平飞状态下旋翼桨叶挥舞弯曲载荷试飞研究  

Flight Test Investigation of the Blade Flapping Load in Horizontal Flight

作　　者：郑甲宏[1] 寇富军[1] 沈雳[1] 

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《科学技术与工程》2012年第31期8474-8478,共5页Science Technology and Engineering

摘　　要：以桨叶应变测量法为基础,通过地面标定试验及飞行试验,获得了桨叶沿着展向6个测量剖面挥舞弯曲载荷。研究了在平飞状态下桨叶挥舞载荷随飞行速度、测点位置及风向的变化规律,为桨叶结构改型及强度设计提供重要依据。The flapping load of blade is investigated through the use of the strain measurement method and the flight test. The flapping load of blade in six measure positions are obtained. Then the speed, measuring positions and wind direction factors, its variety tendency as well as the relation related to the helicopter status of horizontal flight for the flapping load of blade are analyzed. The results provide an important proof for structural optimization and strength design of blade.

关 键 词：直升机 桨叶 飞行试验 挥舞载荷 

分 类 号：V224[航空宇航科学与技术—飞行器设计]