Active Vibration Control of Laminated Composite Plates Using Piezoelectric Devices: A Finite Element Approach

1993 ◽  
Vol 4 (4) ◽  
pp. 496-508 ◽  
Author(s):  
K. Chandrashekhara ◽  
A.N. Agarwal
Keyword(s):  
Finite Element ◽  
Vibration Control ◽  
Active Vibration Control ◽  
Laminated Composite ◽  
Composite Plates ◽  
Laminated Composite Plates ◽  
Finite Element Approach ◽  
Element Approach ◽  
Active Vibration ◽  
Piezoelectric Devices

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.

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.

Design and Analysis of an Aircraft Composite Hinge Bracket Using Finite Element Approach

2014 ◽  
Vol 629 ◽  
pp. 158-163
Author(s):  
Wai Chee Mun ◽  
Ahmad Rivai ◽  
Omar Bapokutty
Keyword(s):  
Finite Element ◽  
Composite Structures ◽  
Laminated Composite ◽  
Composite Plates ◽  
Metallic Structures ◽  
Aircraft Structures ◽  
Finite Element Approach ◽  
Heterogeneous Nature ◽  
Element Approach ◽  
Margin Of Safety

The use of composite materials in aircraft structures have been increasing for the past decade. The anisotropic and heterogeneous nature of composites remains a major challenge to the design and analysis of composite aircraft structures. Composite structures require a different design approach compared to the design of metallic structures. This paper aims to provide a step by step definitive guide to design and analyze composite structures using finite element approach. A simplified design model for the composite structural design was used to analyze an aircraft composite hinge bracket. The composite hinge bracket which is made of IM7/8552 laminated composite plates was successfully designed with a margin of safety of 0.216 and a weight savings of 43.77 percent was estimated.

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