Analysis of Heat Dissipation Performance of Main Reducer Cabin for an Unmanned Helicopter
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摘要: 主减速器是无人直升机传动系统的重要组成部分,为防止高温影响其工作性能,针对某无人直升机主减速器,建立了主减速器舱三维模型;应用CFD(计算流体动力学)对其前飞状态下的主减速器舱流场及温度场进行了数值仿真,研究其流场和温度场分布,得到了提升主减舱散热效果的方法。结果表明:增大侧排气口能有效抑制侧排气口附近的涡流;调节风扇与主减速器的距离,将圆形导风罩改为方形导风罩加导风圈的形式及调节风扇与散热器之间的距离等方法均可以降低散热器散热的不均匀性,提高散热性能。Abstract: The main reducer is an important part for the unmanned helicopter transmission system. In order to avoid the high temperature to affect its working performance, a three-dimensional model for the main reducer cabin is established. The flow field and temperature field in the main reducer cabin in the front flight state is simulated via CFD (Computational fluid dynamics), the method to improve the heat dissipation performance in the main reducer cabin is obtained. The results show that to increase the size of the side vent can effectively suppress the eddy current near the side vent, and to adjust the distance of the fan from the main reducer, to change the circular air deflector to the square air deflector with the wind guide ring, to adjuste the distance between the fan and the radiator can reduce the non uniformity of the heat dissipation of the radiator and improve the heat dissipation performance.
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表 1 边界条件名称及类型
边界条件 边界名称 边界类型 上进气口 Inlet1 Velocity-inlet 前进气口 Inlet2 Velocity-inlet 侧排气口 Outlet1 Pressure_outlet 排气口 Outlet2 Pressure_outlet 上机匣 shangjixia wall 中机匣 zhongjixia wall 下机匣 xiajixia wall 旋翼轴 xuanyizhou wall 风扇 fengshan fan 散热器 sanreqi radiator 舱壁 cangbi wall 导风罩 daofengzhao wall 上进气道 qidao_inlet1 wall 前进气道 qidao_inlet2 wall 侧排气道 qidao_outlet1 wall 排气道 qidao_outlet2 wall -
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