某型飞机加强框连接区疲劳裂纹分析

Analysis on Fatigue Crack at the Connecting Area of Reinforced Frame on a Certain Type of Aircraft

机身加强框作为多承力结构,属于飞机传力关键构件,同时也是疲劳薄弱构件,对其进行疲劳分析具有重要工程意义。某型飞机某框属于承受进气道较大气动载荷和机身-机翼接头集中载荷的加强框。本文分析了两类载荷对该框连接构件疲劳性能的影响比重,通过改进载荷的传力路线提升了连接构件的疲劳寿命。

As a multi-load bearing structure,the reinforced frame of fuselage is not only a key load-transfer component but also a fatigue weak component.Fatigue analysis of the reinforced frame on fuselage plays an important role in the engineering field.A certain frame on a certain type of aircraft is designed as a reinforced frame which bears a considerable aerodynamic load from the air intake and a concentrated load on the fuselage-wing joint.This paper,by analyzing the proportion of impacts of two types of loads on the fatigue performance of the connecting component of this frame,extends the fatigue life of the connecting component with the modification of force transferring route.