| 引用本文: | 颜光耀,刘治国,穆志韬,等.多种服役环境下航空铝合金疲劳裂纹扩展行为.[J].国防科技大学学报,2019,41(3):112-118.[点击复制] |
| YAN Guangyao,LIU Zhiguo,MU Zhitao,et al.Aviation aluminum crack propagation behavior in multiple service environment[J].Journal of National University of Defense Technology,2019,41(3):112-118[点击复制] |
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| 多种服役环境下航空铝合金疲劳裂纹扩展行为 |
| 颜光耀, 刘治国, 穆志韬, 李旭东 |
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(海军航空大学青岛校区 航空机械系， 山东 青岛 266041)
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| 摘要: |
| 通过收集机场环境数据并依据环境谱编谱流程，编制出试验室环境下航空铝合金加速腐蚀试验谱，并依据该谱开展LD2CS铝合金预腐蚀疲劳试验。统计分析试验数据，利用影响平均值方法，筛选出三个重要腐蚀损伤表征量，即最大蚀坑深度、最大蚀坑宽度、点蚀率。通过归一化无量纲处理和加权平均方法，计算出腐蚀损伤综合指标α。对比不同损伤程度下预制裂纹疲劳扩展行为特点，定义腐蚀加速系数Ω(α)。利用加速腐蚀第18—20a的试验数据验证Ω(α)表达式的有效性，得到预测值相对误差均小于10%，这说明修正后的疲劳裂纹扩展公式适用于表示腐蚀损伤对长裂纹扩展的加速作用，为航空铝合金的损伤容限设计提供新的思路。 |
| 关键词: 飞行器转场环境 航空铝合金 加速腐蚀试验 影响平均值 腐蚀损伤综合指标 腐蚀加速系数 |
| DOI：10.11887/j.cn.201903018 |
| 投稿日期：2018-03-19 |
| 基金项目:国家部委基金资助项目（4010901030201） |
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| Aviation aluminum crack propagation behavior in multiple service environment |
| YAN Guangyao, LIU Zhiguo, MU Zhitao, LI Xudong |
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(Aviation Mechanics Department, Qingdao Branch of Naval Aeronautical University, Qingdao 266041, China)
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| Abstract: |
| The aviation aluminum alloy accelerated corrosion test spectrum was established according to the environment spectrum conducting process after collecting the airports environment data. Based on the accelerated corrosion test spectrum, aluminum alloy LD2CS pre-corroded fatigue test was carried out. Test data were analyzed statistically and the three main corrosion damage characterization factors, namely maximum pit depth, maximum pit width and pit surface rate, were sifted out by using MIV (mean impact value) method. Then the corrosion damage composite indictor α was computed by applying the normalization non-dimension and the weighted average methods. By comparing the characteristics of fatigue precrack propagation behaviors at different corrosion damage levels, the corrosion acceleration coefficient Ω(α) was defined to correct the classical fatigue crack growth formula. The validity of Ω(α)expression was verified by employing test data corroding the 18th to 20th equivelent years and the relative errors were all below 10%. It demonstrates that the corrected fatigue crack growth function in flight transfer environment is appropriate for reflecting the corrosion damage acceleration effect on crack propagation, which proposing new ideas for aviation aluminum alloy damage tolerance design. |
| Keywords: flight transfer environment aviation aluminum alloy accelerated corrosion test mean impact value corrosion damage indictor corrosion acceleration coefficient |
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