| 铝合金6082T6中的疲劳不扩展裂纹 |
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| 引用本文： | 陈荣康,吴昊. 铝合金6082T6中的疲劳不扩展裂纹[J]. 理化检验(物理分册), 2012, 0(9): 569-571,630 |
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| 作者姓名： | 陈荣康 吴昊 |
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| 作者单位： | 同济大学航空航天与力学学院 |
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| 摘 要： | 铝合金6082T6作为一种常用的航空材料具有很好的力学性能，使用这种材料对疲劳不扩展裂纹进行了研究。试样形状为单边缺口拉伸试样，并在裂纹尖端使用数控机床钻直径为1mm的止裂孔。通过分析可得：疲劳不扩展裂纹可以通过对试样几何尺寸的合理设置得到。在设计中可以在疲劳构件容易萌生裂纹的部位预留出不扩展裂纹的容许长度，从而更大限度的提高构件的寿命可靠性，并且可以抵抗一定程度的外界不确定载荷的冲击影响，减少在裂纹维修或检查间隔期间的裂纹扩展风险。
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| 关 键 词： | 铝合金6082T6 疲劳 小裂纹 不扩展裂纹 应力梯度 |
Non-propagating Crack in Aluminum Alloy 6082T6 |
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| CHEN Rong-kang,WU Hao. Non-propagating Crack in Aluminum Alloy 6082T6[J]. Physical Testing and Chemical Analysis Part A:Physical Testing, 2012, 0(9): 569-571,630 |
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| Authors: | CHEN Rong-kang WU Hao |
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| Affiliation: | (School of Aerospace Engineering and Applied Mechanics,Tongji University,Shanghai 200092,China) |
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| Abstract: | As a frequently-used aeronautical material,aluminium alloy 6082T6 has the excellent mechanical properties.The fatigue non-propagating crack in the metal was studied.The SENT specimens were used in the fatigue tests.The 1 mm radii stop-holes were carefully centered and drilled at the fatigue crack tips with the help of a milling machine.After the researches it was found that the non-propagating crack length can be achieved through the reasonable specimens design.The non-propagating crack tolerance can be pre-setted at the dangerous place where the crack tends to be initiated and the reliability life of component can be significantly improved.The method can improve the impact resistance of component and reduce the risk of crack propagation during the maintenance interval. |
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| Keywords: | aluminum alloy 6082T6 fatigue short crack non-propagating crack stress gradient |
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