直升机尾桨叶疲劳试验技术的研究  

Study on Fatigue Test Technology of Helicopter Tail Rotor Blade

作　　者：王久龙 杨库 曹金华 杨雄飞 李黎明 于国庆 WANG Jiu-long;YANG Ku;CAO Jin-hua;YANG Xiong-fei;LI Li-ming;YU Guo-qing(AVIC Harbin Aircraft Industry Group Co.,Ltd.,Harbin 150066,China;Bureau of Military Representation of the Aviation Corps of the Army Equipment Department in the Harbin Regional Aviation Military Representation Office,Harbin 150066,China)

机构地区：[1]航空工业哈尔滨飞机工业集团有限责任公司,黑龙江哈尔滨150066 [2]陆军装备部航空兵军事代表局驻哈尔滨地区航空军事代表室,黑龙江哈尔滨150066

出　　处：《测控技术》2022年第3期49-54,共6页Measurement & Control Technology

摘　　要：基于直升机尾桨叶疲劳试验技术研究的现状,对尾桨叶疲劳试验实现技术进行了重点阐述。根据尾桨叶疲劳试验的加载及测量要求,结合尾桨叶构型特性,设计制造了可同时对尾桨叶施加离心力、挥舞力、摆振力、扭力及法兰盘压载荷的尾桨叶疲劳试验台,并说明了尾桨叶疲劳试验台的工作原理。通过应用对尾桨叶粘贴应变片的方法测得了3件尾桨叶疲劳试验中尾桨叶各监控剖面的载荷情况,得到了规律的、稳定的可靠试验数据,证明了尾桨叶疲劳试验技术的合理性。同时,主动控制桨叶位移进行加载实现桨叶多向协调载荷要求的试验工装设计方法,对其他复合材料结构件的疲劳试验研究设计具有借鉴意义。Based on the research on fatigue test technology of helicopters tail rotor blade,the realization of this test technology is discussed in detail.According to the loading and measurement requirements of tail rotor blade fatigue test,combined with the structural characteristics of tail rotor blade,a tail rotor blade fatigue test-bed which can impose centrifugal load,swing load,shimmy load,torque and flange loads to tail rotor blade at the same time is designed and manufactured,and the working principle of this test-bed is explained.The bending moment of tail blade each profile in the fatigue test of three tail blades is monitored by the way of pasted strain gauges on tail blades,the regular and stable and reliable test data are obtained,which proves the rationality of the realization technology of tail rotor blade fatigue test.The test tooling design method of actively controlling the blade displacement to load and realize the requirements of multi-direction coordinated load of the blade has reference significance for design of other composite product fatigue test.

关 键 词：直升机 尾桨叶 疲劳试验 工装设计 测量控制 

分 类 号：TP23[自动化与计算机技术—检测技术与自动化装置]