基于全机精细模型的非钉孔疲劳强度分析方法  

Fatigue strength analysis method of non-pinned hole based on the fine link finite element model of the whole aircraft

作　　者：李向哲 田忠良[1] 沈培良[1] 李三平[1] Li Xiangzhe;Tian Zhongliang;Shen Peiliang;Li Sanping(Shanghai Aircraft Design and Research Institute,Shanghai,201210,China)

机构地区：[1]上海飞机设计研究院,上海201210

出　　处：《机械设计与制造工程》2024年第10期73-77,共5页Machine Design and Manufacturing Engineering

摘　　要：针对传统基于自然网格模型的内力解疲劳强度分析方法在民用飞机非钉孔结构分析时存在的问题,采用更能反映结构细节特征的全机精细有限元模型,在传统疲劳强度分析方法基础上建立基于全机非钉孔结构的疲劳强度分析方法体系。首先依据全机精细模型的特点制定多级筛选计算流程;其次根据结构几何特征,合理保留易导致局部应力集中的单元作为疲劳源,通过引入飞续飞载荷谱最大单个循环损伤比、多轴应力等效、全向损伤评估等计算方法剔除大量低载单元;最后通过飞续飞疲劳载荷谱及人工甄别得到具有疲劳风险的单元,并以图形化方式对疲劳风险点的位置进行展示。整个体系有效平衡了计算精度和效率之间的矛盾,显示出良好的工程应用价值。Aiming at the issues existing in the traditional fatigue strength analysis method based on the natural mesh model internal force solution in the analysis of civil aircraft non-pinned hole structure,it uses the fine link finite element model of the whole aircraft that better reflects the detailed structural characteristics,establishes the fatigue strength analysis method system based on the traditional fatigue strength analysis method for the non-pinned hole structure of the whole aircraft.Firstly,a multi-level screening calculation process is formulated based on the characteristics of the fine model of the whole aircraft;secondly,according to the geometric characteristics of the structure,the units that are prone to local stress concentration are reasonably retained as the fatigue sources.Through the introduction of the maximum single cycle damage ratio of the flight-continuous flight load spectrum,multi-axis stress equivalence,omnidirectional damage assessment and other calculation methods to eliminate a large number of low-loaded units,it combines with the flight-continuous flight fatigue load spectrum and manual screening to get the fatigue risk of the unit,and graphically displays the location of the fatigue risk points.The whole system effectively balances the contradiction between calculation accuracy and efficiency,and shows good engineering application value.

关 键 词：民用飞机 精细有限元 疲劳 非钉孔 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]