Active vibration control of an arbitrary thick smart cylindrical panel with optimally placed piezoelectric sensor/actuator pairs

2015 ◽  
Vol 12 (1) ◽  
pp. 1-16 ◽  
Author(s):  
Seyyed M. Hasheminejad ◽  
A. Oveisi
Keyword(s):  
Vibration Control ◽  
Active Vibration Control ◽  
Piezoelectric Sensor ◽  
Cylindrical Panel ◽  
Sensor Actuator ◽  
Active Vibration

scholarly journals OPTIMAL PLACEMENT AND ACTIVE VIBRATION CONTROL OF COMPOSITE PLATES INTEGRATED PIEZOELECTRIC SENSOR/ACTUATOR PAIRS

2018 ◽  
Vol 56 (1) ◽  
pp. 113 ◽  
Author(s):  
Vu Van Tham ◽  
Tran Huu Quoc ◽  
Tran Minh Tu
Keyword(s):  
Vibration Control ◽  
Degrees Of Freedom ◽  
Active Vibration Control ◽  
Laminated Composite ◽  
Composite Plates ◽  
Piezoelectric Sensor ◽  
Optimal Placement ◽  
Laminated Composite Plates ◽  
Sensor Actuator ◽  
Active Vibration

In this study, a finite element model based on first-order shear deformation theory is presented for optimal placement and active vibration control of laminated composite plates with bonded distributed piezoelectric sensor/actuator pairs. The model employs the nine-node isoparametric rectangular element with 5 degrees of freedom for the mechanical displacements, and 2 electrical degrees of freedom. Genetic algorithm (GA) is applied to maximize the fundamental natural frequencies of plates; and the constant feedback control method is used for the vibration control analysis of piezoelectric laminated composite plates. The results of this study can be used to aid the placement of piezoelectric sensor/actuator pairs of smart composite plates as well as for robust controller design.

Active Vibration Control of a Doubly Curved Composite Shell Stiffened by Beams Bonded With Discrete Macro Fiber Composite Sensor/Actuator Pairs

2018 ◽  
Vol 140 (12) ◽  
Author(s):  
Ali H. Daraji ◽  
Jack M. Hale ◽  
Jianqiao Ye
Keyword(s):  
Vibration Control ◽  
Composite Shell ◽  
Active Vibration Control ◽  
Vibration Reduction ◽  
Piezoelectric Sensor ◽  
Feedback Gain ◽  
Linear Quadratic ◽  
Sensor Actuator ◽  
Active Vibration ◽  
Doubly Curved

Doubly curved stiffened shells are essential parts of many large-scale engineering structures, such as aerospace, automotive and marine structures. Optimization of active vibration reduction has not been properly investigated for this important group of structures. This study develops a placement methodology for such structures under motion base and external force excitations to optimize the locations of discrete piezoelectric sensor/actuator pairs and feedback gain using genetic algorithms for active vibration control. In this study, fitness and objective functions are proposed based on the maximization of sensor output voltage to optimize the locations of discrete sensors collected with actuators to attenuate several vibrations modes. The optimal control feedback gain is determined then based on the minimization of the linear quadratic index. A doubly curved composite shell stiffened by beams and bonded with discrete piezoelectric sensor/actuator pairs is modeled in this paper by first-order shear deformation theory using finite element method and Hamilton's principle. The proposed methodology is implemented first to investigate a cantilever composite shell to optimize four sensor/actuator pairs to attenuate the first six modes of vibration. The placement methodology is applied next to study a complex stiffened composite shell to optimize four sensor/actuator pairs to test the methodology effectiveness. The results of optimal sensor/actuator distribution are validated by convergence study in genetic algorithm program, ANSYS package and vibration reduction using optimal linear quadratic control scheme.

Analysis of sensor-debonding failure in active vibration control of smart composite plate

2017 ◽  
Vol 28 (18) ◽  
pp. 2603-2616 ◽  
Author(s):  
Asif Khan ◽  
Hyun Sung Lee ◽  
Heung Soo Kim
Keyword(s):  
Vibration Control ◽  
Composite Plate ◽  
Controller Design ◽  
Active Vibration Control ◽  
Piezoelectric Sensor ◽  
Smart Structure ◽  
Control Input ◽  
Smart Composite ◽  
Active Vibration ◽  
Controlled Structure

In this article, the effect of a sensor-debonding failure on the active vibration control of a smart composite plate is investigated numerically. A mathematical model of the smart structure with a partially debonded piezoelectric sensor is developed using an improved layerwise theory, a higher-order electric-potential field that serves as the displacement field, and the potential variation through the piezoelectric patches. A state-space form that is based on the reduced-order model is employed for the controller design. A control strategy with a constant gain and velocity feedback is used to assess the vibration-control characteristics of the controller in the presence of the sensor-debonding failure. The obtained results show that sensor-debonding failure reduces the sensor-output, control-input signal, and active damping in magnitude that successively degrades the vibration attenuation capability of the active vibration controller. The settling time and relative tip displacement of the controlled structure increase with the increasing length of partial debonding between the piezoelectric sensor and host structure. Furthermore, a damage-sensitive feature along with multidimensional scaling showed excellent results for the detection and quantification of sensor-debonding failure in the active vibration control of smart structures.

A HIGHER ORDER FINITE ELEMENT MODELING OF PIEZOLAMINATED SMART COMPOSITE PLATES AND ITS APPLICATION TO ACTIVE VIBRATION CONTROL

2007 ◽  
Vol 04 (01) ◽  
pp. 141-162 ◽  
Author(s):  
V. BALAMURUGAN ◽  
B. MANIKANDAN ◽  
S. NARAYANAN
Keyword(s):  
Finite Element ◽  
Vibration Control ◽  
Degrees Of Freedom ◽  
Active Vibration Control ◽  
Composite Plates ◽  
Piezoelectric Sensor ◽  
Higher Order ◽  
Interpolation Function ◽  
Smart Composite ◽  
Active Vibration

This paper presents a higher order — field consistent — piezolaminated 8-noded plate finite element with 36 elastic degrees-of-freedom per element and two electric degrees-of-freedom per element, one each for the piezoelectric sensor and actuator. The higher order plate theory used satisfies the stress and displacement continuity at the interface of the composite laminates and has zero shear stress on the top and bottom surfaces. The transverse shear deformation is of a higher order represented by the trigonometric functions allowing us to avoid the shear correction factors. In order to maintain the field consistency, the inplane displacements, u and v are interpolated using linear shape functions, the transverse displacement w is interpolated using hermite cubic interpolation function, while rotations θx and θy are interpolated using quadratic interpolation function. The element is developed to include stiffness and the electromechanical coupling of the piezoelectric sensor/actuator layers. The active vibration control performance of the piezolaminated smart composite plates has been studied by modeling them with the above element and applying various control strategies.

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