依据海军现役飞机的腐蚀环境特点及结构件腐蚀损伤深度拟合规律，采用应力场强法和局部应力应变法分别对疲劳缺口系数K_f及疲劳寿命计算模型进行了分析，提出了一种腐蚀环境下飞机结构疲劳寿命的评定方法。该方法以室温大气环境下的寿命评定结论为依据，考虑了结构件腐蚀损伤后潮湿空气、盐雾、盐雾＋SO₂等环境介质对疲劳寿命的影响，并结合国产某型飞机机翼前梁缘条腐蚀损伤部位的疲劳寿命及剩余寿命估算实例进行了分析。

According to the environment characteristics and corrosion depth distribution law of the naval aircraft structures fatigue notch factor (K_f) and fatigue life mathematical model was built by using the Stress Field Intensity (SFI) and Local Stress-strain methods. In this paper, a method for evaluating service life of aircraft structure under corrosive condition was developed. On the basis of the evaluation result under room temperature and air, and taking into consideration the influences of corrosion depth in the ground environment and corrosion fatigue in flight environment of the humidity air, salt fog, salt fog + SO₂ this method made correction for fatigue life. Finally, combing with a real case of fatigue life and residual life prediction of the flange for the aircraft wing, this calculating method was appraised.