| 止裂孔尺寸对止裂效果影响的研究 |
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| 引用本文： | 何云树 陈立军 杜洪增. 止裂孔尺寸对止裂效果影响的研究[J]. 中国民航学院学报, 2004, 22(3): 29-31 |
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| 作者姓名： | 何云树 陈立军 杜洪增 |
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| 作者单位： | 中国民用航空学院机电工程学院 天津300300(何云树，陈立军)，中国民用航空学院机电工程学院 天津300300(杜洪增) |
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| 基金项目： | 中国民航总局科技基金项目(2003-8-2). |
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| 摘 要： | 当航空器结构在航线使用过程中出现疲劳裂纹损伤时,通常在裂纹尖端打止裂孔进行临时性修理。通过理论分析和计算及试验分析,研究了止裂孔尺寸对止裂效果的影响。结果表明,当航空器结构出现疲劳裂纹损伤时,采用5.57～7.14mm直径的止裂孔进行止裂修理,止裂效果较好;当止裂孔直径为6.35mm时,止裂效果最好。
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| 关 键 词： | 应力集中 有限元素法 局部应力应变法 疲劳寿命 |
| 文章编号： | 1001-5000(2004)03-0029-03 |
| 修稿时间： | 2003-11-25 |
Effectiveness Varying in Dimension of Crack-Stopping Holes |
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| HE Yun-shu,CHEN Li-jun,DU Hong-zeng. Effectiveness Varying in Dimension of Crack-Stopping Holes[J]. Journal of Civil Aviation University of China, 2004, 22(3): 29-31 |
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| Authors: | HE Yun-shu CHEN Li-jun DU Hong-zeng |
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| Abstract: | A kind of temporary maintenance which is to create stopping crack holes at both ends of a crack occurred because of mechanical fatigue,while the aircraft is at a stop on a ongoing flight service.Through a theoretical research,experimental analysis and algorithm,finding out that the effectiveness to terminate the crack by a stopping crack hole varies in dimension of the hole itself. A diameter ranging from 5.57~7.14 mm diameter is better,while a hole of 6.35 mm diameter is the most effective means to end to the development of a crack. |
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| Keywords: | stress concentration finite element method local stress-strain method fatigue life |
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