Free Vibration and Aeroelastic Stability Analysis of Truncated Conical Panels in Supersonic Flows

The current study is dedicated to free vibration and aeroelastic stability analysis of truncated conical ‎panels in supersonic flows. Governing equations of motion and the corresponding boundary conditions are ‎derived using Hamiltonian formulations. The aeroelastic stability problem is formulated based on first-order ‎shear deformation theory as well as classical shell theory with the linearized first-order piston theory for ‎aerodynamic loading. Based on the Galerkin truncation, the coupled fluid-solid interaction equation ‎transferred to ordinary differential equations.‎‏ ‏By solving the eigenvalue problem, frequencies and damping ‎of the system have been obtained versus supersonic flows‎. ‏ ‏The results are validated using numerical and theoretical data ‎available in the literature.‎ The study has been accomplished for truncated ‎conical shells with various geometries. The flutter boundaries are obtained for truncated conical shells with different ‎semi-vertex cone angles, different subtended angles, and different thicknesses. In all cases, the truncated conical shell ‎loses its stability through coupled-mode flutter.‎