L. Librescu, N.K. Chandiramani

Flutter instability of symmetrically laminated anisotropic composite flat panels exposed to a coplanar supersonic flow of arbitrary direction is analyzed. Due to the complexity of· the problem, the solution is obtained within a Rayleigh-Ritz procedure generalized to the case of nonconservative systems. Towards the same goal, the concept of the stability parabola coupled with the Sylvesters determinant technique are used to determine the flutter boundary. The structural plate model incorporates the transverse shear deformations as well as the anisotropy and heterogeneity effects while the expression of supersonic aerodynamic loads is based on a 2-D aerodynamic approximation. The numerical results underline the strong influence played by transverse shear deformations on the flutter predictions, as well as the inadequacy of the classical Kirchhoff model when applied to a panel which does not fulfill the requirements of a thin plate and/or when its material exhibits a weak rigidity in transverse shear.

International Forum on Aeroelasticity and Structural Dynamics 1991, Aachen

Conference Paper

englisch

21,0 x 29,7 cm, 7 Seiten

DGLR-Bericht, 1991, 1991-06, International Forum on Aeroelasticity and Structural Dynamics 1991 Proceedings; S.404-410; 1991; Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn

NA

aeroelasticity

Bestellbar

1991