Fatigue Life Corrective Factor of Wing-Main-Beam under Corrosive Condition
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摘要: 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 C2T 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.Abstract: 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.
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Key words:
- fatigue life /
- corrosion fatigue /
- accelerated testing /
- grounding corrosion
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[1] 刘文,李玉海,贾国荣. 腐蚀条件下飞机结构使用寿命的评定与监控[J]. 北京航空航天大学学报,1996,22(3):259~263. [2]刘文,蒋冬滨.飞机结构关键危险部位加速腐蚀试验环境谱研究[J]. 航空学报,1998,19(3):434~438.
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