基于整体壁板的损伤容限分析和试验  

Damage Tolerance Analysis and Test Based on Integral Panel

作　　者：姜昊 JIANG Hao(AVIC General Huanan Aircraft Industry Co.,Ltd.,Zhuhai 519040,Guangdong,China)

机构地区：[1]中航通飞华南飞机工业有限责任公司,广东珠海519040

出　　处：《工程与试验》2024年第4期28-31,共4页Engineering and Test

摘　　要：现代民机结构设计的主流思想是按照损伤容限进行设计。整体壁板具有良好的抗疲劳性能,但是其损伤容限性能却弱于组合结构。NASGRO虽然是NASA进行损伤容限分析指定软件,却并没有针对整体壁板适用的分析模型。当裂纹靠近筋条时,应力强度因子的变化是分析的难点,也是影响损伤容限分析精确度的重要因素。为研究某型号整体壁板的损伤容限特性,进行了试验设计,应用有限元软件Abaqus建立了含裂纹整体壁板的细节有限元模型,并对裂纹扩展进行了假设。用围线积分方法计算不同裂纹长度下的应力强度因子,并结合NASGRO扩展模型,对裂纹扩展和剩余强度进行了分析。与相应的整体壁板试验对比表明,分析与试验相吻合,对整体壁板的抗断裂设计和损伤容限分析提供了参考。The mainstream idea of modern civil aircraft structure is to design according to the damage tolerance.The integral panel has good fatigue resistance,but its damage tolerance performance is weaker than that of the composite structure.As a designated software of NASA for damage tolerance analysis,NASGRO does not have a suitable analysis model for the integral panel,and when the crack is close to the rib,the change of stress intensity factor is a difficult point in the analysis,and it is also an important factor affecting the accuracy of damage tolerance analysis.In order to study the damage tolerance characteristics of a certain type of integral panel,the experimental design is carried out.The finite element software Abaqus is used to establish the detailed finite element model of the integral panel with cracks,and the crack propagation is assumed.The stress intensity factor under different crack lengths is calculated by the contour integration method,and the crack propagation and residual strength are analyzed in combination with the NASGRO expansion model.The comparison with the corresponding integral panel test shows that the analysis is consistent with the test,which provides a certain reference for the fracture resistance design and damage tolerance analysis of the integral panel.

关 键 词：整体壁板 损伤容限 应力强度因子 剩余强度 有限元分析 

分 类 号：V214.3[航空宇航科学与技术—航空宇航推进理论与工程]