Abstract
OMPOSITE materials are used in the construction of curved panels of aircraft and space vehicles. Only a few works1'3 are available on panel flutter analysis of shell panels. In this investigation, circular cylindrical shell panels of rectangular planform, with edges clamped laterally and free from in-plane stresses (movable edges), are considered. The panel is subjected to supersonic flow parallel to the generator on one side only. The aerodynamic forces are approximated by using two-dimensional quasisteady aerodynamic theory. The problem is solved by using the integral equation technique. Formulation A typical cross-ply laminated panel is shown in the inset of Fig. 1. Two fourth-order aeroelastic governing differential equations, based on DonnelPs shallow shell approximation, can be derived in terms of the transverse displacement w and stress function F.4 They are
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