Limit cycle oscillation behavior of transonic control surface buzz considering free-play nonlinearity

2016 ◽  
Vol 61 ◽  
pp. 431-449 ◽  
Author(s):  
Shun He ◽  
Zhichun Yang ◽  
Yingsong Gu
Keyword(s):  
Limit Cycle ◽  
Free Play ◽  
Control Surface ◽  
Limit Cycle Oscillation ◽  
Cycle Oscillation

Nonlinear Aeroelastic Characteristics of a Fighter-Type Wing With Control Surface

2002 ◽  
Author(s):  
Jae-Sung Bae ◽  
In Lee
Keyword(s):  
Limit Cycle ◽  
Chaotic Motion ◽  
Free Play ◽  
Control Surface ◽  
Limit Cycle Oscillation ◽  
Nonlinear Flutter ◽  
Wide Range ◽  
Flutter Boundary ◽  
Linear And Nonlinear ◽  
Cycle Oscillation

The nonlinear aeroelastic characteristics of a fighter-type wing with control surface have been investigated. The fictitious mass modal approach is used to reduce the problem size and the computation time in the linear and nonlinear flutter analyses. A Doublet-Hybrid method are used for the computation of subsonic unsteady aerodynamic forces. Structural nonlinearity of the control surface hinge is represented by a free-play spring. The linear and nonlinear flutter analyses indicate that the flapping mode of control surface and the hinge stiffness have significant effects on the flutter characteristics. The nonlinear flutter analysis shows that limit cycle oscillation and chaotic motion are observed in the wide range of air speed below the linear flutter boundary and the jump of limit cycle oscillation amplitude is observed. The nonlinear flutter characteristics and the nonlinear flutter boundary of limit cycle oscillation and chaotic motion have been investigated.

Investigation of Missile Control Surface Effects on F-16 Limit-Cycle Oscillation

2015 ◽  
Vol 52 (2) ◽  
pp. 462-470 ◽  
Author(s):  
Colin Q. Hanson ◽  
Donald L. Kunz ◽  
Ned J. Lindsley
Keyword(s):  
Limit Cycle ◽  
Surface Effects ◽  
Control Surface ◽  
Limit Cycle Oscillation ◽  
Cycle Oscillation

Fuzzy control of nonlinear aeroelastic system based on neural network identification

2021 ◽  
pp. 095441002110109
Author(s):  
Bo Zhang ◽  
Jing-Long Han ◽  
Hai-Wei Yun ◽  
Xiao-Mao Chen
Keyword(s):  
Neural Network ◽  
Fuzzy Control ◽  
Control Method ◽  
Free Play ◽  
Control Surface ◽  
Limit Cycle Oscillation ◽  
Identification Algorithm ◽  
Aeroelastic System ◽  
Network Identification ◽  
Cycle Oscillation

This article presents a fuzzy control method for the limit cycle oscillation (LCO) suppression of nonlinear aeroelastic systems based on the neural network identification algorithm. A prototypical 2D wing section with a single control surface at the trailing edge of the main wing, which contains a symmetrical free play nonlinearity in the pitch degree of freedom, is modeled to illustrate the proposed method. A neural network is used to identify the fuzzy control rules from the existing LCO suppression input and output data. A new fuzzy control rate of the nonlinear aeroelastic system is obtained by adjusting the parameters of the fuzzy control surface. Numerical simulations are conducted to verify the effectiveness of the proposed method.

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