Energy efficiency optimization method of automatic variable pitch propeller electric propulsion system
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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。
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%.
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图 1 电推进系统基本架构示意图
Figure 1. Schematic diagram of basic electrical propulsion system architecture
图 3 供应商提供的UQM PowerPhase 145电动机效率特性图
Figure 3. Manufacturer's motor efficiency map of UQM PowerPhase 145
图 4 基于UQM PowerPhase 145的参数化电动机模型效率特性图（单位：%）
Figure 4. Efficiency map of parameter motor model based on UQM PowerPhase 145 （unit：%）
图 5 供应商数据与参数化电动机模型计算结果的对比
Figure 5. Comparison of manufacturer’s data and calculation results of parameter motor model
图 10 典型变桨距螺旋桨定
$C_{{T}}^0$ 螺旋桨性能图（给定飞行工况和推力需求）Figure 10. Performance map of typical variable pitch propeller depicting constant
$C_{{T}}^0$ （given flight condition and thrust requirement）
图 12 电推进系统及部件效率特性曲线（最优功率控制规律）
Figure 12. Characteristic curves of electric propulsion system and components efficiency （optimal power control）
图 13 电推进系统及部件效率特性曲线（恒速控制规律）
Figure 13. Characteristic curves of electric propulsion system and components efficiency （constant speed control）
图 14 两种控制规律下螺旋桨效率特性对比
Figure 14. Comparison of propeller efficiency characteristic under two control laws
图 15 两种控制规律下电动机效率特性对比
Figure 15. Comparison of motor efficiency characteristic under two control laws
图 16 两种控制规律下电推进系统总效率特性对比
Figure 16. Comparison of electric propulsion system efficiency characteristic under two control laws
图 17 两种控制规律下电推进系统消耗功率对比
Figure 17. Comparison of electric propulsion system power under two control laws
表 1 电推进飞机的关键参数
Table 1. Key parameters of electrically aircraft
参数 数值 机翼面积/m2 26.0 翼载/（kg/m2） 151.4 质量/kg 3937.0 展弦比 9.35 诱导阻力系数 0.85 寄生阻力系数 0.035 最大升阻比 13.4 最大升力系数 4.52 
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