Stochastic flutter of a panel subjected to random in-plane forces. I- Two mode interaction

The analysis includes stochastic stability and response moments of linear and nonlinear panels. The response moment equations are generated by using the Fokker-Planck equation approach. The mean-square stability boundaries and response moments are determined as functions of the spectral density of in-plane loads, aerodynamic pressure, air-to-structure mass ratio, and structural damping ratios. The nonlinear response is estimated by using a cumulant-neglect scheme. The nonlinear response statistics are obtained in the time domain, the steady-state reveals that the response process is strictly stationary