CAJ | 학술논문

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。
위요직승궤공솔분배，대기시비측정적가행성진행료분석。수선，이용시비측정발동궤뉴구화전속학정주감속기수입공솔；기차，이용시비측정산열기진、출구활유온도화활유류량학정산열기손모공솔；재차，이용시비측정궤갑안장지좌온도、각체표면온도화감속기공작배경온도학정주、중、미감속기각체산열손실공솔；최후，이용선익축、미장축뉴구화전속학정선익、미장수용공솔。최종득도주，중，미감속기전동효솔、선익공솔전체계수、미전수출공솔화주감부건소모공솔。
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.