Construction of Compressible Euler Solver Using Building-Cube Method and Application to Flutter Analysis of Aircraft Wing

2014 ◽  
Vol 62 (2) ◽  
pp. 39-46 ◽  
Author(s):  
Yasutaka NISHIMURA ◽  
Daisuke SASAKI ◽  
Kazuhiro NAKAHASHI
Keyword(s):  
Aircraft Wing ◽  
Flutter Analysis ◽  
Compressible Euler ◽  
Euler Solver

Flutter analysis of cascades using a two dimensional Euler solver

1991 ◽  
Author(s):  
T. REDDY ◽  
MILIND BAKHLE ◽  
DENNIS HUFF ◽  
TIMOTHYW. SWAFFORD
Keyword(s):  
Two Dimensional ◽  
Flutter Analysis ◽  
Euler Solver

Flutter analysis of propfans using a three-dimensional Euler solver

1996 ◽  
Vol 12 (2) ◽  
pp. 267-273 ◽  
Author(s):  
R. Srivastava ◽  
T. S. R. Reddy ◽  
O. Mehmed
Keyword(s):  
Three Dimensional ◽  
Flutter Analysis ◽  
Euler Solver

Flutter suppression of an aircraft wing with a flexibly mounted mass using magneto-rheological damper

2019 ◽  
Vol 234 (3) ◽  
pp. 827-839
Author(s):  
Amir Hossein Ghasemikaram ◽  
Abbas Mazidi ◽  
Mohammad Reza Fazel ◽  
Seyed Ahmad Fazelzadeh
Keyword(s):  
Differential Equations ◽  
State Feedback ◽  
Structural Model ◽  
Aerodynamic Force ◽  
Governing Equations ◽  
Aircraft Wing ◽  
Flutter Suppression ◽  
Flutter Analysis ◽  
Finite State ◽  
Magneto Rheological

Flutter analysis and suppression of an aircraft wing with a flexibly mounted external store using a magneto-rheological damper are investigated. The wing performs as a cantilever beam and the structural model, which incorporates bending-torsion flexibility, is used. A modified Bouc–Wen model is utilized in order to model the elastic connection between the store and the wing. The modified Peter’s finite-state loading is also considered to simulate the aerodynamic force and moment. The governing equations are obtained via Hamilton’s principle and assumed modes method is subsequently applied to transform the resulting partial differential equations into a set of ordinary differential equations. Numerical simulations are validated against several previously published papers by using a clean Goland wing. In order to control the vertical and rotational vibrations of the store and the wing, a state feedback controller and a compensator with full-order observer are designed. The performance of these controllers is compared together in several situations. Eventually, the performances are treated when disturbance is applied to the system. The results show that magneto-rheological damper’s performance is suitable for controlling the limit cycle oscillations of the wing and external store, in flutter condition.

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