孔边倒角裂纹当量初始缺陷尺寸的确定方法

doi:10.13700/j.bh.1001-5965.2016.0985

北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (1): 187-195.doi: 10.13700/j.bh.1001-5965.2016.0985

孔边倒角裂纹当量初始缺陷尺寸的确定方法

孙晓娜¹, 贺小帆¹, 李玉海²

1. 北京航空航天大学航空科学与工程学院, 北京 100083;
2. 中国航空工业集团有限公司, 北京 100022

收稿日期:2017-01-03 修回日期:2017-03-10 出版日期:2018-01-20 发布日期:2017-04-13
通讯作者: 贺小帆 E-mail:xfhe@buaa.edu.cn
作者简介:孙晓娜,女,硕士研究生。主要研究方向:结构耐久性;贺小帆,男,博士,副教授。主要研究方向:疲劳/断裂、结构可靠性与耐久性、腐蚀条件下使用寿命评定。

Determination method of equivalent initial flaw size for crack initiated at hole chamfering

SUN Xiaona¹, HE Xiaofan¹, LI Yuhai²

1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. Aviation Industry Corporation of China, Ltd., Beijing 100022, China

Received:2017-01-03 Revised:2017-03-10 Online:2018-01-20 Published:2017-04-13

摘要/Abstract

摘要： 孔边倒角裂纹是含孔下陷细节的常见裂纹形态，为进行含孔下陷细节的经济寿命评定，需要确定倒角裂纹的原始疲劳质量（IFQ）。首先，为探究倒角对裂纹前缘应力强度因子的影响，进行了有、无倒角2种情况下应力强度因子的有限元分析。计算表明倒角对相对小裂纹的应力强度因子影响显著。其次，为合理表征该种裂纹的IFQ，将初始缺陷当量为萌生于倒角和试件表面交点，前缘为圆弧的初始裂纹，以萌生点到裂纹前缘沿孔径向的距离作为裂纹特征尺寸。最后，采用相对小裂纹扩展方程描述倒角裂纹的扩展规律，反推得到倒角裂纹的当量初始缺陷尺寸（EIFS）分布。统计分析表明，采用本文定义的裂纹特征尺寸得到的EIFS分布参数与应力水平无关。

关键词: 原始疲劳质量(IFQ), 应力强度因子, 有限元, 裂纹扩展方程, 当量初始缺陷尺寸(EIFS)

Abstract: Cracks often initiate at the chamfering for sagging holes. The initial fatigue quality (IFQ) of this type of crack needs to be determined prior to economic life assessment. Firstly, finite element models with and without chamfering are developed so as to investigate the effect of chamfering on the stress intensity factors at the crack front. The results show that the chamfering imposes great influence on the stress intensity factors of relatively small crack. Secondly, in order to characterize the IFQ of sagging holes, a circular-front crack initiated at the intersection of the chamfering and specimen surface is taken as the initial flaw, with the radial distance of crack front from the initiation site as the crack size. Finally, the crack growth equation for relatively small cracks is employed to characterize the crack growth behavior, and the equivalent initial flaw size (EIFS) distribution is obtained through back-extrapolation. Statistical analyses show that the EIFS distribution parameters obtained by using the proposed crack size definition are independent of stress levels.

Key words: initial fatigue quality (IFQ), stress intensity factor, finite element, crack growth equation, equivalent initial flaw size (EIFS)

中图分类号:

V215.5

孙晓娜, 贺小帆, 李玉海. 孔边倒角裂纹当量初始缺陷尺寸的确定方法[J]. 北京航空航天大学学报, 2018, 44(1): 187-195.

SUN Xiaona, HE Xiaofan, LI Yuhai. Determination method of equivalent initial flaw size for crack initiated at hole chamfering[J]. JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2018, 44(1): 187-195.

参考文献

[1] TONG Y C.Literature review on aircraft structural risk and reliability analysis:DSTO-TR-1110[R].Melboure:DSTO Aeronautical and Maritime Research Labratory,2001.
[2] RUDD J L,GRAY T D.Quantification of fastener-hole quality[J].Journal of Aircraft,1978,15(3):143-147.
[3] RUDD J L.Applications of the equivalent initial quality method:AFFDL-TM-76-83-FBE[R].Dayton:Wright-Patterson AFB,1977.
[4] MANNING S D,YANG J N,SHINOZUKA M.USAF durability design handbook:Guidelines for the analysis and design of durable aircraft structures:AFFDL-TR84-3027[R].Dayton:Wright-Patterson AFB,1984.
[5] YANG J N.Statistical estimation of economic life for aircraft structures[J].Journal of Aircraft,1980,17(7):528-535.
[6] BARTER S A,MOLENT L.Fatigue cracking from a corrosion pit in an aircraft bulkhead[J].Engineering Failure Analysis,2014,39(4):155-163.
[7] MOLENT L.A review of equivalent pre-crack sizes in aluminium alloy 7050-T7451[J].Fatigue & Fracture of Engineering Materials & Structures,2014,37(10):1055-1074.
[8] MOLENT L,SUN Q,GREEEN A J.Characterisation of equivalent initial flaw sizes in 7050 aluminium alloy[J].Fatigue & Fracture of Engineering Materials & Structures,2006,29(11):916-937.
[9] MATTRAND C,BOURINET J M,THÉRET D.Analysis of fatigue crack growth under random load sequences derived from military in-flight load data[C]//ICAF 2011 Structural Integrity:Inuence of Eciency and Green Imper-atives.Berlin:Springer-Verlag,2011:399-413.
[10] MATTRAND C,BOURINET J M.Random load sequences and stochastic crack growth based on measured load data[J].Engineering Fracture Mechanics,2011,78(17):3030-3048.
[11] XIANG Y,LIU Y. EIFS-based crack growth fatigue life prediction of pitting-corroded test specimens[J].Engineering Fracture Mechanics,2010,77(8):1314-1324.
[12] FAWAZ S A.Equivalent initial flaw size testing and analysis of transport aircraft skin splices[J].Fatigue & Fracture of Engineering Materials & Structures,2003,26(3):279-290.
[13] WANG D Y.An investigation of initial fatigue quality:STPZ8860S[R].West Conshohocken:ASTM Special Technical Publication,1982.
[14] 航空航天部AFFD系统办公室.美国空军耐久性手册背景材料:第Ⅷ卷[M]西安:航空航天部AFFD系统办公室,1989.AFFD System Engineering Office of the Department of Aeronautics and Astronautics. The background information of USAF durability design handbook:Vol.Ⅷ[M].Xi'an:AFFD System Engineering Office of the Department of Aeronautics and Astronautics,1989(in Chinese).
[15] YANG J,MANNING S,RUDD J,et al.Effect of specimen size and notch geometry on equivalent initial flaw size distribution[C]//AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference and Exhibit.Reston:AIAA,1996:385-397.
[16] 曹淑森,贺小帆,杨博霄,等.夹持边界条件下表面裂纹应力强度因子求解[J].北京航空航天大学学报,2014,40(11):1637-1642.CAO S S,HE X F,YANG B X,et al.Solution of stress intensity factor of surface cracked geometry with clamped ends[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(11):1637-1642(in Chinese).
[17] 张行.断裂力学[M].北京:中国宇航出版社,1990:72-169.ZHANG X.Fracture mechanics[M].Beijing:China Aerospace Press,1990:72-169(in Chinese).
[18] 刘文珽.概率断裂力学与概率损伤容限/耐久性[M].北京:北京航空航天大学出版社,1999:144-181.LIU W T.Probabilistic fracture mechanics and probability damage tolerance/durability[M]. Beijing:Beihang University Press,1999:144-181(in Chinese).
[19] PROVAN J W.Probabilistic fracture mechanics and reliability[M]. Leiden:Martinus Nijhoff Publishers,1987:70-72.
[20] 高镇同.疲劳应用统计学[M]. 北京:国防工业出版社,1986:277-295.GAO Z T. Fatigue application statistics[M]. Beijing:National Defence of Industry Press,1986:277-295(in Chinese).

孔边倒角裂纹当量初始缺陷尺寸的确定方法

Determination method of equivalent initial flaw size for crack initiated at hole chamfering

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	董虎, 林苗, 顾苏程, 曹毅, 李巍. 多向气动驱动器软体仿生舌弯曲状态的研究[J]. 北京航空航天大学学报, 2019, 45(9): 1882-1893.
[2]	靳涛, 胡小平, 于保华. 大端接圆柱杆的复合圆锥形变幅杆设计及应用[J]. 北京航空航天大学学报, 2019, 45(8): 1630-1638.
[3]	吕志峰, 张金生, 王仕成, 赵欣, 李婷. 基于智能优化算法和有限元法的多线圈均匀磁场优化设计[J]. 北京航空航天大学学报, 2019, 45(5): 980-988.
[4]	回丽, 陈晓伟, 周松, 杨文军, 王磊. 激光焊接带口盖加筋壁板剪切性能分析[J]. 北京航空航天大学学报, 2019, 45(3): 446-453.
[5]	包佳仪, 王兴伟, 周前祥, 谌玉红, 李晨明, 刘华蔚. 阻拦着舰过程中飞行员颈部的损伤分析与预测[J]. 北京航空航天大学学报, 2019, 45(3): 499-507.
[6]	陈金鹤, 汪正中, 马玉杰. 倾转旋翼机低速回避区研究[J]. 北京航空航天大学学报, 2019, 45(11): 2184-2192.
[7]	许昶, 刘志明. CFRP平-折-平连接接头试验研究与数值模拟[J]. 北京航空航天大学学报, 2019, 45(11): 2207-2216.
[8]	陈旻炜, 李敏, 陈伟民. 水平井多裂纹同步扩展的偏折分析[J]. 北京航空航天大学学报, 2019, 45(1): 99-108.
[9]	陈天雄, 张铮, 王奇志, 林彗星. 二维编织C/SiC复合材料板疲劳损伤分析[J]. 北京航空航天大学学报, 2019, 45(1): 192-199.
[10]	王印超, 全齐全, 于红英, 柏德恩, 邓宗全. 一种单压电叠堆驱动的回转冲击超声波钻[J]. 北京航空航天大学学报, 2018, 44(9): 1850-1859.
[11]	周睿, 周辉, 桂和利, 董虎, 曹毅. 基于柔性铰链的二自由度微动平台分析及优化[J]. 北京航空航天大学学报, 2018, 44(9): 1982-1990.
[12]	王凯, 何勇灵, 孟广威. 客车铝合金车架设计与典型工况分析[J]. 北京航空航天大学学报, 2018, 44(8): 1780-1786.
[13]	詹博文, 孙凌玉, 黄彬城, 赵冠博, 王倩. 车用复合材料螺旋弹簧的设计与优化[J]. 北京航空航天大学学报, 2018, 44(7): 1520-1527.
[14]	郭轩, 关志东, 邱诚, 黎增山. 蜂窝夹芯挖补修理结构弯曲性能研究[J]. 北京航空航天大学学报, 2018, 44(7): 1528-1536.
[15]	王远, 臧勇, 管奔, 秦勤. 基于单胞有限元的波纹板等效刚度特性[J]. 北京航空航天大学学报, 2018, 44(6): 1230-1238.