摘要
本文结合工程实例对直升机关键件疲劳设计和试验验证中的几个问题进行了探讨和分析。提出了几个观点:对承受高周疲劳载荷为主的直升机关键件,宜采用疲劳极限和疲劳寿命共同作为疲劳设计目标参数;疲劳寿命对疲劳极限、载荷谱相当敏感的T-、A-等破坏模式的疲劳设计应采用无限寿命设计方法;多疲劳源、多破坏模式复杂结构疲劳设计时须给予额外设计裕度;多疲劳源、多破坏模式复杂结构疲劳试验须充分利用试件同时考核多个危险部位,获得各危险部位准确的疲劳性能。
Several issues on fatigue design and test substantiation of helicopter critical part are discussed using engineering instance.Some opinions are presented hereinafter.Fatigue limit and fatigue life are suitable together for target parameters of fatigue design of helicopter critical part endured mainly high cycle fatigue load.Infinite life method is adapted to fatigue design on failure mode T-and A-whose fatigue life is sensitive to fatigue limit and load.Additional design margin is required to large part wit...
出处
《直升机技术》
2009年第4期6-9,共4页
Helicopter Technique
关键词
疲劳设计
直升机
关键件
helicopter
critical part
fatigue design
