| 直升机复合材料桨叶前缘包铁疲劳定寿方法研究 |
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| 引用本文： | 余洵,岳巍.直升机复合材料桨叶前缘包铁疲劳定寿方法研究[J].直升机技术,2009(3). |
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| 作者姓名： | 余洵 岳巍 |
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| 作者单位： | 中国直升机设计研究所,景德镇,333001 |
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| 摘 要： | 通过标准样件试验,获得直升机桨叶前缘包铁的静强度极限和疲劳极限,通过有限元分析,获得应力集中系数,再应用应力集中系数对试验中获得的静强度极限和疲劳极限进行修正。本文最后以某型机桨叶前缘包铁为例,通过计算分析,给出了其静强度结论和寿命评估结论。
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| 关 键 词： | 直升机桨叶 前缘包铁 疲劳极限 寿命评估 |
Study of Fatigue Life Evaluation Method for Leading Edge of Helicopter Composite Blade |
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| Authors: | YU Xun YUE Wei |
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| Institution: | YU Xun; YUE Wei(China Helicopter Research and Development Institute; Jingdezhen; 333001); |
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| Abstract: | In this paper,the strength limit and fatigue limit of leading edge of a helicopter blade are obtained by tests of standard specimen,and stress concentration factors by finite element analysis.Then the strength limit and fatigue limit are corrected by using the stress concentration factors.As an example,a leading edge of a certain helicopter blade is calculated and analyzed,and the conclusion of its static and fatigue strength is finally given. |
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| Keywords: | helicopter blade leading edge fatigue limit life evaluation |
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