Nonlinear Aeroelastic Behavior of a Panel Subjected to Oscillating Shock Waves

Oscillating shock waves are a typical flow structure in hypersonic regimes. Compared with stationary shock waves, oscillating shock waves induce significant pressure fluctuations, which are more likely to trigger fluid–structure interaction issues on panels. In this paper, a verified in-house code is employed to investigate the nonlinear dynamic response of a panel subjected to an oscillating shock wave. The obtained results indicate that the introduction of oscillating shock waves results in complex nonlinear dynamic responses of the panel. First, compared with the second-order-mode-dominated vibration exhibited by the panel subjected to a stationary shock, the panel primarily exhibits first-order-mode-dominated vibration. Second, under the influence of an oscillating shock, a modal transition occurs at a certain low dynamic pressure; the dynamic pressure at which this transition occurs increases with the shock oscillation frequency and decreases with the shock oscillation amplitude. Finally, variations in shock wave oscillation frequencies and amplitudes significantly alter the evolution of the panel’s dynamic behavior, including the dynamic pressure at which the first bifurcation occurs, as well as the evolutionary path from predictable limit cycle oscillation to unpredictable chaotic motion.