飞机典型连接结构多位置损伤实验设计及验证  

Experimental Design and Verification of Typical Aircraft Joint Structures With Multiple Site Damage

作　　者：饶聃钰 徐武[1] 张博 余音[1] 王旭 RAO Danyu;XU Wu;ZHANG Bo;YU Yin;WANG Xu(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China;Shanghai Aircraft Airworthiness Certification Center of Civil Aviation of China,Shanghai 200335,China)

机构地区：[1]上海交通大学航空航天学院,上海200240 [2]中国民用航空上海航空器适航审定中心,上海200335

出　　处：《机械设计与研究》2021年第5期148-153,164,共7页Machine Design And Research

摘　　要：适航要求飞机设计商需评定广布疲劳损伤(WFD)建立有效性限制(LOV),以保证飞机服役期间结构不会发生WFD而导致灾难性事故。采用三维有限元分析多位置损伤(MSD)敏感结构,通过优化试样尺寸、合理选择铆钉和螺钉,设计了搭接、对接两类共线8孔铆钉连接结构,使得同排共线孔孔边具有相似应力分布特征且偏心弯曲小,能够随机萌生疲劳裂纹。通过实验验证了这些结构疲劳实验均随机萌生多裂纹,并给出了这两类典型飞机连接结构的多位置损伤实验裂纹萌生和结构失效寿命的平均行为。Airworthiness certification requires the aircraft designers to assess widespread fatigue damage(WFD)and establish limit of validity(LOV)in order to ensure that WFD will not occur in service.In this paper,threedimensional finite element analysis was used to analyze the structure susceptible to multiple site damage(MSD).Two types of eight collinear hole structures,lap-joint type and butt-joint type,were designed by optimizing the sizes of the specimen and selecting reasonable rivets and bolts.The design is to achieve that the collinear hole edges have similar stress distribution,and the influence of eccentric bending is reduced to a certain extent.It proves in all fatigue experiments that multiple cracks were randomly initiated.The crack initiation and propagation process of the multiple cracks were recorded for these two typical types of joint structures,and their average life behaviors of crack initiation and structure failure were determined.

关 键 词：多位置损伤 实验设计 疲劳实验 裂纹萌生 裂纹扩展 

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]