Nonlinear Flutter of Cylindrical Panels Under Yawed Supersonic Flow Using Finite Elements

2005 ◽  
Author(s):  
Mohamed Azzouz ◽  
Chuh Mei
Keyword(s):  
Supersonic Flow ◽  
Finite Elements ◽  
Nonlinear Flutter ◽  
Cylindrical Panels

Nonlinear Flutter of Composite Panels Under Yawed Supersonic Flow Using Finite Elements

AIAA Journal ◽  
10.2514/2.818 ◽  
1999 ◽  
Vol 37 (9) ◽  
pp. 1025-1032 ◽  
Author(s):  
K. Abdel-Motaglay ◽  
R. Chen ◽  
C. Mei
Keyword(s):  
Supersonic Flow ◽  
Finite Elements ◽  
Composite Panels ◽  
Nonlinear Flutter

Nonlinear flutter of composite panels under yawed supersonic flow using finite elements

AIAA Journal ◽  
1999 ◽  
Vol 37 ◽  
pp. 1025-1032
Author(s):  
K. Abdel-Motaglay ◽  
R. Chen ◽  
C. Mei
Keyword(s):  
Supersonic Flow ◽  
Finite Elements ◽  
Composite Panels ◽  
Nonlinear Flutter

Aeroelastic Analysis of Laminated FG-CNTRC Cylindrical Panels Under Yawed Supersonic Flow

2019 ◽  
Vol 11 (06) ◽  
pp. 1950052 ◽  
Author(s):  
Ali Ghorbanpour Arani ◽  
Farhad Kiani ◽  
Hassan Afshari
Keyword(s):  
Carbon Nanotubes ◽  
Supersonic Flow ◽  
Volume Fraction ◽  
Differential Quadrature Method ◽  
Shear Deformation Theory ◽  
External Pressure ◽  
Functionally Graded ◽  
Geometrical Parameters ◽  
Cylindrical Panels ◽  
Generalized Differential

This paper presents a parametric study on aeroelastic stability analysis of multi-layered functionally graded carbon nanotubes reinforced composite (FG-CNTRC) cylindrical panels subjected to a yawed supersonic flow. The panel is considered to be composed of different layers reinforced by carbon nanotubes arranged in different directions with various patterns and different volume fractions. Reddy’s third-order shear deformation theory (TSDT) is employed to model the structure and external pressure is estimated based on the linear supersonic piston theory. The set of governing equations and boundary conditions are derived using Hamilton’s principle and are solved numerically using generalized differential quadrature method (GDQM). Convergence and accuracy of the presented solution are confirmed and effect of volume fraction, distributions and orientation of carbon nanotubes (CNTs), yaw angle and geometrical parameters of the panel on the flutter boundaries are investigated. Results of this paper can be considered as a useful tool in design and analysis of supersonic airplanes and missiles.

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