Panel flutter suppression using adaptive material actuators

1994 ◽  
Vol 31 (1) ◽  
pp. 213-222 ◽  
Author(s):  
R. C. Scott ◽  
T. A. Weisshaar
Keyword(s):  
Panel Flutter ◽  
Flutter Suppression

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.

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.

Supersonic Nonlinear Panel Flutter Suppression Using Shape Memory Alloys

2007 ◽  
Vol 44 (4) ◽  
pp. 1139-1149 ◽  
Author(s):  
Xinyun Guo ◽  
Yiu-Yin Lee ◽  
Chuh Mei
Keyword(s):  
Shape Memory Alloys ◽  
Shape Memory ◽  
Panel Flutter ◽  
Flutter Suppression ◽  
Nonlinear Panel Flutter

Analysis of Curved Panel Flutter in Supersonic and Transonic Airflows Using a Fluid–Structure Coupling Algorithm

2017 ◽  
Vol 139 (4) ◽  
Author(s):  
Guanhua Mei ◽  
Jiazhong Zhang ◽  
Can Kang
Keyword(s):  
Dynamic Pressure ◽  
Stable State ◽  
Aerodynamic Load ◽  
Panel Flutter ◽  
Governing Equations ◽  
Fluid Structure ◽  
Flutter Suppression ◽  
Flight Vehicles ◽  
Curved Panel ◽  
Coupling Algorithm

In order to accurately study the effect of curvature on panel aeroelastic behaviors, a fluid–structure coupling algorithm is adopted to analyze the curved panel flutter in transonic and supersonic airflows. First, the governing equation for the motion of the curved panel and the structure solver are presented. Then, the fluid governing equations, the fluid solver, and the fluid–structure coupling algorithm are introduced briefly. Finally, rich aeroelastic responses of the curved panel are captured using this algorithm. And the mechanisms of them are explored by various analysis tools. It is found that the curvature produces initial aerodynamic loads above the panel. Thus, the static aeroelastic deformation exists for the curved panel in stable state. At Mach 2, with its stability lost on this static aeroelastic deformation, the curved panel shows asymmetric flutter. At Mach 0.8 and 0.9, the curved panel exhibits only positive static aeroelastic deformation due to this initial aerodynamic load. At Mach 1.0, as the dynamic pressure increases, the curved panel loses its static and dynamic stability in succession, and behaves as static aeroelastic deformations, divergences, and flutter consequentially. At Mach 1.2, with its stability lost, the curved panel flutters more violently toward the negative direction. The results obtained could guide the panel design and panel flutter suppression for flight vehicles with high performances.

Active panel flutter suppression using self-sensing piezoactuators

AIAA Journal ◽  
1996 ◽  
Vol 34 (6) ◽  
pp. 1224-1230 ◽  
Author(s):  
F. Dongi ◽  
D. Dinkler ◽  
B. Kroeplin
Keyword(s):  
Panel Flutter ◽  
Flutter Suppression
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