基于实测载荷的直升机变距拉杆损伤计算方法研究  

Research on Damage Calculating Method of Helicopter Pitch Link Based on Measured Load

作　　者：王泽峰[1] Wang Zefeng(Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院

出　　处：《航空科学技术》2019年第5期36-41,共6页Aeronautical Science & Technology

摘　　要：变距拉杆作为直升机操纵链系和传力路径上极其重要的关键组件,在飞行过程中受载严重,疲劳问题突出,从试飞安全的角度考虑,有必要对其飞行过程中的结构损伤情况进行监控。本文结合飞行实测得到的变距拉杆载荷,基于结构有限元计算结果,采用名义应力法对直升机不同飞行状态下的变距拉杆疲劳寿命和损伤情况进行计算,得到了较为准确的变距拉杆疲劳损伤计算结果,建立了一种直升机变距拉杆疲劳损伤计算方法,为试飞过程中该部件结构损伤监控提供了方案,同时对于直升机飞行过程中其他动部件的结构完整性监测也有借鉴意义。As a key component of helicopter control chain and force path,pitch link bears severe alternating load during flight.Considering flight safety,it is necessary to calculate and monitor structural damage during flight.In this paper,the fatigue life and fatigue damage of pitch link under different flight conditions are calculated by nominal stress method,based on the results of structural finite element analysis and miner fatigue damage criterion.The more accurate fatigue damage calculation results of pitch links are obtained,and a fatigue damage meter for helicopter pitch link is established.The calculation method provides a method for the structural integrity monitoring of the component during flight test.

关 键 词：实测载荷 直升机 飞行 变距拉杆 疲劳损伤 

分 类 号：V275[航空宇航科学与技术—飞行器设计]