基于正交试验法的机翼壁板桁条端部疲劳特性分析  

Fatigue Behavior Analysis of Stringer Run-Out for Wing Panel Based on Orthogonal Experiment Method

作　　者：张彦军 王斌团 雷晓欣 朱亮 车承牮 Zhang Yanjun;Wang Bintuan;Lei Xiaoxin;Zhu Liang;Che Chengjian(AVIC The First Aircraft Institute,Xi’an 710089,China)

机构地区：[1]航空工业第一飞机设计研究院,陕西西安710089

出　　处：《航空科学技术》2022年第6期34-40,共7页Aeronautical Science & Technology

基　　金：航空科学基金(2020Z009003002)。

摘　　要：采用正交仿真试验法分析了整体壁板长桁端部斜削结构的斜削角、斜削角底部圆角半径、腹板根部圆角半径三个关键几何参数对细节应力集中系数的影响程度,并确定了影响该处细节疲劳性能的主要几何因素。开展了三长桁整体壁板疲劳试验,得到了长桁端部斜削结构的破坏寿命。采用细节疲劳额定值(DFR)法和名义应力法分别计算了该种结构细节的疲劳寿命。计算结果与三长桁整体壁板疲劳试验结果相比,疲劳危险部位一致,计算结果与试验结果吻合较好,且DFR方法预测结果更接近试验结果。The orthogonal experiment method is adopted to study the influence of the key geometrical factors of stringer run-out, such as run-out angle, radius at run-out, and radius of web bottom on stress concentration factor. The major parameter influencing fatigue behavior at the run-out is determined. Fatigue test of integral panel with three stringers is carried out and fatigue life of the most severe position is obtained. Finally, fatigue life of stringer run-out is calculated using Detail Fatigue Rating(DFR) method and nominal stress method respectively. The calculated result shows a good agreement with result of fatigue test on integral panel with three stringers configuration at both fatigue position and fatigue life, and predicted result of the DFR method are closer to the test results.

关 键 词：长桁 正交试验 斜削端 应力集中 疲劳 

分 类 号：V215[航空宇航科学与技术—航空宇航推进理论与工程]