A Method of Panel Flutter Suppression and Elimination for Aeroelastic Structures in Supersonic Airflow

2018 ◽  
Vol 140 (6) ◽  
Author(s):  
Zhi-Guang Song ◽  
Tian-Zhi Yang ◽  
Feng-Ming Li ◽  
Erasmo Carrera ◽  
Peter Hagedorn
Keyword(s):  
Natural Frequency ◽  
Active Control ◽  
Stiffness Matrix ◽  
Control Method ◽  
Plate Theory ◽  
Piezoelectric Materials ◽  
Panel Flutter ◽  
Structural System ◽  
Flutter Suppression ◽  
Control Forces

In traditional active flutter control, piezoelectric materials are used to increase the stiffness of the aeroelastic structure by providing an active stiffness, and usually the active stiffness matrix is symmetric. That is to say that the active stiffness not only cannot offset the influence of the aerodynamic stiffness which is an asymmetric matrix, but also will affect the natural frequency of the structural system. In other words, by traditional active flutter control method, the flutter bound can just be moved backward but cannot be eliminated. In this investigation, a new active flutter control method which can suppress the flutter effectively and without affecting the natural frequency of the structural system is proposed by exerting active control forces on some discrete points of the structure. In the structural modeling, the Kirchhoff plate theory and supersonic piston theory are applied. From the numerical results, it can be noted that the present control method is effective on the flutter suppression, and the control effects will be better if more active control forces are exerted. After being controlled by the present control method, the natural frequency of the structure remains unchanged.

Active control of composite panel flutter using piezoelectric materials

1993 ◽  
Author(s):  
Derek A. Paige ◽  
Robert C. Scott ◽  
Terrence A. Weisshaar
Keyword(s):  
Active Control ◽  
Piezoelectric Materials ◽  
Composite Panel ◽  
Panel Flutter

Identification and Control of Rotating Disk Vibration

1983 ◽  
Vol 105 (1) ◽  
pp. 39-45 ◽  
Author(s):  
C. J. Radcliffe ◽  
C. D. Mote
Keyword(s):  
Active Control ◽  
Control Method ◽  
Travelling Waves ◽  
Circular Disk ◽  
Rotating Disk ◽  
Dominant Mode ◽  
Transverse Motion ◽  
Modal Amplitude ◽  
On Line ◽  
Control Forces

Small amplitude, transverse vibration of a circular disk can be viewed as a superposition of travelling waves each wave corresponding to a particular vibration mode. When the plate damping is small, the transverse motion of the plate is often dominated by response in one mode [1]. The active control method discussed here used an on-line FFT analysis of the rotating disk displacement to periodically identify the dominant mode of the disk response in a changing operating environment. Active control forces were applied electromagnetically to the disk to suppress the amplitude of that particular mode. In laboratory tests, the prototype controller reduced the modal amplitude to less than 15 percent of the uncontrolled value. Analytical predictions correlated well with these laboratory observations.

A Feedback Linearization Approach for Panel Flutter Suppression With Piezoelectric Actuation

2010 ◽  
Vol 6 (3) ◽  
Author(s):  
Oluseyi O. Onawola ◽  
S. C. Sinha
Keyword(s):  
Feedback Control ◽  
Electric Fields ◽  
Feedback Linearization ◽  
Plate Theory ◽  
Nonlinear Partial Differential Equation ◽  
Control Panel ◽  
Panel Flutter ◽  
Piezoelectric Actuation ◽  
Nonlinear Feedback ◽  
Flutter Suppression

Panel flutter suppression by exact state transformations and feedback control using piezoelectric actuation is presented. A nonlinear control system is designed for a simply supported rectangular panel with bonded piezoelectric layers based on the von Kármán large-deflection plate theory. The governing nonlinear partial differential equation for the panel is reduced to a set of ordinary differential equations using a two mode approximation. Distributed piezoelectric actuators and sensors connected to processing networks are used as modal actuators and sensors to actively control panel vibrations. The control inputs are given by the electric fields required to drive the actuators based on piezoelectric actuation. Nonlinear feedback control laws are formulated through a transformation of the discretized nonlinear system into an equivalent controllable linear system. The simulated results show that the resulting closed-loop system based on feedback linearized controllers effectively suppress panel flutter limit-cycle motions.

scholarly journals Maximum Damping of the Lowest Room Eigenfrequency by a Monopole

2020 ◽  
Vol 320 ◽  
pp. 00026
Author(s):  
Darya Mameshina ◽  
Nikolay Kanev
Keyword(s):  
Natural Frequency ◽  
Active Control ◽  
Sound Absorption ◽  
Control Method ◽  
Absorption Efficiency ◽  
Free Oscillations ◽  
Damping Coefficients ◽  
Rigid Walls ◽  
Rectangular Room ◽  
Active Control Method

In this paper, we consider the problem of sound absorption by a monopole in a rectangular room with absolutely rigid walls. The absorption efficiency is characterized by the damping coefficients of free oscillations of the “monopole-room” system. The impedance of the monopole is found, at which the damping coefficient of the resonance of the system with the lowest natural frequency is maximum. The monopole with this impedance can be realized using an active control method that allows the required impedance to be achieved over a wide frequency band.

A Feedback Linearization Approach for Panel Flutter Suppression With Piezoelectric Actuation

2009 ◽  
Author(s):  
Oluseyi O. Onawola ◽  
S. C. Sinha
Keyword(s):  
Feedback Control ◽  
Electric Fields ◽  
Feedback Linearization ◽  
Plate Theory ◽  
Nonlinear Partial Differential Equation ◽  
Control Panel ◽  
Panel Flutter ◽  
Piezoelectric Actuation ◽  
Nonlinear Feedback ◽  
Flutter Suppression

Panel flutter suppression by exact state transformations and feedback control using piezoelectric actuation is presented. A nonlinear control system is formulated for the nonlinear partial differential equation governing the dynamics of a simply supported rectangular panel with bonded piezoelectric layers based on the von Ka´rman large-deflection plate theory. Distributed piezoelectric actuators and sensors connected to processing networks are used as modal actuators and sensors to actively control panel vibrations. The control inputs are given by the electric fields required to drive the actuators based on piezoelectric actuation. Nonlinear feedback control laws are formulated through a transformation of the nonlinear system into an equivalent controllable linear system. The simulated results show that the resulting closed-loop system based on feedback linearized controllers effectively suppress panel flutter limit-cycle motions.

scholarly journals A Critical Review of Supersonic Flow Control for High-Speed Applications

2021 ◽  
Vol 11 (15) ◽  
pp. 6899
Author(s):  
Abdul Aabid ◽  
Sher Afghan Khan ◽  
Muneer Baig
Keyword(s):  
Supersonic Flow ◽  
Flow Control ◽  
Active Control ◽  
Critical Review ◽  
High Speed ◽  
Passive Control ◽  
Control Method ◽  
Sudden Expansion ◽  
Control Approach ◽  
Cost Efficient

In high-speed fluid dynamics, base pressure controls find many engineering applications, such as in the automobile and defense industries. Several studies have been reported on flow control with sudden expansion duct. Passive control was found to be more beneficial in the last four decades and is used in devices such as cavities, ribs, aerospikes, etc., but these need additional control mechanics and objects to control the flow. Therefore, in the last two decades, the active control method has been used via a microjet controller at the base region of the suddenly expanded duct of the convergent–divergent (CD) nozzle to control the flow, which was found to be a cost-efficient and energy-saving method. Hence, in this paper, a systemic literature review is conducted to investigate the research gap by reviewing the exhaustive work on the active control of high-speed aerodynamic flows from the nozzle as the major focus. Additionally, a basic idea about the nozzle and its configuration is discussed, and the passive control method for the control of flow, jet and noise are represented in order to investigate the existing contributions in supersonic speed applications. A critical review of the last two decades considering the challenges and limitations in this field is expressed. As a contribution, some major and minor gaps are introduced, and we plot the research trends in this field. As a result, this review can serve as guidance and an opportunity for scholars who want to use an active control approach via microjets for supersonic flow problems.

scholarly journals Structural Health Monitoring of 2D Plane Structures

2021 ◽  
Vol 11 (5) ◽  
pp. 2000
Author(s):  
Behnam Mobaraki ◽  
Haiying Ma ◽  
Jose Antonio Lozano Galant ◽  
Jose Turmo
Keyword(s):  
Mechanical Properties ◽  
Health Monitoring ◽  
Mathematical Analysis ◽  
Stiffness Matrix ◽  
State Of The Art ◽  
System Of Equations ◽  
Matrix System ◽  
Structural System ◽  
Detailed Mathematical Analysis ◽  
Structural System Identification

This paper presents the application of the observability technique for the structural system identification of 2D models. Unlike previous applications of this method, unknown variables appear both in the numerator and the denominator of the stiffness matrix system, making the problem non-linear and impossible to solve. To fill this gap, new changes in variables are proposed to linearize the system of equations. In addition, to illustrate the application of the proposed procedure into the observability method, a detailed mathematical analysis is presented. Finally, to validate the applicability of the method, the mechanical properties of a state-of-the-art plate are numerically determined.

Structural Control Considering Time Delay Effect

1985 ◽  
Vol 9 (4) ◽  
pp. 224-227 ◽  
Author(s):  
Mohamed Abdel-Rohman
Keyword(s):  
Time Delay ◽  
Active Control ◽  
Theoretical Consideration ◽  
Structural Control ◽  
Control Mechanism ◽  
Structural Response ◽  
Delay Effect ◽  
Numerical Example ◽  
Control Forces ◽  
Time Delay Effect

The time delay between measuring the structural response, and applying the designed active control forces may affect the controlled response of the structure if not taken into consideration. In this paper it is shown how to design the control forces to compensate for the delay effect. It is also shown that the time delay effect can be used as a criterion to judge the effectiveness of the proposed control mechanism. As an illustration of the theoretical consideration, a numerical example in which a tall building is controlled by means of active tendons is presented.

Sign in / Sign up

Export Citation Format

Share Document