摘要
由于直升机以动部件为代表的特殊结构形式以及复杂的振动载荷环境,飞行实测载荷是疲劳设计和评定过程中的关键数据。本文结合某直升机实测载荷数据,介绍了实测载荷有效性分析的工作内容和方法,其中相关性分析和规律性分析等方法可进一步用于获取各结构的状态、重量、重心、高度疲劳载荷的分布规律和相互关系,使其应用到新型号设计中。为我国直升机疲劳设计载荷的获得提供一些可借鉴的思路。
Flight test load is the key data for fatigue design and evaluation because of the especial structure type such as rotating components and complex vibration load circumstance on helicopter.The content and method of the validity analysis on flight test load are introduced,example on some helicopter flight test load is shown.Relativity and orderliness analysis method can be used to get the distributing and correlation among the fatigue loads of different cases,weight,centre of gravity and altitude.This offers some references for getting the fatigue load during new helicopter design period.
出处
《直升机技术》
2007年第4期19-23,共5页
Helicopter Technique
