Nonlinear aeroelastic analysis of an airfoil with control surface free-play using stochastic approach

2017 ◽  
Vol 72 ◽  
pp. 114-126 ◽  
Author(s):  
Saeid Sazesh ◽  
Shahrokh Shams
Keyword(s):  
Stochastic Approach ◽  
Free Play ◽  
Control Surface ◽  
Aeroelastic Analysis

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.

Transonic Aeroelastic Analysis of All-Movable Wing with Free Play and Viscous Effects

2008 ◽  
Vol 45 (5) ◽  
pp. 1820-1824 ◽  
Author(s):  
Jong-Yun Kim ◽  
Kyung-Seok Kim ◽  
In Lee ◽  
Young-Keun Park
Keyword(s):  
Free Play ◽  
Viscous Effects ◽  
Aeroelastic Analysis

Modeling and characterization of the impact of control surface free-play on flutter for an all moving surface

2012 ◽  
Author(s):  
C. E. Whitmer ◽  
A. G. Kelkar ◽  
J. M. Vogel ◽  
D. Chaussee ◽  
C. Ford ◽  
...  
Keyword(s):  
Free Play ◽  
Control Surface ◽  
Moving Surface ◽  
The Impact

Nonlinear Dynamics of Aeroelastic Systems

2000 ◽  
Author(s):  
Earl H. Dowell
Keyword(s):  
Wind Tunnel ◽  
Delta Wing ◽  
Free Play ◽  
Physical Models ◽  
Forced Oscillations ◽  
Control Surface ◽  
Dynamical Response ◽  
Wind Tunnel Experiments ◽  
Nonlinear Dynamical ◽  
Flight Regimes

Abstract Aeroelastic systems are those that involve the coupled interaction between a convecting fluid and a flexible elastic structure. The nonlinear dynamical response of such systems is of great current interest. Existing aircraft are known to encounter limit cycle oscillations (LCO) in certain flight regimes, and relatively simple experimental wind tunnel models have been designed to exhibit LCO as well. In the present paper, the results of these wind tunnel experiments are discussed and compared to comparable results from mathematical models. The physical models include (1) an airfoil and a control surface attached with an elastic spring including free-play and (2) a delta wing with elastic geometrical nonlinearities due to bending and torsional deformations. Both self-excited oscillations such as flutter and LCO, as well as forced oscillations due to an aerodynamic gust, are discussed. The advantages of representing the unsteady aerodynamic flow field in terms of global modes for such studies are emphasized and illustrated.

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

Characterization of typical aeroelastic sections under combined structural concentrated nonlinearities

2021 ◽  
pp. 107754632110001
Author(s):  
José Augusto I da Silva ◽  
Flávio D Marques
Keyword(s):  
Time Integration ◽  
Unsteady Aerodynamics ◽  
Nonlinear Effects ◽  
Free Play ◽  
Control Surface ◽  
Trailing Edge ◽  
Aeroelastic System ◽  
Practical Applications ◽  
Structural Nonlinearities ◽  
The Stability

Structural nonlinearities are usually present in aeroelastic systems. The analysis of this system commonly comprises a study involving only one type of nonlinearity, influencing a particular motion of the airfoil. However, practical applications of aeroelastic systems can be affected by different types of structural nonlinearities. It becomes essential to study the stability of the aeroelastic system under these conditions to assess more real operational flight procedures. In this context, this article presents an investigation of a typical aeroelastic section response with trailing edge control surface subjected to combinations of concentrated structural nonlinearities. Different nonlinear scenarios involving cubic hardening stiffness in pitching and free play, free play with preload, and slip dry friction in the trailing edge control surface motion are analyzed. The mathematical model is based on linear unsteady aerodynamics coupled to a three-dof typical aeroelastic section. Hopf bifurcations diagrams are obtained from direct time integration of the equation of motion. The post-flutter limit cycle oscillations are investigated, revealing supercritical and subcritical bifurcations. A complete parametric study of the nonlinear parameters is carried out, thereby allowing a sensitivity analysis of each nonlinear scenario. The results show that aeroelastic tailoring considering the mild post-flutter behavior can be achieved through an appropriate choice of combined nonlinear effects. Moreover, combined nonlinearities can mitigate the undesired subcritical aeroelastic responses caused by free play.

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