飞机结构多裂纹造成的多部位损伤MSD剩余强度分析含4张CAD图+说明书

尾部气密框处的蒙皮拼接

目录
摘要III
Abstract IV
1绪论1
1.1研究背景1
1.2国内外MSD剩余强度研究现状2
1.3本文研究内容3
2广布疲劳损伤的敏感结构4
2.1引言4
2.2敏感结构的三维模型4
2.3计算模型7
2.4本章小结8
3 MSD剩余强度分析理论9
3.1引言9
3.2应力强度因子9
3.3相互影响因子13
3.4剩余强度理论14
3.5本章小结20
4有限元建模21
4.1引言21
4.2 ABAQUS验证21
4.3建模过程23
4.4本章小结29
5 MSD剩余强度分析30
5.1引言30
5.2建模数据30
5.3应力强度因子分析32
5.4剩余强度签到股分析37
5.5本章小结46
6结束语47
6.1本文的主要贡献47
6.2需要进一步研究的问题47
参考文献48
致谢50
MSD剩余强度分析
摘要
随着老龄飞机机队老化的发展，其可持续适航问题已成为民用航空业和公众关注的焦点。对于老龄飞机来说，广布疲劳损伤是一种普遍而又复杂的问题。它是许多老龄飞机中存在的一种非常典型的损伤形式。广布疲劳损伤会导致飞机结构的破损。因此，研究广布疲劳损伤结构的剩余强度问题拥有较大的前景和实用意义。本文在前人的研究发现的基础上，对本课题进行试验，各个环节都有所依靠或予以验证，从而表明本文数据的正确性，可靠性。主要针对多裂纹造成的多部位损伤（MSD）剩余强度的问题，进行了基于三维软件和ABAQUS有限元分析软件，origin数据处理软件，对老龄化飞机结构建立有限元模型；在了解材料参数，断裂参数以及边界条件的基础上，讨论孔边裂纹的相对位置和长度对应力强度因子的影响规律，并进行净截面应力强度和剩余强度分析得出一系列对工程应用具有实用价值的结论。
关键词：广布疲劳损伤，多部位损伤，应力强度因子，净截面，剩余强度，有限元分析
MSD residual strength analysis
ABSTRACT
With the passage of time, the expansion of fleets of older aircraft and their continued airworthiness have become the focus of attention of the civil aviation community and the general public. For aging aircraft, widespread fatigue damage is a common and complex problem. It is a very typical form of damage that exists in many older aircraft. Widespread fatigue damage can compromise the integrity of the aircraft structure. Therefore, it is of great engineering significance and practical value to study the residual strength of fatigue damage structures. This article starts from the research basis of the predecessors and tests this topic. Every link has been relied on or verified to show the correctness and reliability of the data. Mainly for the problem of multi-slice damage (MSD) residual strength caused by multiple cracks, based on three-dimensional software and ABAQUS finite element analysis software, origin data processing software, established a finite element model for the aging of the aircraft structure; in understanding the material parameters, fracture Based on the parameters and boundary conditions, the influence of the relative position and length of the hole cracks on the stress intensity factor is discussed, and the analysis of the net section stress intensity and residual strength yields a series of practically useful conclusions for engineering applications.

Key words: extensive fatigue damage， multi-site damage ，stress intensity factor， net cross section， residual strength， finite element analysis

机翼上表面处机身附属装置

字数统计

说明书前三页

设计所包含文件

腹板或蒙皮厚度突变—气密或非气密结构

机身舷窗周围结构