首页 | 本学科首页   官方微博 | 高级检索  
     检索      

自动变桨距螺旋桨电推进系统能效优化方法
引用本文:魏宝泽,杨勇,张新榃,张驰.自动变桨距螺旋桨电推进系统能效优化方法[J].航空动力学报,2023,38(3):717-727.
作者姓名:魏宝泽  杨勇  张新榃  张驰
作者单位:中国商用飞机有限责任公司 北京民用飞机技术研究中心,北京 102211
摘    要:为了提升自动变桨距螺旋桨电推进系统的整体效率,引入最优功率控制规律:自动变桨距螺旋桨电推进系统可根据飞行工况和推力需求,同时调节桨距角和螺旋桨转速两个变量,最终获得一组桨距角和螺旋桨转速的组合,使得推进系统在满足推力需求的情况下实现最小的功率消耗,最终达成飞行任务剖面内最小能耗控制的目标。为了验证方法的有效性,针对同一电推进系统,分别采用最优功率控制规律和恒速控制规律完成相同的飞行任务剖面,获得了两种控制规律下的螺旋桨推进效率、电动机效率、电推进系统总效率和电推进系统能耗数据。结果证明:相较于恒速控制规律,最优功率控制规律能够有效的提升电推进系统效率并降低能耗,完成相同飞行任务剖面的能耗降低6.3%左右。

关 键 词:电推进系统  变桨距螺旋桨  最优功率控制规律  恒速控制规律  能效优化
收稿时间:2022-11-17

Energy efficiency optimization method of automatic variable pitch propeller electric propulsion system
Institution:Beijing Aircraft Technology Research Institute, Commercial Aircraft Corporation of China,Limited,Beijing 102211,China
Abstract:To improve the overall efficiency of automatic variable pitch propeller electric propulsion system, the optimal power control law was introduced: automatic variable pitch propeller electric propulsion system can adjust both the pitch angle and rotation speed simultaneously according to the flight conditions and thrust demand, and finally obtain a pitch angle/rotation speed combination, so that the propulsion system can meet the thrust demand and achieve the minimum power consumption, ultimately achieving the goal of minimum energy consumption control in the whole flight profile. To verify the effectiveness of the method, the same electric propulsion system was used to complete the same mission profile with the optimal power control law and the constant speed control law, then the propeller propulsion efficiency, motor efficiency, total electric propulsion system efficiency and electric propulsion system energy consumption data under the two control laws were obtained. The results proved that the optimal power control law can effectively improve the electric propulsion system efficiency and reduce the energy consumption compared with the constant speed control law, and the energy consumption of the same mission profile was reduced by about 6.3%. 
Keywords:
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号