Supersonic Flutter of Shear Deformable Laminated Composite Flat Panels
Flutter-type instability of cross-ply shear deformable composite flat panels exposed to a supersonic flow is analyzed. The two-dimensional static aerodynamic approximation and a higher order transverse shear deformation theory for the structural plate model are used. Comparisons of the results obtained in this framework with those derived within their first order transverse shear deformation and classical (Kirchhoff) counterparts are presented and a number of conclusions concerning their range of applicability are outlined. The results underline the strong effect played by transverse shear deformation and transverse normal stress, as well as by the higher order effects on the flutter instability of panels made of advanced composite materials. © 1990.
V. Birman and L. Librescu, "Supersonic Flutter of Shear Deformable Laminated Composite Flat Panels," Journal of Sound and Vibration, Elsevier, Jan 1990.
The definitive version is available at https://doi.org/10.1016/0022-460X(90)90887-6
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
Article - Journal
© 1990 Elsevier, All rights reserved.