Active Vibration Control of Flexible Space Structures by Using Piezoelectric Sensors and Actuators

1993 ◽  
Author(s):  
Brij N. Agrawal ◽  
Hyochoong Bang
Keyword(s):  
Vibration Control ◽  
Vibration Suppression ◽  
Active Vibration Control ◽  
Flexible Structures ◽  
Space Structures ◽  
Sensors And Actuators ◽  
Flexible Space Structures ◽  
Flexible Arm ◽  
Active Vibration ◽  
Structural Mode

Abstract The application of piezoelectric actuators and sensors in the vibration suppression of flexible structures is demonstrated experimentally. Navy Type II piezoceramic wafers were bonded at the base of a flexible arm to increase damping of its first structural mode at at 0.138 Hz. A Positive Position Feedback (PPF) analog compensator was used for active vibration control. The damping of the first mode was increased from 0.3% to 1.5 % by using the active control.

Distributed active vibration cooperative control for flexible structure with multiple autonomous substructure model

2020 ◽  
Vol 26 (21-22) ◽  
pp. 2026-2036
Author(s):  
Xiangdong Liu ◽  
Haikuo Liu ◽  
Changkun Du ◽  
Pingli Lu ◽  
Dongping Jin ◽  
...  
Keyword(s):  
Vibration Control ◽  
Cooperative Control ◽  
Vibration Suppression ◽  
Control Strategies ◽  
Active Vibration Control ◽  
Flexible Structures ◽  
Lyapunov Theory ◽  
Sensors And Actuators ◽  
Active Vibration ◽  
Distributed Cooperative Control

The objective of this work was to suppress the vibration of flexible structures by using a distributed cooperative control scheme with decentralized sensors and actuators. For the application of the distributed cooperative control strategy, we first propose the multiple autonomous substructure models for flexible structures. Each autonomous substructure is equipped with its own sensor, actuator, and controller, and they all have computation and communication capabilities. The primary focus of this investigation was to illustrate the use of a distributed cooperative protocol to enable vibration control. Based on the proposed models, we design two novel active vibration control strategies, both of which are implemented in a distributed manner under a communication network. The distributed controllers can effectively suppress the vibration of flexible structures, and a certain degree of interaction cooperation will improve the performance of the vibration suppression. The stability of flexible systems is analyzed by the Lyapunov theory. Finally, numerical examples of a cantilever beam structure demonstrate the effectiveness of the proposed methods.

Positive Position Feedback Vibration Control of a Composite I-Beam With Fuzzy Gain Tuning

2002 ◽  
Author(s):  
H. Gu ◽  
G. Song
Keyword(s):  
Vibration Control ◽  
Least Squares ◽  
Fuzzy System ◽  
Vibration Suppression ◽  
Active Vibration Control ◽  
Flexible Structures ◽  
Training Data ◽  
Sensors And Actuators ◽  
Positive Position Feedback ◽  
Position Feedback

Positive position feedback (PPF) control is widely used in active vibration control of flexible structures. To ensure the vibration is quickly suppressed, a large PPF scalar gain is often applied in a PPF controller. However, PPF control with a large scalar gain causes initial overshoot, which is undesirable in many situations. In this paper, a fuzzy gain tuner is proposed to tune the gain in the positive position feedback control to reduce the initial overshoot while still maintaining a quick vibration suppression. The fuzzy system is trained by the desired input-output data sets by batch least squares algorithm so that the trained fuzzy system can behave like the training data. A 3.35 meter long I-beam with piezoceramic patch sensors and actuators is used as the experimental object. The experiments include the standard PPF control, standard PPF control with traditional fuzzy gain tuning, and PPF control with batch least squares fuzzy gain tuning. Experimental results clearly demonstrate that PPF control with batch least squares fuzzy gain tuner behaves much better than the other two in terms of successfully reducing the initial overshoot and quickly suppressing vibration.

scholarly journals The Effect of Attack Angle On The Vibration Suppression Of Composite Wing Airfoil NACA 0012

2021 ◽  
Vol 27 (4) ◽  
pp. 17-21
Author(s):  
Hassan Ali Kadhem ◽  
Ahmed Abdul Hussein
Keyword(s):  
Vibration Control ◽  
Glass Fiber ◽  
Vibration Suppression ◽  
Fiber Composite ◽  
Active Vibration Control ◽  
Attack Angle ◽  
Sensors And Actuators ◽  
Glass Fiber Composite ◽  
Active Vibration ◽  
Composite Wing

Active vibration control is presented as an effective technique used for vibration suppression and for attenuating bad effects of disturbances on structure. In this work Proportional-Integral-Derivative control were employed to study suppression of active vibration wing affected by wind airflow. Two different composite wings with different manufacturing materials had been made with specific size to be suitable for using in wind tunnel. Piezoelectric (PZT (transducers are used as sensors and actuators in vibration control systems. The velocity was 25 m/s and three different attack angles (0, 10, 20 degrees) had been taken to show their effect on the wings vibrations suppression. The results shows that the suppression of the wing amplitude is reduced when the attack angle increases for both woven and random composite wing matt and this happened due to the vortex which became more violent at the increase of attack angle and also due to the area that face the wind which will increase when the attack angle increase and this will reduces the suppression. The maximum control amplitude of woven Glass-fiber matt was 1.75cm and the damping was about 38 % at zero attack angle while it was 2cm and the damping was about 26 % at 20 degree attack angle for random Glass-fiber composite matt

scholarly journals The Effect of Wind Velocity on the Suppression of Composite Wing Airfoil NACA 0012

2019 ◽  
Vol 15 (3) ◽  
pp. 38-44
Author(s):  
Hassan Ali Kadhem ◽  
Ahmed Abdul Hussein
Keyword(s):  
Vibration Control ◽  
Glass Fiber ◽  
Wind Velocity ◽  
Vibration Suppression ◽  
Active Vibration Control ◽  
Harmonic Oscillation ◽  
Sensors And Actuators ◽  
Engineering Department ◽  
Active Vibration ◽  
Composite Wing

The first studies on shocks and vibrations were carried out at the beginning of the 1930s to improve the behavior of buildings during earthquakes. Vibration tests on aircraft were developed from 1940 to verify the resistance of parts and equipments prior to their first use. Flutter is a well-known example of dynamic aero elasticity, where when oscillation of structure interacted with unsteady aerodynamic forces the flutter will occur. Vibration on any structure without damping means that self-harmonic oscillation will occur, and in most cases the oscillation may start to increase until structural failure. This behavior is very similar to resonance phenomena if only the oscillation is being studied as a vibration case. In vibration suppression, the active vibration control is one of the more effective technique which is used for attenuating bad effects of disturbances on structure. In this work, two different composite wings have been used; one of them is made of Glass-fiber random matt and the other is made of woven ({0/90} Glass-fiber). The proportional-integral-derivative (PID) control is employed here for studying the suppression of active vibration wing affected by wind velocity flow through wind tunnel in the laboratory of mechanical engineering department at the university of Baghdad. Piezoelectric (PZT (transducers are used as sensors and actuators in vibration control systems. The attack angle was 10 degrees and three different velocities (15, 20, 35 m/s) have been taken to show their effect on the wings vibrations suppression. Is noticed that the suppression of the wing amplitude is reduced when the wind velocity increases for both woven and random composite wing matt. This is happened due to the vortex which has became more violent increase in wind velocity. It is concluded that the composite woven wing has high resistance more than the composite random wing. Also, the maximum control amplitude of woven matt is 1.9 cm and the damping is about 33% at 25 m/s wind velocity while the amplitude is 2.22 cm and the damping is about 53% at 10 m/s wind velocity for random wing.

scholarly journals Independent Modal Variable Structure Fuzzy Active Vibration Control of Cylindrical Thin Shells Laminated with Photostrictive Actuators

2013 ◽  
Vol 20 (4) ◽  
pp. 693-709 ◽  
Author(s):  
R.B. He ◽  
S.J. Zheng ◽  
H.T. Wang
Keyword(s):  
Vibration Control ◽  
Vibration Suppression ◽  
Sliding Mode ◽  
Active Vibration Control ◽  
Flexible Structures ◽  
Variable Structure ◽  
Structure Control ◽  
Coupling Equations ◽  
Active Vibration ◽  
Control Forces

Photostrictive actuator, which can produce photodeformation strains under the activation of ultraviolet lights, is a new promising non-contact photoactuation technique for active vibration control of flexible structures. Generally, the membrane control action plays a major role in vibration control of flexible thin shell structures. However, it is unfortunate that the existing photostrictive actuator configuration can not induce negative membrane control forces. In this paper, a novel multi-layer actuator configuration is first presented to remedy this deficiency, followed by presenting the photostrictive/shell coupling equations of thin cylindrical shells laminated with the proposed multi-layer actuator configuration. Moreover, considering the time-variant and nonlinear dynamic characteristics of photostrictive actuator, variable structure self-adjusting parameter fuzzy active controller is explored to overcome disadvantages of conventional control schemes, in which off-line fuzzy control table is adopted. The optimal switching surface is derived to increase the range of sliding mode to facilitate vibration suppression. A continuous function is used to replace the sign function for reducing the variable structure control chattering. Finally, two case studies are carried out to evaluate the effectiveness of the proposed actuator configuration and the control scheme. Numerical simulation results demonstrate that the proposed actuator configuration is effective in shell actuation and control. It is also suggested that the proposed control strategy could give better control responses than the proportional velocity feedback.

ACTIVE VIBRATION CONTROL OF AN AIRCRAFT CABIN PANEL USING PIEZOELECTRIC SENSORS AND ACTUATORS

2003 ◽  
Vol 03 (01) ◽  
pp. 131-141 ◽  
Author(s):  
Y. Y. LEE ◽  
K. C. LAM ◽  
K. K. YUEN ◽  
H. F. LAM ◽  
J. YAO
Keyword(s):  
Vibration Control ◽  
Vibration Suppression ◽  
Active Vibration Control ◽  
Random Excitation ◽  
Piezoelectric Sensors ◽  
Mode Shapes ◽  
Sensors And Actuators ◽  
Aircraft Cabin ◽  
Piezoelectric Sensors And Actuators ◽  
Active Vibration

In this paper, the active vibration suppression of an aircraft cabin panel embedded with piezoelectric sensors and actuators under sinusoidal or random excitation is studied experimentally. The Independent Modal Space Control (IMSC) approach is employed in the controller design. The piezoelectric sensors and actuators associated with the IMSC technique have been applied to the active vibration control of the aircraft panel, and shown to be effective in vibration control. A second order controller is selected in the control scheme to suppress the fundamental modal vibration response of the aircraft cabin panel. The mode shapes of the panel are experimentally obtained, and used as the parameters of the objective functions for minimizing the unwanted vibration responses by appropriately selecting the sensor and actuator gains. Based on the experimental results, it is found that the vibration levels of the open and closed loop systems differ by up to 5.0 dB (for sinusoidal excitation) and 7.4 dB (for random excitation), even when the control circuit is interfered by electrical and magnetic noises.

Sign in / Sign up

Export Citation Format

Share Document