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采用周期浸润加速腐蚀试验与疲劳试验相结合的方法,研究了腐蚀及腐蚀与疲劳交替作用对某型飞机30CrMnSiN i2A机翼主梁疲劳寿命的影响。结果表明,腐蚀环境的影响会引起30CrMnSiN i2A高强度结构钢的疲劳寿命明显降低。与未腐蚀状态相比,预腐蚀5、10、15天后,某型飞机机翼主梁模拟件的平均疲劳寿命分别下降了17.3%、20.5%、33.2%;而在腐蚀与疲劳交替作用下,其平均疲劳寿命下降了22.8%。在给定的腐蚀环境和疲劳载荷谱作用下,平均疲劳寿命N50随预腐蚀时间t的变化可以用N50=1044.541-219.978t描述。
The effects of corrosion, corrosion and fatigue alternation on fatigue life of 30CrMnSiN i2A airfoil main girder were studied by cyclic infiltration accelerated corrosion test and fatigue test. The results show that the fatigue life of 30CrMnSiN i2A high-strength structural steel is significantly reduced due to the influence of corrosive environment. Compared with the non-corrosive state, the average fatigue life of the wing girder simulations of a certain type of aircraft decreased by 17.3%, 20.5% and 33.2% respectively after pre-eroded for 5, 10 and 15 days. However, under the alternation of corrosion and fatigue, The average fatigue life decreased by 22.8%. Under given corrosive environment and fatigue load spectrum, the change of average fatigue life N50 with pre-etching time t can be described by N50 = 1044.541-219.978t.