预腐蚀铝合金典型螺栓单搭接件疲劳寿命研究

陈跃良; 卞贵学; 郁大照

预腐蚀铝合金典型螺栓单搭接件疲劳寿命研究

1.
海军航空工程学院青岛分院, 山东, 青岛 266041;
2.
海军航空工程学院研究生管理大队, 山东, 烟台 264001

基金项目: 国家自然科学基金项目(50675221,51075394);航空科学基金项目(2008ZH85001);总装“十一五”预研项目(51327030104)

详细信息

作者简介:
陈跃良(1962-),男,浙江东阳人,教授,博士,博导,从事飞机结构寿命评定、结构疲劳断裂与可靠性研究(E-mail: cyl0532@sian.com);郁大照(1976-),男,山东郓城人,讲师,博士,从事腐蚀环境下飞机结构多处损伤研究(E-mail: ytyudazhao@yahoo.com).

中图分类号: TG171
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出版历程
- 收稿日期: 2012-05-08
- 修回日期: 2012-05-08
- 刊出日期: 2012-05-24

STUDY ON FATIGUE LIFE OF PRE-CORRODED ALUMINUM ALLOY TYPICAL SINGLE BOLTED LAP JOINTS

1.
Qingdao Branch of Naval Aeronautical Engineering University, Qingdao, Shandong 266041, China;
2.
Graduate Students Brigade of Naval Aeronautical Engineering University, Yantai, Shandong 264001, China

More Information

Corresponding author:
BIAN Gui-xue: 卞贵学

摘要

摘要: 模拟飞机服役环境,对航空LY12 铝合金板材典型螺栓单搭接试验件做了预腐蚀试验,然后通过疲劳试验得到了未腐蚀试验件和预腐蚀后试验件的疲劳寿命。通过对试验件分解检查,分析了腐蚀对航空LY12 铝合金典型螺栓单搭接件的影响。建立了考虑腐蚀影响的基于断裂力学的沉孔螺栓搭接件疲劳寿命计算模型,对预腐蚀搭接件的疲劳寿命进行了计算和分析。结果表明:螺栓孔附近和搭接面腐蚀较表面其他部位严重,腐蚀产物的膨胀作用下产生了“枕垫效应”;计算模型得到的疲劳寿命与试验寿命吻合较好,其中模型1 最大相对误差为36.7%,模型2 的最大相对误差为25.7%。搭接件不同的腐蚀程度要选择不同的计算模型才能得出精确的结果。在分析较严重的腐蚀对搭接件疲劳寿命影响时,应考虑搭接面的多腐蚀损伤。
- 疲劳 /
- 铝合金 /
- 腐蚀损伤 /
- 搭接件 /
- 飞机结构
Abstract: Corrosion experiment was performed for aviation LY12 aluminum alloy typical single bolted lap joints with imitating service environment of the military airplane. The fatigue life data for both un-corroded and pre-corroded specimens was obtained by fatigue tests. The specimens were torn down and then inspected. The corrosion effect on LY12 aluminum was analyzed. Two predictive models which consider the effect of corrosion for countersunk bolted lap joints are presented to calculate the fatigue life based on fracture mechanics. Results of two predictive models were calculated and analyzed. The results show that the faying surface and region round about bolt were corroded seriously with “pillowing effect” due to the expansion of corrosion products. Results of predictive models agree reasonably with the experiment results, with the maximum relative error being 36.7% for model 1 and 25.7% for model 2. It may be necessary to use different predictive models rather than a single predictive model to predict the fatigue lives. Multiple corrosion site damage in faying surface should be considered when serious corrosion effect on fatigue life of lap joint is investigated.
- fatigue /
- aluminium alloy /
- corrosion damage /
- lap joints /
- aircraft structure

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参考文献(20)

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