摘要
以无人机主推进电动机为研究对象,基于流固耦合传热理论,结合无人机主推进电动机通风特性及开启式结构特点,建立电动机在强冷却条件下流固耦合物理模型与数学模型,给出温度场计算方法,得出主推进电动机额定状态下温度分布及轴向剖面温度分布及主要部件的温升变化规律。对电动机进行风洞与飞行试验,并将试验结果与理论分析进行对比,验证理论分析的正确性。研究结果可为无人机主推进电动机温度场研究及优化设计提供理论依据。
According to the fluid-solid heat transfer theory,taking the main propulsion motor（MPM） of Unmanned Aerial Vehicle （UAV） as the object of study,the fluid-solid coupled physical and mathematical models were established under the strong cooling condition combining the ventilation and structure characteristics of MPM.The method of temperature field calculation is proposed,and temperature distribution of MPM at rated condition,temperature distribution of MPM at axis section view and temperature rise change rule for main parts of PMM were obtained under different flight conditions.The wind tunnel and flight tests of MPM were performed,and the theoretical analysis was compared with the test,which proved the correctness of analyzed method.The works provide a theoretical basis for the temperature field research and optimal design for MPM of UAV.
出处
《电机与控制学报》
EI
CSCD
北大核心
2014年第6期116-120,共5页
Electric Machines and Control
基金
国家自然科学基金(51177106)
关键词
无人机
主推进电动机
直驱
流固耦合
温度场
UAV
main propulsion motors
direct drive
fluid-solid coupled
temperature field
