螺旋桨多设计点气动优化方法和变桨距角策略

doi:10.7527/S1000-6893.2023.28831

Abstract

Abstract:

The high-altitude solar powered Unmanned Aerial Vehicle（UAV） has a slow flight speed， low climb rate and long climb time in the take-off and climb stage， the propeller needs to provide large pull force to achieve fast climb. However， the low-altitude air density is high， and the propeller is in the state of low speed and high torque. At the altitude of 20 km， the air density is only 1/14 of the ground， requiring the propeller to be in a state of high speed and high efficiency. Due to the power limitation of the power system， fixed-pitch propellers cannot match these two states， so variable pitch technology is needed to realize the configuration of small pitch， low speed and large tension at low altitude， and large pitch， high speed and high efficiency at high altitude. This paper presents a method of aerodynamic profile optimization for propeller with multiple design points and a strategy of variable pitch angle under multiple operating conditions. The aerodynamic profile optimization model of propeller with multiple design points was established based on standard strip analysis， and the profile parameters of propeller were optimized， such as chord length and torsion angle distribution. A fast aerodynamic calculation model considering pitch angle variation is added to the model to realize the strategy of variable pitch angle under multiple working conditions. By comparing the aerodynamic performance of the propeller under fixed pitch and variable pitch， the results show that the efficiency of the propeller designed based on the aerodynamic shape optimization model of the propeller at multiple design points at high altitude is more than 80%， which is conducive to the long-term flight of the solar powered UAV. Considering the propeller with variable pitch optimization strategy， the maximum pulling force can be increased by 78.42% in take-off climbing condition， which can provide a larger climbing rate， which is conducive to the solar powered UAV quickly flying through the troposphere to reach the upper design point during take-off.

Key words: propeller, standard strip analysis, multiple design points, solar powered UAV, aerodynamic optimization, variable pitch angle, optimization strategy

CLC Number:

V211.44

Haifeng WANG, Kunpeng LIU, Hongxin JIANG, Chenxi DU. Aerodynamic optimization method of propeller multi⁃design points and variable pitch angle strategy[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(9): 528831.

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References 23

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阶段	工况	飞行高度 H/km	爬升率 V_h /（m·s^-1）	升力系数C_L	阻力系数C_D
起飞爬升	0 km	0	1.0	0.611	0.019 8
	h₂/3	7	1.0	0.607	0.020 0
	2h₂/3	14	1.0	0.602	0.020 6
昼夜循环	h₁	13	0	0.602	0.020 5
	（h₁+h₂）/2	17	0.5	0.595	0.022 0
	h₂	21	0	0.591	0.025 0

阶段	工况	桨叶拉力需求 T/N	来流速度 V/（m·s^-1）
起飞爬升	0 km	268.275	10.629
	h₂/3	207.841	15.383
	2h₂/3	157.965	24.873
昼夜循环	h₁	72.306	23.005
	（h₁+h₂）/2	112.023	31.670
	h₂	89.820	43.567

参数类型	参数	取值
设计变量	螺旋桨外形参数向量X_S	0.5 X_S₀~1.5 X_S₀
设计变量	变距策略参数向量X_β /（°）	0~-20
约束条件	最大转速n_s/（r·min^-1）	1 200
	最大扭矩Q_max/ （N·m）	65
	起飞爬升阶段工况1需求拉力 T_1min/N	268.275
	起飞爬升阶段工况2需求拉力 T_2min/N	207.841
	起飞爬升阶段工况3需求拉力 T_3min/N	157.965

参数变量	优化结果
c_R_root	0.104 6
c_R_max	0.107 4
c_R_tip	0.032 3
x_c_max	0.289 9
β_root/（°）	47.31
β_tip/（°）	14.31
x_p/mm	1 718.3
β₁/（°）	-12.7
β₂/（°）	-9.8
β₃/（°）	-3.0

阶段	飞行高度/ km	转速/ （r·min^-1）	拉力/N	扭矩/ （N·m）	效率
起飞爬升	0	763.9	329.0	65	0.673
	7	886.5	283.5	65	0.723
	14	998.6	211.7	65	0.775
昼夜循环	13	594.8	72.3	32.12	0.831
	17	917.8	112.0	44.99	0.821
	21	1200	89.8	38.47	0.811

Aerodynamic optimization method of propeller multi⁃design points and variable pitch angle strategy

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飞行高度/km	性能参数	优化前	优化后
13	拉力/N	64.7	72.3
	扭矩/（N·m）	29.30	32.12
	效率	0.816	0.831
17	拉力/N	104.3	112.0
	扭矩/（N·m）	42.92	44.99
	效率	0.801	0.821
21	拉力/N	83.8	89.8
	扭矩/（N·m）	36.98	38.47
	效率	0.786	0.811

飞行高度/km		0	7	14
定距桨	转速/（r·min^-1）	357.8	515.7	827.9
	拉力/N	184.4	182.4	179.8
	效率/%	80.50	79.90	79.40
变距桨	转速变化/%	113.5	71.90	20.62
	拉力变化/%	78.42	55.43	17.74
	效率变化/%	-13.18	-7.63	-1.86

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