摘要
首先，通过对某型直升机重心法向过载飞参数据的研究得到直升机在实际飞行中的重心过载谱；然后，发展了一种基于飞参数据的名义应力法并对某机群中的每架直升机进行了相对疲劳损伤的计算，计算结果比较符合实际情况；最后，对由相对损伤计算得到的寿命进行了可靠性分析，分析表明机体结构的寿命管理是个动态的过程，利用飞参数据实现从定时维修到状态维修的转变是可靠的也是可行的。
First, the loading spectrums of helicopter gravity center were obtained by analysis data of flight data recorder. Then the nominal stress method based on the data of flight data recorder was developed and the opposite fatigue damage of every helicopter in some air fleet was computed. The results accorded well with the fact. Lastly, the reliability of the life by computing opposite fatigue damage was analyzed. Analysis results showed that the management of aircraft structure life was a dynamic process and the maintenance idea of conversion from time maintenance to condition based maintain was reliable and feasible.
出处
《海军航空工程学院学报》
2011年第1期41-44,共4页
Journal of Naval Aeronautical and Astronautical University
关键词
定时维修
状态维修
相对疲劳损伤
飞参数据
time maintenance
condition based maintenance
maintenance relative fatigue damage
flight data recorder
