| 某型飞机翼身主交点框下部疲劳寿命试验 |
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| 引用本文： | 刘成义.某型飞机翼身主交点框下部疲劳寿命试验[J].飞机设计,2005(1):1-7. |
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| 作者姓名： | 刘成义 |
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| 作者单位： | 沈阳飞机设计研究所,沈阳,110035 |
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| 摘 要： | 介绍了某型飞机翼身主交点框下部疲劳寿命的试验方法及其结果, 还介绍了考虑预加高载对结构疲劳寿命影响的元件疲劳寿命试验。文章指出, 随着飞机使用范围的扩大, 环境影响引起的材料腐蚀损伤已成为飞机机体结构的致命杀手。在主交点框下部发生的环境腐蚀疲劳裂纹问题就是一个实例, 必须引起飞机总设计师和广大设计人员的重视。
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| 关 键 词： | 腐蚀疲劳裂纹 载荷谱 使用寿命 |
| 修稿时间： | 2004年9月6日 |
Fatigue Life Test of the Lower Portion of a Main Fuselage - Wing Bulkhead |
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| Liu Chengyi.Fatigue Life Test of the Lower Portion of a Main Fuselage - Wing Bulkhead[J].Aircraft Design,2005(1):1-7. |
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| Authors: | Liu Chengyi |
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| Abstract: | Test techniques and results of the fatigue life tests of the lower portion of the main fuselage-wing bulkhead in a certain-type aircraft are presented. An element fatigue life test where the effect of high pre-loading is accounted for is also conducted. It is indicated that as operation regions of the aircraft are extended, environment effect become a major factor causing corrosion of airframe structures. Fatigue crack due to environment corrosion occuring in the lower portion of main fuselage-wing bulkhead is a typical example. This shall receive considerable attention in aircraft designers. |
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| Keywords: | corrosion fatigue crack loadspectrum service life |
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