Nonlinear oscillations of a fluttering plate.

Supersonic Aerothermoelastic Nonlinear Flutter Study of Curved Panels: Frequency Domain

“…Fung [13] and Houboult [14] were the first to consider the flutter of a buckled plate in a partial nonlinear analysis for two-dimensional panels subjected to uniform temperature distribution. Kobayashi [15], Fralich [16], Ventres and Dowell [17], and Dowell [18] performed a complete nonlinear analysis for the flutter of buckled plates. Dowell articulated a relation between an equivalent mechanical in-plane pressure and the uniform temperature distribution effect.…”

Aeroelastic Analysis of Composite Pinched Panels Using Higher-Order Shell Elements

“…Panel flutter was observed for the first time when the first supersonic flights were performed and it was studied theoretically in the fifties by Hayes [1], Miles [2], and Shen [3]. Significant contributions have been made by Dowell [4][5][6]. The classical approach to panel flutter analysis considers both the aerodynamic and the structural model as linear.…”

Application of aeroelastic modes on nonlinear supersonic panel flutter at elevated temperatures

“…The traditional approach is to reduce the PDE or the finite element system equations to a set of coupled nonlinear ordinary differential equations using the in vacuo natural modes (NMs). It is known that a minimum of six (or 6 · 1) NMs is needed for converged LCO of isotropic rectangular plates at zero yaw angle [1,3]. For isotropic or orthotropic rectangular plates under an arbitrary non-zero yawed supersonic flow, 36 or 6 · 6 NMs are needed [4]; for laminated anisotropic rectangular plates even at zero yaw angle, 36 or fewer NMs are needed [4].…”

“…Comparison of LCO amplitudes using 2 AEMs, 6 NMs and Dowell[3] for a simply supported isotropic square plate at K = 0°.…”