全电无人机主推进直驱永磁电动机热负荷研究

张炳义; 王森; 冯桂宏

doi:10.13224/j.cnki.jasp.2015.05.028

全电无人机主推进直驱永磁电动机热负荷研究

doi: 10.13224/j.cnki.jasp.2015.05.028

1. 沈阳工业大学电气工程学院教育部特种电动机与高压电器重点实验室, 沈阳 110870;
2. 沈阳工程学院自动化学院, 沈阳 110136

基金项目:

国家自然科学基金(51077093)

详细信息

作者简介:
张炳义(1954-),男,辽宁抚顺人,教授、博士生导师,博士,研究方向为特种电动机及其控制,主要研究低速大转矩、低压大功率、低速大功率稀土永磁电动机及其控制技术.

中图分类号: V19
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- 被引次数: 0
出版历程
- 收稿日期: 2013-12-14
- 刊出日期: 2015-05-28

Research on heat load for main propulsion direct drive PMM of all-electric UAV

1. Special Motor and High Voltage Apparatus Key Laboratory of Education Ministry, School of Electrical Engineering, Shenyang University of Technology, Shenyang 110870, China;
2. School of Automatic Control Engineering, Shenyang Institute of Engineering, Shenyang 110136, China

摘要

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5500A²/(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).
- 热负荷 /
- 永磁电动机 /
- 直驱 /
- 主推进 /
- 全电无人机
Abstract: 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 characteristics 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 mechanics and heat transfer theory. The temperature rise of main propulsion motor was calculated in different heat loads and climbing angles. The changing rules of heat load and temperature 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 5500A²/(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 between 3000A²/(cm·mm²) and 5500A²/(cm·mm²).
- heat load /
- PMM /
- direct drive /
- main propulsion /
- all-electric UAV

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