摘要
利用商用软件ABAQUS建立某型飞机机翼肋段间有限元模型。采用面面接触模拟裂纹附近结构之间的连接,Tie绑定模拟非考核区的连接,获得下壁板裂纹附近的应力分布,并与装配应力叠加,采用名义应力法和线性累积损伤理论估算出该结构的疲劳寿命,将其与全机疲劳试验结果对比。结果显示,某型飞机机翼下壁板的疲劳寿命估算结果与试验值相差5.5%,其疲劳裂纹由谱载和装配应力叠加导致,且装配应力越大,结构寿命越短。
The finite element model of a certain aircraft wing rib section was established by using commercial software ABAQUS.The stress distribution near the lower-panel cracks was obtained by adopting a surface-to-surface contact to simulate the connections between the structures near the cracks and binding to Tie to simulate the connections in the non-test area.After the stress distribution has been superimposed with the assembly stress,the fatigue life of the structure was estimated using the nominal stress method and the linear cumulative damage theory and compared with the full-scale aircraft fatigue test results.The results show that for the certain type of aircraft,there is a 5.55%difference between the lower panel's estimated fatigue life and the test value and the fatigue cracks are caused by the superposition of spectrum loading and assembly stress,and the greater the assembly stress,the shorter the structural life.
作者
熊健
邓强
黄晓霞
张里伟
Xiong Jian;Deng Qiang;Huang Xiaoxia;Zhang Liwei(AVIC Hongdu,Nanchang,Jiangxi,330024)
出处
《教练机》
2025年第2期22-26,共5页
Trainer
作者简介
熊健,男,1998年12月出生,工程师。
