学术
摘 要:
为建立疲劳裂纹对典型结构件性能影响的机理性模型，解决疲劳分析问题，以飞机的典型部件机翼为研究对象，建立了机翼的变幅载荷谱．基于弹塑性断裂力学，进行了机翼裂纹的扩展分析，利用多自由度动态有限元解析理论，进行了机翼的工作状态模拟和疲劳断裂分析，并给出了裂纹寿命预测的公式以预测构件的裂纹寿命．[著者文摘]
文章出处:
《哈尔滨理工大学学报》-2007年12卷1期 -118-121页
栏目信息:
分 类 号:
文献标识码:
A
文章编号:
1007-2683（2007）01-0118-04
Fatigue Life Analysis and Research for Typical Structure Part
SUN Ming-qi （The School of Mechanical ,＆ Power Engineering, Harbin Univ. Sei. Tech. , Harbin 150080, China）
Abstract:
To establish the mechanism model of fatigue crack to the performance of typical structure part and solve the problem of fatigue analysis, the wing as a typical part of aerospace vehicle is studied in this paper. The variable- amplitude load spectrum is presented and an expansion analysis to the wing crack is processed based on elasto - plastio fracture mechanics. The simulation of working state and the analysis fatigue fracture is processed employing the dynamic finite element theory of multi - degree of freedom. The equation for predicting the crack life is also presented to predict the crack life of the part.[著者文摘]
Key words:
fracture mechanics ; load spectrum; fatigue life ; finite element method
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