摘要
直升机金属动部件是单路传力结构,承受高周疲劳载荷,一般认为不适合采用损伤容限设计,但对多个螺栓连接的大型接头,有较好的损伤容限特性。文章根据线弹性断裂力学Paris理论,提出了一套适合直升机动部件的损伤容限分析方法,通过对某型机尾桨叶接头进行损伤容限分析,得出了具有高可靠度的较长的裂纹扩展寿命。
Because of suffering high cycle fatigue loads and single load path, helicopter rotary com-ponents are not generally capability for damage toleranee design. But some muhi-boh connecting large fittings have good damage tolerance characteristics. This paper offered a sort of damage toler-ance analysis method for helicopter rotary components, and applied to tail rotor blade fittings, a long crack propagation life with high reliability was acquired.
出处
《直升机技术》
2013年第2期28-32,共5页
Helicopter Technique
