某型飞机机身壁板鼓胀效应研究

Bulging Research of a Aircraft Fuselage Panel

本文介绍了国外机身壁板鼓胀效应研究的理论背景,在国内首次提出了一种新的基于有限元计算的机身壁板鼓胀效应研究方法。通过ANSYS建立有限元模型,模拟了某型飞机机身壁板框间裂纹,框下裂纹(框完好)和框下裂纹(框断开)3种情况下的鼓胀效应。通过对ANSYS软件进行二次开发,计算了这三种情况不同裂纹长度组合下的应力强度因子,并与平板理论解进行了对比分析。

After introducing the theories of bulging research of aircraft fuselage panel oversea, a new finite element method of bulging study is first raised in china in this paper. By building finite element model in ansys, this paper simulates the bulging phenomenon of fuselage panel with crack between frames, crack under intact frame and broken frame. Compared with the result of flat panel in theory, the stress intensity factors under different crack lengths of the three models are calculated after deeply exploiting the ANSYS in this paper.