中文摘要：

以全电无人飞机主推进直驱永磁电动机为研究对象，分析处于不同工况下主推进电动机热负荷特性．针对主推进电动机开启式结构特点，根据流体力学及传热学理论，建立强风冷却条件下流固耦合物理模型与数学模型，通过仿真计算不同热负荷、不同爬升角度时主推进电动机的温升，分析主推进电动机热负荷及温升随飞行工况的变化规律．对主推进电动机进行风洞与飞行试验．结果表明：热负荷为5500A。／（cm·mm2）时电动机最高温升为124K，与仿真值误差在2％以内，验证了理论分析正确性．无人机主推进电动机热负荷选取范围为3000～5500A2／（cm·mm2）．

英文摘要：

Taking the main propulsion direct drive permanent magnet motor （PMM） of all-electric unmanned aerial vehicle （UAV） as the object of study, the heat load characteris- tics of main propulsion motor were analyzed in different working conditions. The fluid-solid coupled physical and mathematical models were established under strong cooling condition for the structure characteristics of open of main propulsion motor according to the fluid me chanics and heat transfer theory. The temperature rise of main propulsion motor was calcu- lated in different heat loads and climbing angles. The changing rules of heat load and temper- ature rise of main propulsion motor were deeply analyzed under different working conditions. The wind tunnel and flight tests of main propulsion motor were performed. Result shows that, the highest temperature rise of motor is 124K when the heat load is 5 500 A2/（cm · mm2）. Compared with the simulation value, the accuracy is within 2%, verifying the correctness of theoretical analysis. The heat load range of UAV main propulsion motor is between3000Az/（cm· mm2） and5500A2/（cm. mm2）.