摘要
介绍了目前现行的抗疲劳设计方法,认为名义应力疲劳设计法适用于航空电子设备结构设计。通过实际设备有限元仿真分析,得到其加速度响应,根据箱体最大加速度响应处的固有频率,确定最大响应振动次数,以此判断选用何种名义应力疲劳设计方法。计算出设备耐久振动的最大应力,用名义应力疲劳判据校核其疲劳强度。
We present the anti-fatigue design method and believe that the nominal stress fatigue design method suits structural designs in avionics. The finite element analysis of avionics equipment produces its largest acceleration re- sponse, whose natural frequency is calculated with the finite element method. According to the natural frequency, the number of the largest response vibration cycles is determined to select the type of nominal stress fatigue design method. The largest endurance vibration stress is calculated. The nominal stress fatigue is used to determine the fa- tigue life of avionics equipment.
出处
《机械科学与技术》
CSCD
北大核心
2014年第4期621-624,共4页
Mechanical Science and Technology for Aerospace Engineering
关键词
抗疲劳设计
有限元
航空电子设备
acceleration
anti-fatigue design
avionics
calculations
dynamic response
fatigue of materials
finite element analysis
finite element method
natural frequencies
nominal stress fatigue
power speetial density
stress concentration
structural design
vibrations （mechanical）
