines. The optimal geometry of piezo-actuators which minimizes the control performance index is determined by the optimization technique referred to as the sequential linear programming method. The numerical result shows a substantial saving in control effort compared with the initial model.

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H∞ control for flutter suppression of a laminated plate with self-sensing actuators

Kim

Nam

1996

KSME Journal

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Flutter control of an adaptive composite panel

Cited by 9 publications

References 2 publications

A comparison of active, passive and hybrid damping in structural design

A comparison of active, passive and hybrid damping in structural design

Optimal sizing and placement of piezo-actuators for active flutter suppression

H∞ control for flutter suppression of a laminated plate with self-sensing actuators

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