摘要
对高周疲劳环境下直升机疲劳载荷谱的编制方法进行了研究，采用某直升机尾桨叶飞行实测数据，对飞行实测到的１８３个飞行状态分别进行统计处理、假设检验及回归分析，确定了每个飞行状态的载荷分布类型及状态损伤，最后压缩归并成对尾桨叶造成损伤比较大的１８种飞行状态，编制了建立在统计基础上的尾桨叶实测疲劳载荷谱。文中还对载荷谱的高载截取和低载截除进行了分析讨论。提出了适合工程应用的高、低载截取（除）准则和编谱方法。
The method of establishing fatigue load spectrum of helicopter under high cycle fatigue has been studied in this paper. Using the flight survey data of the tail blade, the statistical treatment, the assumption test and the regression analysis have been made to every measured state of 183 flight conditions, by example of the helicopter tail blade, then the distribution types and the damage of different conditions are determined. Finally, we amalgamated 18 flight conditions that produce bigger and main damage to tail blade. The fatigue load spectrum of the tail blade has been made on the basis of statistics. The high load interception and the low load truncation are studied. Else in this paper, then the criteria of high load interception and low load truncation, method of establishing load spectrum in engineering application are proposed.
出处
《机械强度》
CAS
CSCD
北大核心
1999年第4期302-304,共3页
Journal of Mechanical Strength
关键词
疲劳载荷谱
直升机
飞行状态
高周疲劳载荷
fatigue load spectrum, dynamic components of helicopter, flight conditions, high cycle fatigue load
