Study of aeroelastic REsponse of cylindrical composite panels in A high-speed flow

摘要

This study aims to investigate the aeroelastic behaviors of cylindrical composite panels in a high-speed flow. A fluid-structure coupling program is applied to simulate the response of the interaction with the presence of both fluid and structural nonlinearities at Ma = 0.99. The cylindrical composite panels with different layer orientations, cross-ply and angle-ply are modeled by an assemblage of triangular finite elements and the nonlinearity caused by large displacement is described by an updated tangent stiffness matrix. The inviscid unsteady equations are discretized by an AUSMpw+ flux splitting scheme. The static divergence, flutter characteristic and post-flutter response are computed and analyzed with the increase of the dynamic pressure. The results show that static and dynamic responses vary with the layer orientation. Particularly, the dynamic response of the cross-ply panel presents as high-frequency resonant oscillation; on the contrary, the dynamic response of the angle-ply panel appears as low-frequency single mode oscillation. Nonlinearities involved with aeroelastic response, such as the movement of the multiple-shock structure, and large displacement in structure, are discussed.