Design and test of a multi-input multi-output adaptive active flutter suppression system based on neural network for a wing model

1999 ◽  
Vol 6 (1) ◽  
pp. 129-143
Author(s):  
M. Rendina ◽  
G. Mazzoni
Keyword(s):  
Neural Network ◽  
Flutter Suppression ◽  
Wing Model ◽  
Active Flutter Suppression ◽  
Suppression System

A neural network approach for improving airfoil active flutter suppression under control-input constraints

2020 ◽  
pp. 107754632092915
Author(s):  
Difan Tang ◽  
Lei Chen ◽  
Zhao F Tian ◽  
Eric Hu
Keyword(s):  
Neural Network ◽  
Optimal Control ◽  
Function Approximation ◽  
Value Function ◽  
Control Input ◽  
Input Constraints ◽  
Value Function Approximation ◽  
Flutter Suppression ◽  
Active Flutter Suppression ◽  
Parameter Varying

This study deals with improving airfoil active flutter suppression under control-input constraints from the optimal control perspective by proposing a novel optimal neural-network control. The proposed approach uses a modified value function approximation dynamically tuned by an extended Kalman filter to solve the Hamilton–Jacobi–Bellman equality online for continuously improved optimal control to address optimality in parameter-varying nonlinear systems. Control-input constraints are integrated into the controller synthesis by introducing a generalized nonquadratic cost function for control inputs. The feasibility of using a performance index involving the nonquadratic control-input cost with the modified value function approximation is examined through the Lyapunov stability analysis. Wind tunnel experiments were conducted for controller validation, where an optimal controller synthesized offline via linear parameter-varying technique was used as a benchmark and compared. It is shown, both theoretically and experimentally, that the proposed method can effectively improve airfoil active flutter suppression under control-input constraints.

Time-Domain Aeroservoelastic Modeling and Active Flutter Suppression by Model Predictive Control

2014 ◽  
Vol 898 ◽  
pp. 688-695
Author(s):  
Zhi Wei Sun ◽  
Jun Qiang Bai
Keyword(s):  
Control Theory ◽  
Model Predictive Control ◽  
Predictive Control ◽  
Time Domain ◽  
Loop Analysis ◽  
Flutter Suppression ◽  
Flutter Speed ◽  
Active Flutter Suppression ◽  
Induced Flow ◽  
Suppression System

A time-domain aeroservoelastic model is developed to calculate the flutter speed and an active flutter suppression system is designed by model predictive control. The finite-state, induced-flow theory and equilibrium beam finite element method are chosen to formulate the aeroservoelastic governing equations in state-space form, which is necessary for active flutter suppression design with modern control theory. A sensitivity analysis is performed to find the most appropriate number of induced-flow terms and beam elements. Model predictive control theory is adopted to design an active flutter suppression system due to its ability to deal with the constraints on rate change and amplitude of input. The numerical result shows a satisfactory precision of the flutter speed prediction, the close loop analysis shows that the flutter boundary is considerable expanded.

Design of an active flutter suppression system

1986 ◽  
Vol 9 (1) ◽  
pp. 64-71 ◽  
Author(s):  
Bradley S. Liebst ◽  
William L. Garrard ◽  
William M. Adams
Keyword(s):  
Flutter Suppression ◽  
Active Flutter Suppression ◽  
Suppression System

Recent Development of the YF-17 Active Flutter Suppression System

1981 ◽  
Vol 18 (7) ◽  
pp. 537-545 ◽  
Author(s):  
C. Hwang ◽  
E.H. Johnson ◽  
W.S. Pi
Keyword(s):  
Flutter Suppression ◽  
Active Flutter Suppression ◽  
Suppression System

Group Delay in Digital Filter Induced Instability of a Two-Dimensional Airfoil Active Flutter Suppression System

2012 ◽  
Vol 226-228 ◽  
pp. 64-69
Author(s):  
Ming Li Yu
Keyword(s):  
Wind Tunnel ◽  
Digital Filter ◽  
Group Delay ◽  
Numerical Study ◽  
Wind Tunnel Test ◽  
Control Surface ◽  
Two Dimensional ◽  
Flutter Suppression ◽  
Active Flutter Suppression ◽  
Suppression System

The presented paper deals with the group delay in the digital filter induced instability of a two dimensional airfoil section active flutter suppression system. Firstly, the aeroelastic model of the airfoil with an ultrasonic motor actuated control surface is set up; secondly, both H∞and μ robust controllers are designed; and then, the group delay induced instability in wind tunnel test is presented; finally, through a combined theoretical and numerical study, the test phenomenon is well explained. Wind tunnel experiments and numerical simulations demonstrate that long enough group delay in digital filter can induce instability of flutter control system, the flutter under control will decrease first, and then become another flutter of lower frequency and moderated amplitude, and μ controller works better than H∞controller on the same condition.

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