Structural skins of aerospace vehicles are typically made of large, internally reinforced curved panels. The presence of stiffening components subdivides the panel into several bays that interact structurally. In this context, the present study investigates the effects of adjacent bays interaction in curved panels under supersonic flutter. The analyses reveal severe jumps in the post-flutter LCO amplitudes and sub-critical bifurcation with the coexistence of different LCO branches for a specific range of dynamic pressure. These discontinuities consist of abrupt changes in the LCO amplitudes, directly related to the nonlinear coupling between adjacent bays under supersonic flutter with strong sensitivity to initial conditions.

航空航天器的结构蒙皮通常由内部增强的大型弯曲面板制成。加强组件的存在将面板分为几个在结构上相互作用的隔间。在这种情况下，本研究调查了在超声速颤振作用下弯曲面板中相邻海湾相互作用的影响。分析表明，在特定的动态压力范围内，振颤后的LCO幅度和亚临界分叉出现严重跳跃，并且不同LCO分支并存。这些不连续性包括LCO幅度的突然变化，直接与超声振颤下相邻隔间之间的非线性耦合有关，并且对初始条件具有很高的敏感性。