摘要
首先以主桨叶为研究对象,理论分析了直升机俯冲拉起状态下主桨叶实测载荷的影响因素;其次,以某型直升机旋翼载荷试飞为例,选取其主桨叶上的关键剖面,采用电阻应变计法进行飞行载荷测量,得到了不同重量重心、不同高度、不同法向过载等情况下的实测载荷;分析了实测的主桨叶挥舞弯矩、摆阵弯矩载荷值在直升机整个俯冲拉起过程中的变化规律,分析了实测载荷值随法向过载等的变化规律。为该型直升机试飞提供技术支持的同时,也为后续其他直升机法向过载包线拓展验证试飞提供重要支持。
The paper studied the subject of main rotor. First of all, theoretically analyzed the influencing factors of measured load of main blade while helicopter diving and pull-up. Secondly, based on some helicopter rotor load flight tests, selected the key sections of the main blade, using a resistance strain gage method to measure the flight load, got the result under different weight, center of gravity, height and normal acceleration situation. Analyzed the regularity of measured main rotor flapping and legging moment between the whole diving and pulling-up, analyzed moment value varies with normal acceleration. It not only provids technical support for the test flight of the helicopter, but also provids important technology support for other helicopters' flight test for overioad envelope.
作者
王泽峰
李清龙
WANG Zefeng LI Qinglong(Chinese Flight Test Establishment, Xi'an 710089, China)
出处
《航空科学技术》
2017年第10期13-17,共5页
Aeronautical Science & Technology
关键词
直升机
俯冲拉起
主桨叶
飞行
实测载荷
helicopter
dive and pull-up
main rotor
flight
measured load