Flutter analysis of composite panels on many supports
Abstract
The flutter characteristics of finite composite panels on multiple simple supports at high supersonic Mach number have been investigated using finite element method. Linear small deflection laminated plate theory and quasi-steady aerodynamic theory are employed. Numerical results are obtained for the cases of one-, two-, three-bay running in either spanwise, streamwise or both directions. It is concluded that the number of modes required to give accurate results is mainly dependent on the number of bays under investigation. The sensitivity of the bay number in the determination of the flutter boundary is a function of the fiber orientation and aspect ratio.
- Publication:
-
Structural Dynamics: Recent Advances
- Pub Date:
- 1991
- Bibcode:
- 1991sdra.proc..377S
- Keywords:
-
- Composite Structures;
- Flutter Analysis;
- Mach Number;
- Rectangular Panels;
- Supersonic Speed;
- Supports;
- Aerodynamic Forces;
- Fiber Orientation;
- Finite Element Method;
- Laminates;
- Plate Theory;
- Structural Mechanics