Title :
Effects of structural damping on composite panel flutter
Author_Institution :
Dept. of Aerosp. Eng., Ulsan Univ., South Korea
Abstract :
The governing equation for the analysis of panel flutter of composite plates including structural damping is derived using the energy method. The classical lamination theory is applied to structural modeling and the eigenvalue problem is obtained by the Rayleigh-Ritz method. The unsteady aerodynamic load in supersonic flow is computed by the piston theory. The critical dynamic pressures for composite plate are calculated to investigate the effects of structural damping on the flutter boundaries. The effect of structural damping on the flutter boundaries of composite plates is investigated with the variation of fiber orientation. The structural damping plays an important role in the flutter stability with low aerodynamic damping but would not affect the flutter boundary with high aerodynamic damping.
Keywords :
Rayleigh-Ritz methods; aerodynamics; aircraft; composite materials; damping; eigenvalues and eigenfunctions; laminations; structural engineering; supersonic flow; Rayleigh-Ritz method; aerodynamic load; composite panel flutter; critical dynamic pressures; eigenvalue problem; fiber orientation variation; flight vehicle thin skin; high aerodynamic damping; lamination theory; low aerodynamic damping; piston theory; structural damping effects; structural modeling; supersonic flow; Aerodynamics; Damping; Equations; Hysteresis; Linear approximation; Optical fiber theory; Pistons; Stability; Transportation; Vehicle dynamics;
Conference_Titel :
Science and Technology, 2002. KORUS-2002. Proceedings. The 6th Russian-Korean International Symposium on
Print_ISBN :
0-7803-7427-4
DOI :
10.1109/KORUS.2002.1027947
