Nonlinear aeroelastic analysis of curved laminated composite panels

The finite element co-rotational theory is applied to model geometrically nonlinear shell panels, and an Euler solver, instead of piston theory or other simplified aerodynamic theories, is utilized to solve for the unsteady aerodynamic pressure. Aeroelastic responses for thin panels, with which have two different sizes of curvature H/h = 5 and H/h = 10, as well as two different layer orientations, [0°/90°/0°/90°/0°] and [45°/−45°/45°/−45°/45°] are simulated under four Mach numbers at 0.76, 0.96, 1.2 and 1.67. The results, comprising the static aeroelastic deformation, limit cycle oscillation, non-periodic oscillation and chaotic behaviors are obtained and studied. Flutter dynamic pressure, amplitudes, and spectra of limit cycle oscillation are analyzed, and the nonlinear characteristics are discussed.