飞机典型连接结构原始疲劳质量评估  

ASSESSMENT ON INITIAL FATIGUE QUALITY OF AIRCRAFT TYPICAL CONNECTED STRUCTURE

作　　者：张胜[1] 何宇廷[1] 张腾[1] 李昌范[1] 张浩宇[1] 

机构地区：[1]空军工程大学航空航天工程学院,西安710038

出　　处：《机械强度》2016年第3期480-484,共5页Journal of Mechanical Strength

基　　金：国家自然科学基金项目(51475470;51505495)资助~~

摘　　要：在谱载下对单片通孔试件及三种不同长度的双片紧固孔试件进行了耐久性试验研究。考虑螺栓干涉量、螺栓紧固力等特征,通过三维有限元仿真得到了结构的薄弱部位。根据结构的耐久性试验分析结果,提出了一种用于结构原始疲劳质量(IFQ)评估的"裂纹超越数概率比较法",并建立了各组试件的控制应力水平曲线与之对比。结果表明,本文提出的结构IFQ评估方法有效,双片紧固孔试件的IFQ高于单片通孔试件,且随结构长度的减小而提高。Durability experimental study is performed on single-piece specimens with through-hole and double-piece specimens with fastening holes of three different lengths on random loading. The weak area of structures is gained through threedimensional finite element analysis,considering pre tightening force of bolts and the interference fit between bolts and holes.Based on the results of durability experimental analysis,a new method is put forward to assess the initial fatigue quality（ IFQ） of structures and controlled stress curves are drawn to compare with this method. As a result,the method to assess IFQ of structures in this paper is proved to be effective. The IFQ of double-piece specimens with fastening holes is higher than that of single-piece specimens with through-hole. Furthermore,the IFQ increases with the decreasing of the length of the structure.

关 键 词：耐久性 原始疲劳质量 当量初始缺陷尺寸 有限元分析 

分 类 号：V215.6[航空宇航科学与技术—航空宇航推进理论与工程] O346.1[理学—固体力学]