A Comprehensive Approach for the Optimal Control of Tiltrotor Cabin Noise Through Actively-Driven Piezoelectric Actuators

2013 ◽  
Author(s):  
Giovanni Bernardini ◽  
Claudio Testa ◽  
Marco Molica Colella ◽  
M. Gennaretti
Keyword(s):  
Optimal Control ◽  
Piezoelectric Actuators ◽  
Comprehensive Approach ◽  
Cabin Noise

Integration of Bilinear Systems and Neural Networks for Designing Nonlinear Semi-Active Suspensions

1995 ◽  
Vol 7 (4) ◽  
pp. 295-300 ◽  
Author(s):  
Antonio Moran ◽  
◽  
Tomohiro Hasegawa ◽  
Masao Nagai
Keyword(s):  
Neural Networks ◽  
Optimal Control ◽  
Design Method ◽  
Piezoelectric Actuators ◽  
Active Suspension ◽  
Bilinear Systems ◽  
Active Suspensions ◽  
Suspension Model ◽  
Nonlinear Components

This paper presents a new design method of semi-active suspensions based on the integration of neural networks and bilinear systems. It is known that semi-active suspensions with ideal linear components have a bilinear structure. However actual semi-active suspensions with nonlinear components have an structure which is not purely bilinear. In order to improve the performance of semi-active suspensions, neural networks and bilinear systems are integrated and used for the identification and optimal control of nonlinear semi-active suspensions. The validity and applicability of the proposed method are analyzed and verified theoretically and experimentally using a semi-active suspension model equipped with piezoelectric actuators.

Vibroacoustic modeling of the control of aircraft cabin noise using piezoelectric actuators

1998 ◽  
Author(s):  
Anant K. Grewal ◽  
Lacramioara Pavel ◽  
David G. Zimcik ◽  
Robby Lapointe
Keyword(s):  
Piezoelectric Actuators ◽  
Aircraft Cabin ◽  
Cabin Noise

Vibration Optimal Control of a Smart Plate with Input Voltage Constraint of Piezoelectric Actuators

2004 ◽  
Vol 10 (12) ◽  
pp. 1749-1774 ◽  
Author(s):  
F. Bakhtiari-Nejad ◽  
M. Meidan-Sharafi
Keyword(s):  
Optimal Control ◽  
Minimum Principle ◽  
Piezoelectric Actuators ◽  
Input Voltage ◽  
Mode Shapes ◽  
Control Procedure ◽  
Plate Vibration ◽  
Allowable Limit ◽  
Forcing Function ◽  
Assumed Mode

A nonlinear optimal control of a plate vibration is developed. Three pairs of piezoelectric patches with limited voltages input are used as a source of applying an active forcing function to control the vibration of the plate. The dynamic model of the plate with piezoelectric actuators is applied for the purpose of analyzing the coupling between piezoelectric actuators and a plate. The model is based on discrete assumed mode shapes of different beams. To keep the voltages of any pair of actuators in their allowable limits, the optimal control procedure presented in this paper shows that the voltage of other piezoelectric actuators that are in the allowable limit would also be affected. Therefore, the Pontryogan minimum principle is not enough for systems with multi inequality constrained of control inputs.

Aircraft Cabin Tonal Noise Alleviation Through Fuselage Skin Embedded Piezoelectric Actuators

2011 ◽  
Vol 133 (5) ◽  
Author(s):  
C. Testa ◽  
G. Bernardini ◽  
M. Gennaretti
Keyword(s):  
Piezoelectric Actuators ◽  
Point Sources ◽  
General Aviation ◽  
Sound Waves ◽  
Control Approach ◽  
System A ◽  
Cabin Noise ◽  
Fuselage Skin ◽  
And Control ◽  
General Aviation Aircraft

An integrated spectral-integral formulation is applied for prediction and active control of the noise generated by propellers inside the cabin of a general aviation aircraft. It consists of a multidisciplinary approach that involves interaction among exterior noise field, elastic fuselage dynamics, interior acoustics, and control system. A fuselage skin embedding piezoelectric elements is supposed to be impinged by external sound waves generated by propellers. An optimal harmonic control approach is applied for the actuation of the piezoelectric patches, aimed at alleviating the corresponding cabin noise. The aeroacoustoelastic plant model considered in the control problem is obtained by combining modal approaches for the description of cabin acoustic field and fuselage shell dynamics, with a boundary element method scattering formulation for the prediction of exterior pressure disturbances. Considering the fuselage of a general aviation aircraft impinged by noise generated by a couple of pulsating point sources moving with it, numerical results examine the effectiveness of the control approach applied to several configurations of piezoelectric actuators.

Modal optimal control of cabin noise of vehicles

2004 ◽  
Vol 14 (1) ◽  
pp. 257-264 ◽  
Author(s):  
Su Huan Chen ◽  
Xue Wei Song ◽  
Zhi Jun Yang
Keyword(s):  
Optimal Control ◽  
Cabin Noise
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