谱载荷下三维构件疲劳分析的损伤力学方法

孟宪红; 白曌宇; 张行

谱载荷下三维构件疲劳分析的损伤力学方法

北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

作者简介:
孟宪红(1971-),女,山东郯城人,副教授,mxh@buaa.edu.cn.

中图分类号: O 346.5
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- 被引次数: 0
出版历程
- 收稿日期: 2010-03-29
- 网络出版日期: 2011-08-30

Damage mechanics method to predict the fatigue life of 3-D structural members under spectrum load

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 建立了工程中常见的三维构件的一个损伤力学守恒积分,并利用此积分的守恒性与小范围损伤的条件,推导出计及损伤耦合效应时集中的应力与应变所应满足的方程.根据以损伤驱动力表示的损伤演化方程,推导了在谱载荷作用下,疲劳裂纹萌生寿命预估的解析表达式,建立了以等效应力表示的非分离变量型损伤演化方程,并在短周期加载条件下得到积分形式的疲劳寿命闭合解.对某飞机起落架为代表的三维构件在谱载荷作用下的疲劳寿命进行了预报.
- 损伤力学 /
- 谱载荷 /
- 三维构件 /
- 疲劳寿命
Abstract: A conservative integral of three dimensional structures in damage mechanics was established. The expression of the stress and the strain considering the effect of damage coupling was deduced by means of the path independent property of this integral and the condition of small scale damage. Based on the damage evolution equations expressed by the damage driving force, a closed form solution to determine the fatigue crack formation life under the spectrum load was obtained. According to the above analysis, the damage evolution equation with equivalent stress of non variable separated type was established, and a closed form solution of integral type was obtained to determine the fatigue crack formation life under the short period load. The fatigue life of the landing gear of certain airplane as the representative of 3-D structural member is predicted.
- damage mechanics /
- spectrum load /
- 3-D structural member /
- fatigue life

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参考文献(1)

[1] Lemaitre J.A course on damage mechanics[M].New York:Springer-Verlag,1992 [2] 张行,赵军.金属构件应用疲劳损伤力学[M].北京:国防工业出版社,1998 Zhang Xing,Zhao Jun,Applied fatigue damage mechanics of metallic structral members[M].Beijing:Press of National Defence Industry,1998(in Chinese) [3] Zhang X,Zhao J,Hwang K C,A method of damage mechanics for the prediction of fatigue life[C]//Proceedings of the 3rd Int Conf on Fract and Strength of Solids.Hong Kong:[s.n.],1997:433-442 [4] 白瞾宇,孟宪红,张行.含沟槽轴对称杆疲劳寿命的损伤力学闭合解[J].航空学报,2007,28(3) :579-581 Bai Zhaoyu,Meng Xianhong,Zhang Xing,Closed form solution of damage mechanics to predict the fatigue life of axially symmetric bars with grooves[J].Acta Aernautica et Astronautica Sinica,2007,28(3):579-581(in Chinese) [5] 高镇同.疲劳性能试验设计和数据处理[M].北京:北京航空航天大学出版社,1999 Gao Zhentong.Fatigue properties experimental design and data analysis[M].Beijing:Press of Beijing University of Aeronautics and Astronautics,1999(in Chinese) [6] 白瞾宇,孟宪红,张行.确定材料概率疲劳曲线的损伤力学方法[J].北京航空航天大学学报,2005,31(9),1027-1030 Bai Zhaoyu,Meng Xianhong,Zhang Xing.Method of damage mechanics to determine the p-S-N curve of material[J].Journal of Beijing University of Aeronautics and Astronautics,2005,31(9):1027-1030 (in Chinese) [7] 白曌宇.疲劳损伤力学新方法及其在工程中之应用[D].北京:北京航空航天大学航空科学与工程学院,2009 Bai Zhaoyu.The new method of damage mechanics and its application in engineering[D].School of Aeronautic Science and Engineering,Beijing University of Aeranautics and Aestronautics,2009(in Chinese) [8] 刘克格,阎楚良,张书明.飞机起落架疲劳损伤估算及其特点[J].吉林大学学报:工学版,2005,35(6):660-664 Liu Kege,Yan Chuliang,Zhang Shuming.Estimation for fatigue damage of airplane landing gear[J].Journal of Jilin University:Engineering and Technology Edition,2005,35(6):660-664 (in Chinese) [9] 杨继运,张行,张珉.基于疲劳裂纹形成曲线的裂纹扩展分析数值方法[J].机械工程学报,2004,40(7):55-62 Yang Jiyun,Zhang Xing,Zhang Min.Numerical method for crack extension analysis based on fatigue crack formation curve[J].Journal of Mechanical Engineering,2004,40(7):55-62(in Chinese)

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