航空学报 > 2021, Vol. 42 Issue (5): 524328-524328   doi: 10.7527/S1000-6893.2020.24328

一种多部位损伤全寿命分析的工程方法

奚蔚1,2, 李强1, 沈培良1, 何瑞2, 杨刚1, 刘世杰1   

  1. 1. 中国商飞上海飞机设计研究院 机体集成部, 上海 201210;
    2. 中国商飞上海飞机制造有限公司 复合材料中心, 上海 201324
  • 收稿日期:2020-08-17 修回日期:2020-10-15 出版日期:2021-05-15 发布日期:2020-12-03
  • 通讯作者: 奚蔚 E-mail:xiwei@comac.cc
  • 基金资助:
    民用飞机专项科研技术研究项目(MJ-2016-F-15)

Full life engineering analysis method for multiple site damage

XI Wei1,2, LI Qiang1, SHEN Peiliang1, HE Rui2, YANG Gang1, LIU Shijie1   

  1. 1. Airframe Integration Department, COMAC Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;
    2. Composites Center, COMAC Shanghai Aircraft Manufacturing Co. Ltd., Shanghai 201324, China
  • Received:2020-08-17 Revised:2020-10-15 Online:2021-05-15 Published:2020-12-03
  • Supported by:
    Civil Aircraft Scientific Research Project (MJ-2016-F-15)

摘要: 提出了一种多部位损伤全寿命分析的工程方法,该方法包含3部分内容。对多裂纹萌生问题,通过研究多细节结构中裂纹萌生机理,将裂纹萌生寿命的取值事件转化为3个独立事件的积事件,前者的发生概率等于3个独立事件发生概率的乘积,3个独立事件的发生概率可由单细节结构裂纹萌生寿命的概率分布求得。从而可由单细节结构裂纹萌生寿命概率分布得到多细节结构中依次出现的各条裂纹的萌生寿命的概率分布。对多裂纹扩展问题,先通过有限元方法计算出多裂纹指定长度组合下的应力强度因子,然后引入响应面法,定量地建立了裂纹长度与应力强度因子之间的函数关系,由响应面模型得到多裂纹任意长度组合下的应力强度因子,最后采用循环接循环法进行裂纹扩展分析。对多裂纹结构失效分析,采用亚临界条件判断结构是否失效,认为结构上萌生的首条裂纹与第2条裂纹的位置相邻,裂纹发生首次连通时,结构失效。进行了单细节带孔板与多细节带孔板的裂纹萌生扩展试验,并对多细节带孔板的裂纹萌生扩展寿命和首次裂纹连通寿命进行了预测。预测结果和试验结果吻合良好,表明该方法是有效的。

关键词: 多部位损伤, 裂纹萌生寿命, 积事件, 概率分布, 裂纹扩展寿命, 裂纹连通

Abstract: An engineering method of full life for structure with multiple site damage is proposed. consists of three parts. For multiple crack initiation, the incident crack initiation life of multiple detail structure with a certain value is transformed into the intersection of three independent incidents. The probability of the former incident is the product of the probability of the latter three independent incidents derived from the probability distribution function of crack initiation life of single detail structure. Thus, the probability distribution functions of initiation for cracks occurring in turn in multiple detail structure are obtained. For multiple crack propagation, the stress intensity factor the specified length combination of multiple cracks is calculated the finite element method. The response surface method is introduced functional relationship between crack length and stress intensity factor. The stress intensity factor of the multiple crack arbitrary length combination is obtained from the response surface model. Finally, the crack propagation analysis is performed using the cycle-by-cycle technique. For failure analysis of multiple crack structure, subcritical conditions are to determine the failure. he first crack in the structure is adjacent to the position of the second crackthe crack linkup failure. Crack initiation and propagation specimens with a hole notch and hole notches carried out model. agreement testing results this model.

Key words: multiple site damage, crack initiation life, intersection of incidents, probability distribution, crack propagation life, crack linkup

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