Volume 47 Issue 12
Dec.  2021
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ZUO Randong, HE Xiaofan, LI Yuhaiet al. Parameter determination method of relative small crack growth rate formula in durability analysis[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(12): 2594-2601. doi: 10.13700/j.bh.1001-5965.2020.0492(in Chinese)
Citation: ZUO Randong, HE Xiaofan, LI Yuhaiet al. Parameter determination method of relative small crack growth rate formula in durability analysis[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(12): 2594-2601. doi: 10.13700/j.bh.1001-5965.2020.0492(in Chinese)

Parameter determination method of relative small crack growth rate formula in durability analysis

doi: 10.13700/j.bh.1001-5965.2020.0492
Funds:

National Key R & D Program of China 2017YFB1104003

National Natural Science Foundation of China 11772027

Aeronautical Science Foundation of China 201909051002

More Information
  • Corresponding author: HE Xiaofan, E-mail: xfhe@buaa.edu.cn
  • Received Date: 02 Sep 2020
  • Accepted Date: 19 Sep 2020
  • Publish Date: 20 Dec 2021
  • Relative small crack growth rate formula of structural details is the key to durability analysis using probabilistic fracture mechanics method. In order to determine the applicable range and parameters of the formula, it is necessary to carry out group fatigue tests under multiple stress levels, which is too complex. To solve this problem, in this paper, first, the stress intensity factor correction coefficient is expanded to a polynomial, and the relative small crack growth rate formula for durability analysis is obtained based on the crack growth rate formula of material stable crack growth section. Then, various crack growth of the central hole plate subjected to far-field uniform tensile load is analyzed based on the approximate solution of stress intensity factor and FRANC3D software, and a method is obtained to determine the relative small crack size range and the corresponding crack growth parameters. Finally, the correctness of the method is verified by durability tests of three specimens under constant amplitude alternating stress.

     

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  • [1]
    中国人民解放军总装备部. 军用飞机结构完整性大纲: GJB 775A—2012[S]. 北京: 总装备部军标出版发行部, 2012.

    General Armament of the Chinese People's Liberation Army. Military aircraft structural integrity program: GJB 775A—2012[S]. Beijing: Military Standard Publishing and Distribution Department of General Equipment Department, 2012(in Chinese).
    [2]
    中华人民共和国工业和信息化部. 民用飞机结构耐久性设计准则: HB/Z 413—2013[S]. 北京: 中国航空综合技术研究所, 2013.

    Ministry of Industry and Information Technology of the People's Repldblic of China. Civil aircraft durability design criteria: HB/Z 413—2013[S]. Beijing: Military Standard Publishing and Distribution Department of General Equipment Department, 2013(in Chinese).
    [3]
    丁传富, 刘建中, 吴学仁. TC4钛合金和7475铝合金的长裂纹和小裂纹扩展特性的研究[J]. 航空材料学报, 2005, 25(6): 11-17. https://www.cnki.com.cn/Article/CJFDTOTAL-HKCB200506002.htm

    DING C F, LIU J Z, WU X R. An investigation of small-crack and long-crack propagation behavior in titanium alloy TC4 and aluminum alloy 7475-T7351[J]. Journal of Aeronautical Materials, 2005, 25(6): 11-17(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-HKCB200506002.htm
    [4]
    MILLER K J. The behaviour of short fatigue cracks and their initiation. Part Ⅱ-A general summary[J]. Fatigue & Fracture of Engineering Materials and Structures, 1987, 10(2): 93-113.
    [5]
    NEWMAN JR J C, PHILLIPS E P, SWAIN M H. Fatigue-life prediction methodology using small-crack theory[J]. International Journal of Fatigue, 1999, 21(2): 109-119. doi: 10.1016/S0142-1123(98)00058-9
    [6]
    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: 144-148.

    LIU W T. Probabilistic fracture mechanics and probabilistic damage tolerance/durability[M]. Beijing: Beihang University Press, 1999: 144-148(in Chinese).
    [7]
    FROST N E, DUGDALE D S. The propagation of fatigue cracks in sheet specimens[J]. Journal of the Mechanics and Physics of Solids, 1958, 6(2): 92-110. doi: 10.1016/0022-5096(58)90018-8
    [8]
    BARTER S, ATHINIOTIS N, CLARK G. The identification of fatigue-critical regions during fatigue testing of Macchi MB326H centre section lower booms[M]//KARIHALOO B L, MAI Y W, RIPLEY M I, et al. Advances in fracture research. Amsterdam: Elsevier, 1997: 447-455.
    [9]
    CLARK G, BARTER S, GOLDSMITH N T. Influence of initial defect conditions on structural fatigue in RAAF aircraft[M]//BLOM A. Durability and structural reliability of airframes Vol 1. Warley: EMAS, 1993: 281-304.
    [10]
    JONES R, BARTER S, MOLENT L, et al. Crack patching: An experimental evaluation of fatigue crack growth[J]. Composite Structures, 2005, 67(2): 229-238. doi: 10.1016/j.compstruct.2004.09.020
    [11]
    MOLENT L, JONES R, BARTER S, et al. Recent developments in fatigue crack growth assessment[J]. International Journal of Fatigue, 2006, 28(12): 1759-1768. doi: 10.1016/j.ijfatigue.2006.01.004
    [12]
    YANG J N, MANNING S D, GARVER W R. Durability methods development. Volume V. Durability analysis methodology development[R]. [S. l. ]: General Dynamics, Fort Worth Division, 1979.
    [13]
    GALLAGHER J P, STALNAKER H D. Predicting flight by flight fatigue crack growth rates[J]. Journal of Aircraft, 1975, 12(9): 699-705. doi: 10.2514/3.59861
    [14]
    GALLAGHER J P, STALNAKER H D. Methods for analyzing fatigue crack growth rate behavior associated with flight-by-flight loading[C]//15th Structural Dynamics and Materials Conference. Reston: AIAA, 1974.
    [15]
    HOEPPNER D W, KRUPP W E. Prediction of component life by application of fatigue crack growth knowledge[J]. Engineering Fracture Mechanics, 1974, 6(1): 47-70. doi: 10.1016/0013-7944(74)90046-0
    [16]
    刘文珽, 姜军, 李贵文, 等. 某歼击机机身主承力框的耐久性分析[J]. 航空学报, 1992, 13(3): 187-192. doi: 10.3321/j.issn:1000-6893.1992.03.012

    LIU W T, JIANG J, LI G W, et al. Durability analysis for a main bulkhead subjected to load on the body of an aircraft[J]. Acta Aeronautica et Astronautica Sinica, 1992, 13(3): 187-192(in Chinese). doi: 10.3321/j.issn:1000-6893.1992.03.012
    [17]
    刘小冬, 刘文珽. 结构使用寿命评定的功能失效概率控制方法[J]. 北京航空航天大学学报, 2002, 28(1): 105-108. doi: 10.3969/j.issn.1001-5965.2002.01.027

    LIU X D, LIU W T. Structural function failure probability control method for service life estimation[J]. Journal of Beijing University of Aeronautics and Astronautics, 2002, 28(1): 105-108(in Chinese). doi: 10.3969/j.issn.1001-5965.2002.01.027
    [18]
    SHAH R C. Stress intensity factors for through and part-through cracks originating at fastener holes [C]//ASTM Special Technical Publications, 1976: 429-459.
    [19]
    RAJU I S, NEWMAN J C. Stress-intensity factors for two symmetric corner cracks[C]//ASTM Special Technical Publications, 1979: 411-430.
    [20]
    NEWMAN J C, RAJU I S. Stress-intensity factor equations for cracks in three-dimensional finite bodies: NASA-TM-85793[R]. Washington, D.C. : NASA, 1986: 311-334.
    [21]
    DONG Y H, HE X F, LI Y H. Marker load-aided bidirectional fatigue crack growth rate measurement via a semi-elliptical surface crack[J]. International Journal of Fatigue, 2018, 111: 208-219. doi: 10.1016/j.ijfatigue.2018.02.010
    [22]
    汝继刚, 伊琳娜. 7B04铝合金疲劳断裂性能研究[J]. 轻合金加工技术, 2007, 35(10): 38-40. doi: 10.3969/j.issn.1007-7235.2007.10.014

    RU J G, YI L N. Research about fatique and fracture properties of 7B04 aluminium alloy[J]. Light Alloy Fabrication Technology, 2007, 35(10): 38-40(in Chinese). doi: 10.3969/j.issn.1007-7235.2007.10.014
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