某型直升机新构型尾桨抗侧风能力验证试飞  

Verification Flight Test of Cross-Wind Resistance of a Helicopter with New Configuration Tail Rotor

作　　者：顾文标[1] 陈圆 陈敏[1] 游洪华[1] GU Wenbiao;CHEN Yuan;CHEN Min;YOU Honghua(China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所,江西景德镇333001

出　　处：《直升机技术》2020年第1期38-41,31,共5页Helicopter Technique

摘　　要：为满足直升机飞行品质规范的要求,更好地适应高原地区使用环境,某型直升机尾桨采用新构型设计,通过尾桨距范围的拓展,获得尾桨最大抗侧风能力的提升。新构型尾桨经过装机适应性检查、地面运转试验、平原地区试飞和高原地区尾桨距放距试飞,完成了最大抗侧风能力验证,为新构型尾桨的后续设计完善提供依据。A helicopter tail rotor has been redesigned,by extending the pitch of the tail propeller,it was expected that the maximum wind resistance of the tail rotor could be improved to make it safer in the chaotic environment of frequent shear and so on in the plateau.Ground operation test,test flight in plain area and tail propeller pitch release test flight in plateau area of tail rotor with new configuration after installation adaptability check had been finished,and verification of maximum cross wind resistance to 18m/s,it provided a basis for the follow-up design of new configuration tail rotor system.

关 键 词：尾桨 新构型 抗侧风能力 飞行验证 

分 类 号：V217.3[航空宇航科学与技术—航空宇航推进理论与工程]