Limit Cycle Flutter Analysis of a High-Aspect-Ratio Wing with an External Store

Limit cycle flutter analysis of a high-aspect-ratiowing with an external store is presented. The concentrated store mass iscombined into the governing equations which are obtained using the extendedHamilton’s principle. The high-aspect-ratio wing structural model, which alsoconsiders the in-plane bending motion, is used. Three possible nonlinearitiesare considered including structural nonlinearities, aerodynamic nonlinearities,and store nonlinearities. Time simulation and bifurcation diagrams areperformed to analysis systems with three nonlinearities.

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Transonic Limit Cycle Flutter of High-Aspect-Ratio Swept Wings

Journal of Aircraft ◽

10.2514/1.29547 ◽

2008 ◽

Vol 45 (5) ◽

pp. 1522-1533 ◽

Cited By ~ 30

Author(s):

Oddvar O. Bendiksen

Keyword(s):

Aspect Ratio ◽

Limit Cycle ◽

High Aspect Ratio ◽

Limit Cycle Flutter ◽

Swept Wings

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Linear and Nonlinear Aeroelastic Analysis of a High Aspect Ratio Wing

Volume 8: 29th Conference on Mechanical Vibration and Noise ◽

10.1115/detc2017-67289 ◽

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.

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Effects of Aeroelastic Nonlinearity on Flutter and Limit Cycle Oscillations of High-Aspect-Ratio Wings

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.110-116.4297 ◽

2011 ◽

Vol 110-116 ◽

pp. 4297-4306 ◽

Cited By ~ 1

Author(s):

Keivan Eskandary ◽

Morteza Dardel ◽

Mohammad Hadi Pashaei ◽

Abdol Majid Kani

Keyword(s):

Aspect Ratio ◽

Limit Cycle ◽

High Aspect Ratio ◽

Large Deflection ◽

Limit Cycle Oscillation ◽

Low Velocity ◽

Wing Model ◽

Structural Nonlinearities ◽

Cycle Oscillation ◽

Compressibility Effects

In this study aeroelastic characteristics of long high aspect ratio wing models with structural nonlinearities in quasi-steady aerodynamics flows are investigated. The studied wing model is a cantilever wing with double bending and torsional vibrations and with large deflection ability in according to Dowell-Hodges wing model. This wing model is valid for long, straight and thin homogeneous isotropic beams. Aerodynamics model is based on quasi-steady aerodynamic which is valid for aerodynamic flows in low velocity and without wake, viscosity and compressibility effects. The effect of different parameters such as mass ratios and stiffness ratios on flutter and divergence velocities and limit cycle oscillation amplitudes are carefully studied.

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Transonic Limit Cycle Flutter of High-Aspect-Ratio Swept Wings

47th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference<BR> 14th AIAA/ASME/AHS Adaptive Structures Conference<BR> 7th ◽

10.2514/6.2006-1635 ◽

2006 ◽

Cited By ~ 3

Author(s):

Oddvar Bendiksen

Keyword(s):

Aspect Ratio ◽

Limit Cycle ◽

High Aspect Ratio ◽

Limit Cycle Flutter ◽

Swept Wings

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The Effect of Structural Geometric Nonlinearities on the Flutter of the Straight and Swept Wing Configurations

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.189.306 ◽

2012 ◽

Vol 189 ◽

pp. 306-311 ◽

Cited By ~ 2

Author(s):

Qing Guo ◽

Bi Feng Song

Keyword(s):

Aspect Ratio ◽

High Aspect Ratio ◽

Swept Wing ◽

Geometric Nonlinearities ◽

Air Vehicle ◽

Structural Nonlinearity ◽

Flutter Analysis ◽

Long Endurance ◽

The Impact ◽

Straight Wing

High altitude and long endurance (HALE) vehicle always adopt straight or swept configuration, which leads to the problem that the wings of UAV have high aspect ratio and are very flexible. This kind of flexible wing exhibits large deformation when aerodynamic forces are loaded on them and the structural nonlinearity should be considered. So the dynamic and flutter characteristics will be changed. In the engineering applications, the effects of structural geometric nonlinearities on the air vehicle design are the most concerns of aeroelasticity before a systematic flutter analysis for the air vehicle. because the solution for nonlinear flutter speed based on the CFD-CSD method is complex and time consuming. In this paper, we propose a simple and efficient approach that can analyze the effect of structural geometric nonlinearities on the flutter characteristics of high aspect ratio wing quickly. And a straight wing and a straight-swept wing are analyzed to verify the feasibility and efficiency of the proposed method. It is found that the effect of structural geometric nonlinearities has a strong effect on the flutter characteristic of the straight wing, but is weak on the straight-swept wing. And finally the impact of swept angle on the dynamic and flutter characteristics of straight-swept wing is also discussed.

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Limit Cycle Flutter Analysis of Plate-Type Beam with Dissymmetrical Subsection Linear Stiffness

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.66-68.1732 ◽

2011 ◽

Vol 66-68 ◽

pp. 1732-1737

Author(s):

Li Lu ◽

Yi Ren Yang ◽

Chen Guang Fan ◽

Ming Lu Zhang

Keyword(s):

Galerkin Method ◽

Viscous Flow ◽

Limit Cycle ◽

Equivalent Linearization ◽

Incompressible Viscous Flow ◽

Flutter Analysis ◽

Limit Cycle Flutter ◽

The Stability ◽

Theoretical Results ◽

Plate Type

The limit cycle flutter of a plate-type structure with dissymmetrical subsection linear stiffness in incompressible viscous flow was studied. Galerkin Method was used to get the differential equations of system. The equivalent linearization concept was performed to predict the ranges of limit cycle flutter velocities. The flutter borderline map was used to analyze the the stability of limit cycle flutter. By numerical integrating, the velocities of convergence, flutter and instability were obtained. The theoretical results agree well with the results of numerical integration.

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