This paper deals with an analysis of the free vibration and aeroelastic divergence of aircraft wing structures modelled as thin-walled composite beams. A number of non-classical effects featuring the behavior of composite thin-walled beams of closed contour are incorporated and their implications are emphasized. The results which concern the vibrational characteristics obtained in the paper present an evident importance towards obtaining more reliable predictions of the dynamic response and flutter instability of aeronautical/aerospace structures, in general, and of their lifting surfaces in particular. As concerns the results associated with the divergence instability, these could have a significative role in a more efficient design of forward-swept wing aircraft for which this aeroelastic instability is the most critical one.
New developments of the theory of composite thin-walled beams structures incorporating non-classical effects
Neue Entwicklungen der Theorie dünnwandiger Trägerstrukturen aus Verbundwerkstoff unter Einbeziehung nicht-klassischer Effekte
1991
9 Seiten, 9 Bilder, 5 Tabellen, 5 Quellen
Conference paper
English
Simplified theory for composite thin-walled beams
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