裂纹参数和筋条布局对共振九宫板动态应力强度因子的影响

doi:10.7527/S1000-6893.2017.21423

固体力学与飞行器总体设计

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

裂纹参数和筋条布局对共振九宫板动态应力强度因子的影响

刘双燕, 李玉龙, 薛璞, 石霄鹏

西北工业大学航空学院航空结构工程系先进结构和材料研究所, 西安 710072

收稿日期:2017-05-16 修回日期:2017-10-22 出版日期:2018-01-15 发布日期:2018-01-15
通讯作者: 李玉龙,E-mail:liyulong@nwpu.edu.cn E-mail:liyulong@nwpu.edu.cn
基金资助:
国家自然科学基金（11472226，11572260）

Effect of crack parameters and stiffener layout on dynamic stress intensity factor of 3×3 grid stiffened panel at resonance

LIU Shuangyan, LI Yulong, XUE Pu, SHI Xiaopeng

Institute of Advanced Materials and Structures, Department of Aircraft Structures Engineering, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2017-05-16 Revised:2017-10-22 Online:2018-01-15 Published:2018-01-15
Supported by:
National Natural Science Foundation of China (11472226, 11572260)

摘要/Abstract

摘要： 由于裂纹的出现会改变振动结构的断裂行为，本文建立了含中心裂纹九宫板结构的有限元模型并采用模态叠加原理快速求解出该结构在共振条件下的裂纹尖端应力强度因子（SIF），然后分析并讨论了裂纹参数（偏转角度和裂纹长度）及筋条布局对应力强度因子的影响。结果表明：随着裂纹偏转角度的增加，Ⅰ、Ⅱ和Ⅲ型应力强度因子最大值分别表现出不同的变化趋势（单调增加、无显著变化、先增加后减小）；裂纹长度同时影响应力强度因子最大值和裂纹类型；对于裂纹参数相同的九宫板，筋条布局改变了结构的模态振型，从而导致不同裂纹类型出现；特别地，当九宫板中央区域为正方形时，应力强度因子最大值和裂纹类型对裂纹偏转角度不敏感。

关键词: 共振, 九宫板, 中心裂纹, 模态应力强度因子, 动态应力强度因子, 裂纹长度, 偏转角度

Abstract: The fatigue crack generated during vibration would affect the fracture in structures. The 3×3 grid stiffened panel with the center crack was modeled using the finite element method. The modal recombination method was applied to rapidly compute the values of the Stress Intensity Factor (SIF) of crack tip in the panel at resonance. The influence of crack parameters (inclined angle and crack length) and the stiffener layout on SIF values was analyzed. The result shows that the maximum SIF values of the structures for Mode Ⅰ, Mode Ⅱ and Mode Ⅲ showed different trends as the inclined angle of the crack increased (monotonically increase, no significant change, and increase first and then decrease). The maximum SIF values and crack mode were affected by the crack length. For the panels with the same crack parameters, different distribution of the stiffener results in different vibration shape, and thus causes different types of cracks. In particular, effect of the crack inclined angle on the SIF amplitude and crack mode can be ignored when the center region of the panel is square.

Key words: resonance, 3×, 3 grid stiffened panel, center crack, mode stress intensity factor, dynamic stress intensity factor, crack length, inclined angle

中图分类号:

刘双燕, 李玉龙, 薛璞, 石霄鹏. 裂纹参数和筋条布局对共振九宫板动态应力强度因子的影响[J]. 航空学报, 2018, 39(1): 221423-221423.

LIU Shuangyan, LI Yulong, XUE Pu, SHI Xiaopeng. Effect of crack parameters and stiffener layout on dynamic stress intensity factor of 3×3 grid stiffened panel at resonance[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(1): 221423-221423.

参考文献

[1] 姚起杭, 姚军. 工程结构的振动疲劳问题[J]. 应用力学学报, 2006, 23(1):12-15. YAO Q H, YAO J. Vibration fatigue in engineering structures[J]. Chinese Journal of Applied Mechanics, 2006, 23(1):12-15(in Chinese).[2] PAIRS P C, GOMEZ M P, ANDERSON M E. A rational analytical theory of fatigue[J]. Trends in Enginneering, 1961, 13:9-14.[3] 张浩宇, 何宇廷, 冯宇, 等. 先进复合材料薄壁加筋板轴压屈曲特性及后屈曲承载性能[J]. 航空材料学报, 2016, 36(4):55-63. ZHANG H Y, HE Y T, FENG Y, et al. Buckling and post-buckling performance of advanced composite stiffened panel under compression[J]. Journal of Aeronacutical Materials, 2016, 36(4):55-63(in Chinese).[4] 王燕, 李书, 许秋怡, 等. 复合材料加筋板剪切后屈曲分析与优化设计[J]. 航空学报, 2016, 37(5):1512-1525. WANG Y, LI S, XU Q Y, et al. Optimization design and analysis of stiffened composite panels in post-buckling under shear[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(5):1512-1525(in Chinese).[5] KUMAR Y V S, PAIK J K. Buckling analysis of cracked plates using hierarchical trigonometric functions[J]. Thin-Walled Structures, 2004, 42(5):687-700.[6] LEI Z, BAI R, TAO W, et al. Optical measurement on dynamic buckling behavior of stiffened composite panels under in-plane shear[J]. Optics and Lasers in Engineering, 2016, 87:111-119.[7] MOUHAT O, ABDELLATIF K. Dynamic buckling of stiffened panels[J]. Procedia Engineering, 2015, 125:1001-1007.[8] 王博, 田阔, 郑岩冰, 等. 超大直径网格加筋筒壳快速屈曲分析方法[J]. 航空学报, 2017, 38(2):220379. WANG B, TIAN K, ZHENG Y B, et al. A rapid buckling analysis method for large-scale grid-stiffened cylindrical shells[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(2):220379(in Chinese).[9] PAIK J K, SATISH KUMAR Y V, LEE J M. Ultimate strength of cracked plate elements under axial compression or tension[J]. Thin-Walled Structures, 2005, 43(2):237-272.[10] CUI C, YANG P, LI C, et al. Ultimate strength characteristics of cracked stiffened plates subjected to uniaxial compression[J]. Thin-Walled Structures, 2017, 113:27-38.[11] SHI X H, ZHANG J, GUEDES SOARES C. Experimental study on collapse of cracked stiffened plate with initial imperfections under compression[J]. Thin-Walled Structures, 2017, 114:39-51.[12] 陈安, 魏玉龙, 廖江海, 等. 机身加筋壁板复合加载损伤容限性能试验[J]. 航空学报, 2017, 38(1):420093. CHEN A, WEI Y L, LIAO J H, et al. Damage tolerance test of stiffened fuselage panel under complex load[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(1):420093(in Chinese).[13] 刘双燕, 李玉龙, 邓琼, 等. 基于ESO法的九宫板阻尼结构的优化设计方法[J]. 振动与冲击, 2016, 35(22):197-203. LIU S Y, LI Y L, DENG Q, et al. Topological optimization design of 3×3 grid stiffened panel with additional damping layers based on evolutionary structural optimization[J]. Journal of Vibration and Shock, 2016, 35(22):197-203(in Chinese).[14] 中国航空研究院. 应力强度因子手册[M]. 北京:科学出版社, 1981:1-30. Chinese Aeronacutical Establishment. Stress intensity factor handbook[M]. Beijing:Science Press, 1981:1-30(in Chinese).[15] 程靳, 赵树山. 断裂力学[M]. 北京:科学出版社, 2014:57-82. CHENG J, ZHAO S S. Fracture mechanics[M]. Beijing:Science Press, 2014:57-82(in Chinese).[16] DOYLE J F, RIZZI S A. Frequency domain stress intensity calibration of damped cracked panels[J]. International Journal of Fracture, 1993, 61(2):123-130.[17] GALENNE E, ANDRIEUX S, RATIER L. A modal approach to linear fracture mechanics for dynamic loading at low frequency[J]. Journal of Sound and Vibration, 2007, 299(1-2):283-297.[18] ALBUQUERQUE C, CASTRO P, CALCADA R. Efficient crack analysis of dynamically loaded structures using a modal superposition of stress intensity factors[J]. Engineering Fracture Mechanics, 2012, 93:75-91.[19] TRAN V X, GENIAUT S, GALENNE E, et al. A modal analysis for computation of stress intensity factors under dynamic loading conditions at low frequency using eXtended finite element method[J]. Engineering Fracture Mechanics, 2013, 98:122-136.[20] 邱吉宝, 向树红, 张正平. 计算结构动力学[M]. 合肥:中国科学技术大学出版社, 2009:181-182. QIU J B, XIANG S H, ZHANG Z P. Computational structural dynamics[M]. Hefei:University of Science and Technology of China Press, 2009:181-182(in Chinese).[21] HAN Q, WANG Y, YIN Y, et al. Determination of stress intensity factor for mode I fatigue crack based on finite element analysis[J]. Engineering Fracture Mechanics, 2015, 138:118-126.[22] 姜伟, 杨平, 董琴. 平板穿透裂纹尖端动态应力强度因子研究[J]. 武汉理工大学学报(交通科学与工程版), 2016, 40(5):820-825. JIANG W, YANG P, DONG Q. Research on dynamic stress intensity factors for through-cracked plates[J]. Journal of Wuhan University of Technology (Transportation Science & Engineering),2016, 40(5):820-825(in Chinese).[23] ZHU W X, SMITH D J. On the use of displacement extrapolation to obtain crack tip singular stresses and stress intensity factors[J]. Engineering Fracture Mechanics, 1995, 51(3):391-400.[24] GUINEA G V, PLANAS J, ELICES M. K_I evaluation by the displacement extrapolation technique[J]. Engineering Fracture Mechanics, 2000, 66(3):243-255.[25] QIAN G, GONZÁLEZ-ALBUIXECH V F, NIFFENEGGER M, et al. Comparison of K_I calculation methods[J]. Engineering Fracture Mechanics, 2016, 156:52-67.[26] 戴德沛. 阻尼减振降噪技术[M]. 西安:西安交通大学出版社, 1986:16. DAI D P. Damping technology in vibration and noise reduction[M]. Xi'an:Xi'an Jiaotong University Press, 1986:16(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

裂纹参数和筋条布局对共振九宫板动态应力强度因子的影响

Effect of crack parameters and stiffener layout on dynamic stress intensity factor of 3×3 grid stiffened panel at resonance

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]	张依宁, 温昶煊, 庞博, 朱天昊, 何嘉欣, 金紫涵. 基于高精度回归共振的掩星观测轨道设计[J]. 航空学报, 2024, 45(8): 329151-329151.
[2]	杨雄, 李小康, 郭大伟, 程谋森, 张帆, 车碧轩, 雷清雲. 高功率波加热磁等离子体推力器研究现状与展望[J]. 航空学报, 2024, 45(7): 28761-028761.
[3]	王洛烽, 陈仁良. 吊挂飞行对重型直升机空中共振稳定性的影响机理分析[J]. 航空学报, 2023, 44(16): 227983-227983.
[4]	许志远, 杨明绥, 王萌. 压气机声共振特性理论预测与试验研究[J]. 航空学报, 2023, 44(14): 628236-628236.
[5]	赖佑奎, 马海腾, 刘一粟, 欧阳华. 基于磁共振测速的复合冷却涡轮叶片流动分析[J]. 航空学报, 2023, 44(14): 627920-627920.
[6]	陈毅, 侯磊, 林荣洲, 杨洋, 陈予恕. 机动飞行环境下双转子系统主共振特性分析[J]. 航空学报, 2022, 43(1): 224841-224841.
[7]	王洛烽, 陈仁良. 重型直升机飞行动力学刚弹耦合建模及空中共振稳定性分析[J]. 航空学报, 2021, 42(12): 124634-124634.
[8]	李耀华, 巩子瑜. 基于改进FRAM的民机系统安全性分析[J]. 航空学报, 2020, 41(12): 324083-324083.
[9]	于惠勇, 李华峰, 曾捷, 徐志伟, 黄继伟, 赵启迪. 可变弯度机翼后缘形态重构光纤监测技术[J]. 航空学报, 2020, 41(10): 223808-223808.
[10]	洪志亮, 赵国昌, 杨明绥, 孙晓峰. 航空发动机压气机内部流体诱发声共振研究进展[J]. 航空学报, 2019, 40(11): 23139-023139.
[11]	温卓群, 王鹏飞, 张雁, 蒋艳芬. 面向大尺度结构的力学超材料减振技术[J]. 航空学报, 2018, 39(S1): 721651-721651.
[12]	胡国才, 吴靖, 刘湘一, 刘书岩. 垂直着陆中直升机旋翼动力学行为研究[J]. 航空学报, 2018, 39(6): 221355-221355.
[13]	刘玉亮, 邬树楠, 张开明, 吴志刚. 重力姿轨耦合效应引起的太阳能电站轨道共振[J]. 航空学报, 2018, 39(12): 222194-222194.
[14]	吴靖, 胡国才, 柳泉, 刘湘一. 基于直升机地面共振要求的起落架刚度及阻尼优化设计[J]. 航空学报, 2018, 39(12): 222027-222027.
[15]	谭光辉, 李秋彦, 邓俊. 热环境下结构固有振动特性试验及分析[J]. 航空学报, 2016, 37(S1): 32-37.