Linear and Nonlinear Aeroelastic Analysis of Fighter-Type Wing with Control Surface

2002 ◽  
Vol 39 (4) ◽  
pp. 697-708 ◽  
Author(s):  
Jae-Sung Bae ◽  
Seung-Man Yang ◽  
In Lee
Keyword(s):  
Control Surface ◽  
Aeroelastic Analysis ◽  
Linear And Nonlinear

Research and Application of Aeroelastic Analysis Based on Fluid-Structure Interaction

2014 ◽  
Vol 977 ◽  
pp. 418-422
Author(s):  
Rui Li ◽  
Chang Hong Tang
Keyword(s):  
Design Method ◽  
Fluid Structure Interaction ◽  
Nonlinear Aeroelasticity ◽  
Fluid Structure ◽  
Structure Interaction ◽  
Advantages And Disadvantages ◽  
Aeroelastic Analysis ◽  
Linear And Nonlinear ◽  
Development Orientation ◽  
Deforming Mesh

the origins and characteristics of linear and nonlinear aeroelasticity are analyzed.And the deforming mesh , fluid-structure coupling schemes, the design method of aerodynamic module and structure module interface are also analyzed. their advantages and disadvantages are Pointed out. Finally, several recommendations are given for the development orientation of aeroelasticity in the future.

Linear and Nonlinear Aeroelastic Analysis of a High Aspect Ratio Wing

2017 ◽  
Author(s):  
F. Bakhtiari-Nejad ◽  
A. H. Modarres ◽  
E. H. Dowell ◽  
H. Shahverdi
Keyword(s):  
Aspect Ratio ◽  
High Aspect Ratio ◽  
Structural Model ◽  
State Space Model ◽  
Beam Model ◽  
Aeroelastic Analysis ◽  
Structural Nonlinearities ◽  
Flutter Boundary ◽  
Linear And Nonlinear ◽  
Perturbation Equations

In this study, analysis and results of linear and nonlinear aeroelastic of a cantilever beam subjected to the airflow as a model of a high aspect ratio wing are presented. A third-order nonlinear beam model is used as structural model to take into account the effects of geometric structural nonlinearities. In order to model aerodynamic loads, Wagner state-space model has been used. Galerkin method is implemented to solve dynamic perturbation equations about a nonlinear static equilibrium state. The small perturbation flutter boundary is determined by these perturbation equations. The effect of geometric structural nonlinearity of the beam model on the flutter behavior is significant. As it is observed the system’s response to upper speed of flutter goes to limit cycle oscillations and also the oscillations lose periodicity and become chaotic.

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.

Stochastic Nonlinear Aeroelastic Analysis of a Swept Wing Based on Nastran

2013 ◽  
Vol 444-445 ◽  
pp. 738-742
Author(s):  
Yi Li ◽  
Jun Yang ◽  
Nan Chang
Keyword(s):  
Analytical Procedure ◽  
Risk Information ◽  
Free Play ◽  
Uncertain Parameter ◽  
Control Surface ◽  
Swept Wing ◽  
Aeroelastic Analysis

For both military and civil aircrafts are in service, there is always a variation of free play among the joint components of control due to wear. In fact, the variation of free play is an uncertain parameter. In this paper analytical procedure was developed basing on Nastran, which can quantify uncertainties in the complicated swept wing with control surface and gives the quantificational risk information about nonlinear aeroelstic stability in the practice.

Linear and nonlinear aeroelastic analysis frameworks for cable-supported bridges

2013 ◽  
Vol 74 (3) ◽  
pp. 487-516 ◽  
Author(s):  
Teng Wu ◽  
Ahsan Kareem ◽  
Yaojun Ge
Keyword(s):  
Aeroelastic Analysis ◽  
Linear And Nonlinear
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