基于振动台采用高速电机驱动开展航空发动机转子在突加冲击载荷下的动力响应试验研究，完成不同特征转速、不同载荷大小、不同冲击方向、不同脉宽条件下的转子动力响应试验，揭示了突加冲击载荷下转子动力响应的一般规律。研究表明：冲击瞬时，转子动力响应呈现瞬间增大、随后恢复至稳定状态的现象；转子的动力响应随着突加冲击载荷的变大而变大，且各工况条件下，转子上垂直方向的动力响应比水平方向的动力响应要大，同一测量截面垂直方向响应比水平方向响应大4% ~ 46.15%；此外，转子受到轴向基础冲击载荷的动力响应比受到垂向基础冲击载荷的动力响应大；在一定范围内，随着基础冲击载荷脉宽从6 ms变大至11 ms，转子的动力响应变小2.5% ~ 10%。研究为航空发动机转子在突加冲击载荷下的振动响应分析和航空发动机结构安全设计提供了参考，具有重要的工程应用价值。

The experimental research on the dynamic response of aero-engine rotor under sudden impact load was carried out by using high-speed motor drive on the vibration table. Rotor dynamic response tests under different characteristic speeds, load sizes, impact directions, and pulse widths were completed, revealing the general rules of rotor dynamic response under sudden impact loads. The results show that the dynamic response of the rotor increases instantly and then returns to a stable state when under instantaneous impact, and it increases with the increase of the sudden impact load. Besides, the vertical dynamic response of the rotor is greater than the horizontal dynamic response, and the vertical response of the same measurement section is 4% to 46.15% greater than the horizontal response under various operating conditions. In addition, the dynamic response of the rotor under axial foundation impact is greater than that under vertical foundation impact. Within a certain range, as the pulse width of the impact load increases from 6 ms to 11 ms, the dynamic response of the rotor decreases by 2.5% ~ 10%. The study provides a reference for the vibration response analysis of aero-engine rotors under sudden impact loads and the structural safety design of aero-engine, which has important engineering application value.