风扇叶片作为航空发动机遭遇鸟撞后的首要响应部件，其应力变化导致的动态损伤会直接影响飞机的飞行安全。根据“斑头雁”外形的结构特点建立了近真实鸟体三维模型，针对飞机在起飞-爬升、进近-着陆两个最易发生鸟撞事故阶段的飞行工况，进行了不同撞击速度、不同风扇叶片转速以及不同鸟体撞击姿态对叶片动态损伤影响规律的研究。研究结果表明：当航空发动机转速和鸟体撞击叶片的相对速度增大时，风扇叶片的轴向损伤变形程度呈现出单调增加趋势；随着风扇叶片转速的增加，鸟撞后叶片的应力峰值呈V字形趋势，在航空发动机叶片转速为2 005 r/min时，应力峰值最小；当鸟体以不同姿态与风扇叶片碰撞的初始时刻接触面积增大时，叶片受到的应力大小和损伤程度也逐步增大，当鸟体呈现90°撞击姿态时，叶片在轴向上的损伤变形达到60.887 mm。研究结果对航空发动机风扇叶片抗鸟撞设计具有一定参考价值。

The response of an aircraft engine to bird strikes has the fan blade as its primary component, and the flight safety of the aircraft is directly impacted by the dynamic damage caused by stress changes. A three-dimensional model of a near-real bird body was established in this paper based on the structural features of the "bar-headed goose". The dynamic damage of the blade was studied in consideration of the take-off-climb and approach-landing stages where bird strike accidents are most likely to occur for aircraft, with the effects of different impact speeds, fan blade speeds, and bird impact attitudes being taken into account. It is indicated by the results that the axial damage and deformation of fan blades tend to be increased monotonically with the increasing of aero-engine speed and relative velocity of bird strike blades. Additionally, as the fan blade speed is increased, the stress peak value after a bird strike shows a V-shaped trend, with the smallest stress peak value being occurred at 2 005 r/min. Furthermore, as the contact area between the bird body and fan blade at the initial collision moment is increased, both the stress and damage degree of the blade are gradually increased across different postures. When impacted at a 90° posture, the axial damage deformation of the blade is reached to 60.887 mm. Valuable reference for anti-bird strike design considerations for aero-engine fan blades is provided by these research findings.