某涵道式尾桨直升机垂尾载荷实测研究  

Experimental Study on Vertical Tail Load of a Ducted Tail Rotor Helicopter

作　　者：王泽峰[1] 谢强[1] Wang Zefeng;Xie Qiang(Chinese Flight Test Establishment,Xi′an 710089,Shaanxi,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《工程与试验》2018年第1期24-26,108,共4页Engineering and Test

摘　　要：结合某涵道式尾桨直升机载荷谱试飞,研究分析垂尾实测载荷。通过地面载荷校准试验,采用多元回归分析,建立了载荷方程,统计了直升机典型飞行动作下的垂尾载荷,系统地分析了该型直升机垂尾实测载荷的影响因素,研究了载荷随直升机飞行状态参数的变化规律,讨论了不同直升机科目下的垂尾载荷变化规律及影响因素,建立了直升机部件实测载荷数据分析方法,为直升机后续试飞提供技术支持。According to the flight test of load spectrum of a ducted tail rotor helicopter,the actual load of vertical tail is studied and analyzed.Through the ground load calibration test,multiple regression analysis is used to establish the load equation.The vertical tail load of helicopter under typical maneuver is counted,and the influencing factors of the vertical tail actual load of this kind of helicopter are analyzed systematically.Also the variations of the load with the flight parameters are analyzed.An scientific and systematical method is established for data processing of helicopter load,which provides technological support for the subsequent flight test of helicopter.

关 键 词：直升机 涵道式尾桨 垂尾 载荷校准 实测载荷 

分 类 号：V214.11[航空宇航科学与技术—航空宇航推进理论与工程]