空空导弹吊挂疲劳寿命分析

针对空空导弹吊挂在挂飞过程中承受多种复杂多变的载荷(如挂飞振动载荷、机动抖振载荷、起飞着陆冲击载荷等)产生的疲劳破坏问题,研究利用仿真计算其疲劳寿命。在总结国内外最新疲劳理论研究的基础上,提出了基于有限元的时域和频域相结合的疲劳分析方法,在空空导弹吊挂的疲劳研究上形成了一套较为完善的分析流程。以某型空空导弹吊挂为研究对象,对其结构及工况特点进行了探讨和分析,借助Msc.Fatigue软件平台建立了吊挂的疲劳损伤模型,结合S-N曲线,计算出其疲劳损伤及其疲劳寿命,并总结出吊挂疲劳寿命的主要影响因素,对具体的型号研制工作有一定的指导意义和工程应用价值。

Fatigue life analysis of airborne missile hanging

The airborne missile hanging is subject to various complex load （such as durability vibration load , dithering vibration load, impact load of take off and landfall, etc） in flight, which led to the problem of its fatigue failure, aiming at this problem ,we figure up its fatigue life by using means of simulation. Time-domain and frequency-domain method in terms of finite element analysis is presented to investigate the fatigue life of the missile hanging after reviewing the new fatigue theory at home and abroad. A relatively complete analysis process is formed on fatigue research of the airborne missile hanging. In this paper, on the basis of a airborne missile hanging, its structure and working conditions are analyzed, its S-N curve is fitted out, and the fatigue damage model based on the software of Msc. Fatigue is constructed, from which, the fatigue damage and the fatigue life are predicted. In addition, the main influence factors and influence law of the fatigue life are indicated. The research of this paper has certain actual application value and definite direction significance in later development of projects.