Supersonic flutter analysis of composite plates and shells
A high-precision doubly curved quadrilateral thin shell finite element is used for studying the supersonic flutter behavior of laminated composite plates and shells. The composite material property is included using classical lamination theory, and the supersonic aerodynamic effect is included using...
Gespeichert in:
Veröffentlicht in: | AIAA journal 1993-06, Vol.31 (6), p.1109-1117 |
---|---|
Hauptverfasser: | , |
Format: | Artikel |
Sprache: | eng |
Schlagworte: | |
Online-Zugang: | Volltext |
Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
Zusammenfassung: | A high-precision doubly curved quadrilateral thin shell finite element is used for studying the supersonic flutter behavior of laminated composite plates and shells. The composite material property is included using classical lamination theory, and the supersonic aerodynamic effect is included using linearized piston theory. To reduce the number of degrees of freedom of the finite element aeroelastic system, the normal modes approach is adopted. Results are presented to illustrate the behavior of flutter characteristics for composite plates and curved panels, and composite cylindrical and conical shells. Parametric studies concerning the effects of boundary conditions, fiber orientation, degree of orthotropy, and flow angle on the flutter characteristics are presented for a series of selected examples. The accuracy, efficiency, and applicability of the present finite element method are demonstrated by illustrative examples, and, whenever possible, the results are compared to alternative solutions available in the literature. |
---|---|
ISSN: | 0001-1452 1533-385X |
DOI: | 10.2514/3.11735 |