层合板螺栓连接结构疲劳寿命预测

doi:10.7527/S1000-6893.2014.0164

Abstract

Abstract:

In order to accurately predict the onset and progression of composite structures fatigue damage, a method on the basis of unidirectional laminates fatigue property is used to predict the fatigue life of laminated bolted joint structures. The primary task is fitting the parameter of normalized life model and residual strength by T300/BMP-316 laminates test data. An improved fracture toughness-based failure criterions are used to determine fatigue damage onset and propagation, while fiber and delamination failure criterion is added to matrix-dominated failure rule. A two-state load equivalent model is introduced to accumulate damage nonlinear before material property degradation. The error between predicted logarithm fatigue life and test results of different laminated composite structures is within 5% and the error at different stress levels is within 10%; the failure mode and failure region are shown to correlate well with test results.

Key words: composite materials, bolted joints, fatigue damage, fracture toughness, life cycle

CLC Number:

V258⁺.3

LIU Jianming, WAN Xiaopeng, ZHAO Meiying. Fatigue life prediction of laminated bolted joint structures[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1867-1875.

References

[1] Pan Y X, Tong X Y, Li B. Experimental research on fatigue behavior of composites using energy dissipation methodology[J]. Structure & Environment Engineering, 2009, 36(1): 51-56 (in Chinese). 潘应雄, 童小燕, 李斌. 复合材料疲劳性能的能量耗散试验研究[J]. 强度与环境, 2009, 36(1): 51-56.
[2] Lian W, Yao W X. Residual stiffness-residual strength coupled model of composite laminates[J]. Acta Materiae Compositae Sinica, 2008, 25(5): 151-156 (in Chinese). 廉伟, 姚卫星. 复合材料层压板剩余刚度-剩余强度关联模型[J]. 复合材料学报, 2008, 25(5): 151-156.
[3] Min J B, Xue D, Shi Y. Micromechanics modeling for fatigue damage analysis designed for fabric reinforced ceramic matrix composites[J]. Composite Structures, 2014, 111: 213-223.
[4] Naderi M, Maligno A R. Fatigue life prediction of carbon/epoxy laminates by stochastic numerical simulation[J]. Composite Structures, 2012, 94(3): 1052-1059.
[5] Nikishkov Y, Makeev A, Seon G. Simulation of damage in composites based on solid finite elements[J]. Journal of the Americal Helicopter Society, 2010, 55(4): 042009.
[6] Hahn H T, Johannesson T. Mechanics of composite mterials[M]. New York: Pergamon Press, 1983: 135-142.
[7] Davila C G, Camanho P P, Rose C A. Failure criteria for FRP laminates[J]. Journal of Composite Materials, 2005, 39(4): 323-345.
[8] Camanho P P, Davila C G, Pinho S T, et al. Prediction of in situ strengths and matrix cracking in composites under transverse tension and in-plane shear[J]. Composites Part A: Applied Science and Manufacturing, 2006, 37(2): 165-176.
[9] Makeev A, Seon G, Lee E. Failure predictions for carbon/epoxy tape laminates with wavy plies[J]. Journal of Composite Materials, 2010, 44(1): 95-112.
[10] Manson S S, Halford G R. Practical implementation of the double linear damage rule and damage curve appoach for treating cumulative fatigue damage[J]. International Journal Fracture, 1981, 17(2): 169-192.
[11] Harris B, Gathercole N, Lee J A. Life-prediction for constant-stress fatigue in carbon-fibre composites[C]//Philosophical Transactions of the Royal Society of London A, 1997, 355: 1259-1294.
[12] Shokrieh 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.
[13] Wang D Y. Research on prediction of damage failure and fatigue life for composite bolted joints[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2006 (in Chinese). 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.
[14] Gathercole N, Reiter H, Adam T. Life prediction for fatigue of T800/5435 carbon-fibre composites: 2 constant amplitude loading[J]. International Journal of Fatigue, 1994, 16(8): 523-532.
[15] Camanho P P, Matthews F L. A progressive damage model for mechanically fastened joints in composite laminates[J]. Journal of Composite Materials, 1999, 23(24): 2248-2280.
[16] Wu F Q, Yao W X. S-N curve model of composite laminate[J]. Journal of Mechanical Strength, 2004, 26(S1): 127-129 (in Chinese). 吴富强, 姚卫星. 一种复合材料层合板的S-N曲线模型[J]. 机械强度, 2004, 26(S1): 127-129.

Fatigue life prediction of laminated bolted joint structures

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	WAN Aoshuang. Probabilistic assessment on damage tolerance of composite helicopter horizontal tail structure [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525557-525557.
[2]	CAO Zhenzhong, ZHANG Fan, ZHANG Dingguo, YU Yi. Containment of aero-engine casing with bolted flanges [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(9): 224563-224563.
[3]	ZHANG Junrui, ZHENG Xitao, YUAN Lin, ZHONG Guiyong, LI Guochen. Fatigue life prediction method for hybrid multi-bolted joints based on damage weight [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(5): 524306-524306.
[4]	LI Ni, BU Shuhui, SHANG Bolin, LI Yongbo, TANG Zhili, ZHANG Weiwei. Aircraft intelligent design: Visions and key technologies [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(4): 524752-524752.
[5]	WANG Houbing, WEI Jingchao, CHENG Li'nan, LI Xinxiang, ZHAO Rong. Force sensor for axial force and shear force of bolts in joints [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 424459-424459.
[6]	CAO Yuejie, WEI Lingfeng, ZHANG Minghao, CAO Zengqiang. Experimental study on progressive failure mechanism of thin-laminate bolted joints [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(12): 424667-424667.
[7]	WANG Binwen, AI Sen, ZHANG Guofan, NIE Xiaohua, WU Cunli. Validation method for post-buckling analysis model of stiffened composite panels considering uncertainties [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(8): 223987-223987.
[8]	ZHANG Bainan, QI Faren, XING Tao, LIU Yang, WANG Wei. Model based development method of manned spacecraft: Research and practice [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(7): 23967-023967.
[9]	ZHAO Yan, SONG Jiangtao, TANG Ning. Construction of safety-predicting load model on certain wing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(10): 223852-223852.
[10]	HU Qixian, WANG Zhuojian, YU Huan. Partition of line replaceable units in aircraft based on clustering of key components [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(11): 223245-223245.
[11]	YU Yanyan, ZHANG Yuan, GAO Limin, QU Shuxuan, LYU Weibang. Toughness enhancement for interlaminar fracture composite based on carbon nanotube films [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(10): 422900-422900.
[12]	ZHAO Libin, GONG Yu, ZHANG Jianyu. A survey on delamination growth behavior in fiber reinforced composite laminates [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(1): 522509-522509.
[13]	HAN Guangzhao, CAI Lixun, YAO Di, YU Simiao. Fracture criterion and plane-strain fracture toughness of ductile materials [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(8): 221852-221852.
[14]	LI Zhenghong, XU Wu, ZHANG Xiaojing, YU Yin. Experimental and analytical analyses of fatigue crack growth in sheets with multiple holes and cracks [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(7): 221867-221867.
[15]	CUI Ronghong, LIU Kai, HOU Bo, TAN Xiangfei, HE Yuting. Crack monitoring based on high durability film sensor in coupled environment [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(3): 421535-421535.