摘要
飞机结构使用过程中始终处在振动环境之中,振动引起的结构疲劳破坏是飞机结构破坏的主要模式之一,也是航空武器装备研制和使用中的共性问题。本文对国内、外几十年来形成的主要振动疲劳寿命预估方法进行了归纳整理,通过对飞机典型元件的理论分析、数值计算和试验研究,分析了各种振动疲劳寿命预估方法的适用性,为飞机典型结构振动疲劳寿命预计提供分析手段与设计参考。
The aircraft structure is always in a vibration environment. The fatigue failure caused by the vibration is one of the main modes of aircraft structural damage, and is also a common problem in the development and use of aviation weapon equipment. The main vibration fatigue life estimation method of domestic and international in recent decades are summarized In this paper. Through theo- retical analysis, numerical calculation and experimental verification of aircraft typical components, the applicability of the method is analyzed, provide analysis method and design reference for the typical structure vibration fatigue life of aircraft.
作者
周敏亮
陈忠明
邓吉宏
施荣明
ZHOU Min-liang CHEN Zhong-ming DENG Ji-hong SHI Rong-ming(Shenyang Aircraft Design & Research Institute, Shenyang 110035, China)
出处
《飞机设计》
2017年第3期25-30,共6页
Aircraft Design
关键词
功率谱密度
随机载荷
振动疲劳
寿命估算
S-N曲线
power spectral density
random loading
vibration fatigue
life estimation
S-N curve