Efficient Method for Limit Cycle Flutter Analysis Based on Nonlinear Aerodynamic Reduced-Order Models

AIAA Journal ◽  
2012 ◽  
Vol 50 (5) ◽  
pp. 1019-1028 ◽  
Author(s):  
Weiwei Zhang ◽  
Bobin Wang ◽  
Zhengyin Ye ◽  
Jingge Quan
Keyword(s):  
Limit Cycle ◽  
Efficient Method ◽  
Reduced Order Models ◽  
Reduced Order ◽  
Flutter Analysis ◽  
Limit Cycle Flutter ◽  
Nonlinear Aerodynamic

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

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.

Whirl flutter analysis of prop-rotors using unsteady aerodynamics reduced-order models

2008 ◽  
Vol 112 (1131) ◽  
pp. 261-270 ◽  
Author(s):  
M. Gennaretti ◽  
L. Greco
Keyword(s):  
Unsteady Aerodynamics ◽  
Alignment Algorithm ◽  
Reduced Order Models ◽  
Reduced Order ◽  
Flutter Analysis ◽  
Numerical Tools ◽  
Whirl Flutter ◽  
Aerodynamic Modelling ◽  
And Control ◽  
Wake Alignment

Abstract The prediction of this aeroelastic phenomenon is an urgent need of the designer and requires devoted numerical tools. This work examines the influence of the accuracy of the aerodynamic modelling on whirl flutter analysis, with particular attention to those models that can conveniently be applied to preliminary design and control purposes. Considering a simple pylon/prop-rotor structure, the aeroelastic instability boundaries are identified by 2D quasi-steady and 2D unsteady aerodynamics theories, along with a 3D unsteady, potential flow BEM solver. A methodology for deriving reduced-order models from unsteady aerodynamic solutions is used. The numerical investigation highlights that the accuracy of the aerodynamic solver included in the analysis may be of crucial importance. The use of 2D aerodynamic models does not always guarantee conservative stability predictions, and this is particularly true for three-bladed rotors where a fully 3D unsteady solver coupled with a wake alignment algorithm seems to be necessary.

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

2014 ◽  
Vol 912-914 ◽  
pp. 907-910 ◽  
Author(s):  
Jun Xu ◽  
Xiao Ping Ma
Keyword(s):  
Aspect Ratio ◽  
Limit Cycle ◽  
High Aspect Ratio ◽  
Structural Model ◽  
Bifurcation Diagrams ◽  
Governing Equations ◽  
Time Simulation ◽  
Flutter Analysis ◽  
Structural Nonlinearities ◽  
Limit Cycle Flutter

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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