腐蚀条件下机翼主梁的疲劳寿命修正系数

针对歼击机主要疲劳关键件——机翼主梁,采用模拟试件进行加速试验环境谱下相当于地面停放不同年限的预腐蚀及谱载下疲劳试验,获得地面停放腐蚀影响系数C随地面停放年限T的变化曲线;由构成空中局部环境谱的各单一介质对谱载下寿命的影响试验,按百分比加权组合的方法获得空中腐蚀疲劳影响系数K.综合考虑C-T曲线与K,计算出不同无腐蚀条件下寿命和飞机年飞行小时数的组合所对应的腐蚀条件下机翼主梁疲劳寿命修正系数.为修正无腐蚀条件下寿命,从而评定腐蚀条件下机翼主梁寿命奠定了基础.

Fatigue Life Corrective Factor of Wing Main Beam under Corrosive Condition

Accelerated corrosion tests of simulator specimens of the wing main beam of a kind of fighter plane are carried out for different times which correspond to different years of the plan on grounding, before fatigue test are carried out under load spectrum. By analysis of test data, the curve of grounding corrosion influence factor( C ) versus grounding years( T ) is obtained. On the basis of load spectrum fatigue test of simulator specimens in various mediums that composed sky part environmental spectrum, sky corrosion fatigue influence factor( K ) is determined by the percent weighted composite method. Synthesizing C T curve and K , fatigue life correction factors of the wing main beam under corrosion condition are determined, which correspond to various non corrosion life and flight hours per year. The results are valuable for evaluation fatigue life of wing main beam under corrosion condition.