民用飞机蒙皮加筋壁板损伤容限分析方法探讨  

Analysis of Damage Tolerance for Civil Aircraft Stiffened Skin Panel

作　　者：徐力君[1] 王东方[1] 刘旭[1] 

机构地区：[1]中航沈飞民用飞机有限责任公司,沈阳110013

出　　处：《民用飞机设计与研究》2015年第2期34-36,88,共4页Civil Aircraft Design & Research

摘　　要：主要介绍了民用飞机蒙皮加筋壁板损伤容限的分析方法,以中间筋条断裂的两跨纵向裂纹为例,将影响结构损伤容限特性的因素分为三部分进行计算,分别是加筋效应、鼓胀效应以及应力分布效应,最终得到相对应的裂纹尖端的应力强度因子并且进行裂纹扩展分析及剩余强度计算。文中选取实例采用这种方法进行计算,并将计算结果与试验数据对比,两者吻合较好,说明了本方法的可行性及实用性。This article introduces a method of damage tolerance analysis of stiffened skin panel for civil aircraft, shown by an example of panel with two-bay longitudinal crack and center broken frame, taking into account three parts of factors ： stiffening effect, bulging effect and the stress distribution. Stress intensity factor at each crack tip is derived from combination of above mentioned three factors. At last, the analysis of the crack growth in skin and the residual strength for the surrounding intact structures can be performed. One chosen example is calculated by this method, and the analysis results are compared to the relative test results, which show that the agreement be- tween them is very good. The practicability and the feasibility of this method are proved.

关 键 词：蒙皮加筋壁板 损伤容限分析 纵向裂纹 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程]