摘要
按照新的适航规章确定直升机尾减速器连接寿命,并给出结构检查周期.利用有限元分析结合Miner线性累积损伤理论对结构连接按照设计目标寿命进行详细尺寸定义;利用结构疲劳试验结合Miner线性累积损伤理论给出结构连接寿命;载荷谱分别选用有限元计算疲劳载荷谱和实测疲劳载荷谱,同时按照相应的准则将材料的平均S-N曲线转换为计算安全S-N曲线和试验安全S-N曲线.
The safe life of a helicopter tail gearbox link is determined in terms of the new airworthiness regulation and the inspection interval is given. According to the target safe life for design, the detailed structure link size is confirmed by finite element analysis in combination with Miner linear cumulative damage theory ; the safe life of the structure link is confirmed by structure fatigue test in combination with Miner linear cumulative damage theory; the load spectrum is selected respectively as finite element calculation load spectrum and measured fatigue load spectrum, and the average S-N curve of material is converted to calculation safe S-N curve and testing safe S-N curve on basis of the corresponding criterion.
出处
《计算机辅助工程》
2016年第3期24-28,33,共6页
Computer Aided Engineering
