直升机功率分配试飞测定可行性分析  

Feasibility Analysis of Flight Test Measurement for Helicopter Power Distribution

作　　者：李永寿[1] 

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《航空科学技术》2015年第4期39-44,共6页Aeronautical Science & Technology

摘　　要：围绕直升机功率分配,对其试飞测定的可行性进行了分析。首先,利用试飞测定发动机扭矩和转速确定主减速器输入功率;其次,利用试飞测定散热器进、出口滑油温度和滑油流量确定散热器损耗功率;再次,利用试飞测定机匣安装支座温度、壳体表面温度和减速器工作环境温度确定主、中、尾减速器壳体散热损失功率;最后,利用旋翼轴、尾桨轴扭矩和转速确定旋翼、尾桨需用功率。最终得到主,中,尾减速器传动效率、旋翼功率传递系数、尾传输出功率和主减附件消耗功率。This paper got on feasibility analysis to the helicopter power distribution measurement in flight test. Firstly, it determined input power of the maln decreasing gear unit, used of engine torque and speed measured in flight test. Secondly, it determined power loss of the radiator by inlet and outlet oil temperature and oil flow of radiator from flight test. Next, it determined loss of power of the primary, middle and tall reducer housing heat, adopted receiver mounting bracket temperature, surface temperature and gear housing operating ambient temperature in lfight experiment. Final y, it determined requirement power of the rotor and tall rotor using the rotor shaft, tall rotor shaft torque and speed. The ifnal result was to get transmission efifciency of the primary, middle and tall reducer, transfer coefifcient of the rotor power, the power of tall transmission and the consumed power of the maln reducing attachment.

关 键 词：直升机 试飞 功率分配 传动系统 可行性 

分 类 号：V217.39[航空宇航科学与技术—航空宇航推进理论与工程]