层合板单钉接头多级疲劳试验

王丹勇; 温卫东

层合板单钉接头多级疲劳试验

王丹勇¹,
温卫东²

1.
中国兵器工业集团第五三研究所, 济南250031
2.
南京航空航天大学能源与动力学院, 南京210016

计量
- 文章访问数: 1600
- HTML浏览量: 209
- PDF量: 879
- 被引次数: 0
出版历程
- 收稿日期: 2012-08-22
- 刊出日期: 2013-09-28

Experiment on single bolted joints in laminates under multilevel fatigue loading

WANG Dan-yong¹,
WEN Wei-dong²

1.
The Institute 53, China North Industries Group Corporation, Jinan 250031, China
2.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 为探讨层合板单钉接头在实际工作中多级疲劳破坏规律,首先通过特征尺寸为层合板端距与螺栓孔孔径之比为3、层合板宽度与螺栓孔孔径之比为3的层合板单钉接头准静态拉伸试验及常幅拉-拉疲劳试验,分析了层合板单钉接头实际损伤失效形式及单级疲劳破坏规律,为其多级疲劳试验各级应力水平的选取提供基础依据.然后对层合板单钉接头在载荷由高到低及由低到高2种加载方式2级载荷作用下的疲劳性能进行了试验研究,并使用经典线性累积损伤理论Miner法则分析计算了接头疲劳损伤值.结果表明:当应力水平由低向高施加时,疲劳损伤值大于1,而应力水平由高向低施加时,疲劳损伤值小于1.
- 层合板 /
- 单钉接头 /
- 多级 /
- 疲劳试验 /
- 破坏
Abstract: A series of quasi-static tension experiments and constant amplitude tension-tension fatigue experiments for researching the multilevel fatigue behavior under real cyclic loading were performed on single bolted joints in laminates with the ratio of the width of the laminate to the diameter of the central hole being 3 and the ratio of the distance between the central hole and the end of joint to the diameter of the central hole being 3. Real damage types and failure rules of single bolted joints in laminates were also discussed to provide the basis of stress level selecting of multilevel fatigue experiments.Finally,an experimental program of researching fatigue behavior under two-level fatigue for low-to-high and high-to-low loading sequence was conducted.Fatigue damage index was calculated and analyzed by using the classical linear progressive damage method of Miner rule.The results show that the fatigue damage index is larger than 1 when the loading sequence changes from low-level to high-level.On the contrary,the fatigue damage index is less than 1.
- laminates /
- single bolted joint /
- multilevel /
- fatigue experiment /
- failure

HTML

参考文献(15)

[1]	王丹勇,温卫东.有拧紧力矩层合板接头静载损伤失效分析[J].航空动力学报,2008,23(10):1835-1841. WANG Danyong,WEN Weidong.Damage failure analysis for composite bolted joints with tightening torque subjected to static loadings[J].Journal of Aerospace Power,2008,23(10):1835-1841.(in Chinese)
[2]	王丹勇,温卫东,崔海涛.复合材料单钉接头三维逐渐损伤破坏分析[J].复合材料学报,2005,22(3):168-174. WANG Danyong,WEN Weidong,CUI Haitao.Three-dimensional progressive damage analysis of single fastener joints in composite laminates[J].Acta Materiae Compositae Sinica,2005,22(3):168-174.(in Chinese)
[3]	王丹勇,温卫东,崔海涛.含材料非线性的复合材料单钉接头累积损伤分析[J].固体力学学报,2006,27(2):186-190. WANG Danyong,WEN Weidong,CUI Haitao.Progressive damage analysis considering the material nonlinearity of composite laminates containing a hole[J].Acta Mechanica Solida Sinica,2006,27(2):186-190.(in Chinese)
[4]	Tserpes K I,Labeas G,Papanikos P,et al.Stength prediction of bolted joints in graphite/epoxy composite laminates[J]. Composites: Part B Engineering,2002,33(7):521- 529.
[5]	Camanho P P,Matthews F L.A progressive damage model for mechanically fastened joints in composite laminates[J].Journal of Composite Materials,1999,33(24):2248-2280.
[6]	王丹勇.层合板接头损伤失效与疲劳寿命研究[D].南京:南京航空航天大学,2006. WANG Danyong.Research on prediction of damage failure and fatigue life for composite bolted joints[D].Nanjing: Nanjing University of Aeronautics and Astronautics,2006. (in Chinese)
[7]	王丹勇,温卫东.复合材料单钉接头疲劳累积损伤破坏分析[J].复合材料学报,2008,25(1):173-179. WANG Danyong,WEN Weidong.Fatigue progressive damage analysis of single fastener joints in composite laminates[J].Acta Materiae Compositae Sinica,2008,25(1):173-179.(in Chinese)
[8]	Shokrich M M,Lessard L B.Progressive fatigue damage modeling of composite materials:Part Ⅰ modeling[J].Journal of Composite Materials,2000,34(13):1056-1080.
[9]	Shokrich M M,Lessard L B.Progressive fatigue damage modeling of composite materials:Part Ⅱ material characterization and model verification[J].Journal of Composite Materials,2000,34(13):1081-1116.
[10]	Tserpes K I,Papanikos P,Labeas G,et al.Fatigue damage accumulation and residual strength assessment of CFRP laminates[J].Composite Structure,2004,63(2):219-230.
[11]	崔海涛,温卫东.CFRP双剪单钉连接接头强度分析[J].宇航材料工艺,2004,34(4):44-47. CUI Haitao,WEN Weidong.Strength analysis of single-bolted double-lapped joints in CFRP[J].Aerospace Materials and Technology,2004,34(4):44-47.(in Chinese)
[12]	中华人民共和国国家质量监督检验检疫总局.GB/T 1446-2005纤维增强塑料性能试验方法总则[S].北京:中国标准出版社,2005.
[13]	中华人民共和国国家质量监督检验检疫总局.GB/T 16779-2008纤维增强塑料层合板拉-拉疲劳性能试验方法[S].北京:中国标准出版社,2008.
[14]	中国航空研究院.复合材料连接手册[M].北京:航空工业出版社,1994.
[15]	王丹勇,温卫东.复合材料单钉接头损伤失效试验[J].航空动力学报,2008,23(2):286-292. WANG Danyong,WEN Weidong.Experiments on damage failure test of single bolted joints in composite laminates[J].Journal of Aerospace Power,2008,23(2):286-292.(in Chinese)