变转速刚性旋翼性能与载荷风洞试验

刘士明; 应旭成; 李登安; 邵松

doi:10.13224/j.cnki.jasp.20210217

变转速刚性旋翼性能与载荷风洞试验

doi: 10.13224/j.cnki.jasp.20210217

南京模拟技术研究所，南京 210000

基金项目: 旋翼空气动力学重点实验室研究开放课题（RAL20200403）

详细信息

作者简介:
刘士明（1991-），男，高级工程师，博士，主要从事直升机旋翼设计研究

中图分类号: V211.47
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- 被引次数: 0
出版历程
- 收稿日期: 2021-05-07
- 网络出版日期: 2023-01-09

Wind tunnel test of variable speed rigid rotor performance and load

Nanjing Research Institute on Simulation Technology，Nanjing 210000，China

摘要

摘要:
为研究转速变化对旋翼性能与振动载荷的影响，研制了一副无铰式刚性缩比模型旋翼，开展动力学和马赫数相似的悬停试验与风洞试验。试验研究不同旋翼拉力和吹风速度时变旋翼转速对配平、性能、桨叶与拉杆载荷、桨毂载荷等多个方面的影响，以性能和交变载荷的重复性与周期性证明试验结果是可信的。结果表明：降转速可降低旋翼悬停和前飞状态的需用功率，且拉力越低效果越明显；降转速对桨毂振动载荷影响不明显，但增加了配平所需的周期变距操纵，会增加桨叶与变距拉杆的旋翼转速频率振动载荷，对旋转部件疲劳寿命不利；变旋翼转速应避开旋翼固有频率，防止因共振而导致交变载荷增大。
- 旋翼 /
- 气动性能 /
- 悬停效率 /
- 振动载荷 /
- 风洞试验
Abstract:
In order to study the influence of rotating speed variation on the performance and vibratory load of rotor, a scaled hingeless rigid rotor was developed. The dynamic scaled and Mach number scaled hover test and wind tunnel test were carried out. Rotor trim, performance, blade and pitch link loads, hub loads and some other aspects were studied by changing the thrust, airspeed and rotating speed. The credibility of the test results was proved by the repeatability and periodicity of the performance and the vibratory load. Results indicated that the power required can be saved by reducing the rotor speed for both hover and forward flight, and lower thrust showed higher effectiveness. The amplitude of vibratory hub load was not obviously increased by reducing rotor speed. The frequency of rotor rotating speed vibratory blade load and pitch link load increased, because the cyclic pitches were greater in trimmed condition for slower speed, which was adverse to the fatigue life of the rotating parts. Natural frequencies of the rotating blade should be avoided for varying the rotor speed to prevent enlargement of the vibratory load caused by the resonance.
- rotor /
- aerodynamic performance /
- figure of merit /
- vibratory load /
- wind tunnel test

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图 1 刚性旋翼模型

Figure 1. Rigid rotor model

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图 2 旋翼固有频率

Figure 2. Rotor natural frequencies

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图 3 风洞中的旋翼试验模型

Figure 3. Model rotor in the wind tunnel

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图 4 拉力系数-总距重复性（ω=100%Ω）

Figure 4. Repeatability of thrust coefficient with collective pitch （ω=100%Ω）

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图 5 拉力系数与悬停效率关系重复性（ω=100%Ω）

Figure 5. Repeatability of relation between thrust coefficient and figure of merit （ω=100%Ω）

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图 6 不同转速的拉力系数-总距曲线

Figure 6. Curve of thrust coefficient with collective pitch of variable speed rotor

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图 7 不同转速的悬停效率-拉力系数曲线

Figure 7. Curve of figure of merit with thrust coefficient of variable speed rotor

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图 8 不同转速的功率-拉力曲线

Figure 8. Curve of power required with thrust of variable speed rotor

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图 9 不同旋翼转速的悬停效率-拉力曲线

Figure 9. Curve of figure of merit with thrust for different speed rotor

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图 10 桨叶摆振方向应变频谱幅值

Figure 10. Frequency spectrum amplitude of lead-lag direction strain on blade

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图 11 不同ω功率随风洞速度关系

Figure 11. Power versus wind tunnel speed for varying ω

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图 12 不同ω下L/D随风洞速度关系

Figure 12. L/D versus wind tunnel speed for varying ω

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图 13 不同风速操纵角度随旋转速度关系

Figure 13. Control angle versus rotating speed for varying wind speed

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图 14 振动载荷周期性

Figure 14. Periodicity of vibratory load

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图 15 振动载荷重复性（ω=70%Ω，μ=0.18）

Figure 15. Repeatability of vibratory load （ω=70%Ω，μ=0.18）

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图 16 不同转速桨叶弯矩与拉杆载荷谐波幅值

Figure 16. Blade bending moment and pitch link load harmonic amplitudes for various rotating speed

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图 17 不同ω桨叶摆振弯矩（去除均值）

Figure 17. Chordwise bending moment for varying ω （mean removed）

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图 18 不同ω桨毂载荷谐波幅值

Figure 18. Hub load harmonic amplitudes for varying ω

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图 19 不同拉力桨毂侧向载荷谐波幅值

Figure 19. Hub lateral load harmonic amplitudes for various thrust

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图 20 不同拉力桨毂侧向载荷（去除均值）

Figure 20. Hub lateral load for various thrust （mean removed）

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表 1 旋翼模型参数

Table 1. Rotor model parameters

参数	数值及说明
旋翼形式	无铰式刚性旋翼
桨叶片数 k	4
旋翼半径R/m	2
额定转速Ω/（r/min）	1 050
实度σ	0.0712
预锥角 β_p/（°）	4.5

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表 2 翼型和弦长分布

Table 2. Distribution of airfoil and chord

位置	翼型	弦长/m
0.2R	21%厚度（NR121）	0.149
0.454R	15%厚度（NR115）	0.128
0.554R～0.765R	12%厚度（NR112）	0.119～0.101
0.865R～0.965R	9%厚度（NR109）	0.093～0.084
0.965R～1R	9%厚度（NR109）	0.084～0.045 （抛物后掠）

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表 3 模型旋翼结构参数

Table 3. Structural parameter of rotor model

序号	桨叶分段/ mm	挥舞刚度/ （N·m²）	摆振刚度/ （N·m²）	扭转刚度/ （N·m²）	线密度/ （kg/m）	挥舞惯量/ （g·m）	摆振惯量/ （g·m）
1	60～254	20000	12000	16000.0	8.000	8.000	8.000
2	254～282	11368	369845	15575.0	7.615	0.668	10.070
3	282～400	4820	257769	6589.7	5.129	0.415	5.061
4	400～650	1612	57476	2115.8	1.630	0.129	2.076
5	650～1050	740	32961	1077.4	2.178	0.070	1.942
6	1050～1250	209	14541	291.7	0.827	0.019	0.608
7	1250～1650	208	8914	208.9	1.179	0.018	0.660
8	1650～1900	68	4020	90.1	0.809	0.010	0.344
9	1900～2000	39	2201	47.0	1.146	0.009	0.288

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表 4 桨叶固有频率

Table 4. Blade natural frequencies

模态	实测值/Hz	计算值/Hz	误差/%
静态β₁（仅桨叶）	6.38	5.816	−8.84
静态β₂（仅桨叶）	24.93	24.93	0
静态ζ₁（仅桨叶）	38.30	37.89	−1.07
静态ζ₁（旋翼）	21.7	23.8	9.7
额定转速ζ₁	29.5	29.1	−1.4

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表 5 变转速对旋翼悬停性能的影响

Table 5. Influence of performance of rotor in hover with variable speed

拉力/N	额定转速功率/kW	降转速功率/kW	节省功率/kW	功率相对变化/%
1 500	24.6	14.6	10	40.7
2 000	30.6	21.4	9.2	30.1
2 500	37.6	29.8	7.8	20.7
3 000	45.6	39.4	6.2	13.6
3 500	55.0	49.5	5.5	10.0

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参考文献(18)

[1]	JASON H S, FARHAN G. An investigation of variable speed rotor RPM on performance and trim[C]// Proceedings of the American Helicopter Society 64th Annual Forum. Montreal, Canada: the American Helicopter Society International, 2008: 278.1-278.9.
[2]	邓景辉. 高速直升机前行桨叶概念旋翼技术[J]. 航空科学技术,2012(3): 9-14. doi: 10.3969/j.issn.1007-5453.2012.03.003 Deng Jinghui. The ABC rotor technology for high speed helicopter[J]. Aeronautical Science & Technology,2012(3): 9-14. (in Chinese) doi: 10.3969/j.issn.1007-5453.2012.03.003
[3]	方永红. 无人直升机系统发展展望[J]. 航空科学技术,2021,32(1): 35-40. FANG Yonghong. Development prospect of unmanned helicopter system[J]. Aeronautical Science & Technology,2021,32(1): 35-40. (in Chinese)
[4]	陈铭,武梅丽文,曹飞. 复合式直升机技术特点及发展概述[J]. 航空制造技术,2017,60(21): 94-101. CHEN Ming,WU Meiliwen,CAO Fei. Technology and development overview for compound helicopter[J]. Aeronautical Manufacturing Technology,2017,60(21): 94-101. (in Chinese)
[5]	GRAHAM M B D,INDJERT C. Aeromechanics of a slowed rotor[J]. Journal of the American Helicopter Society,2015,60(3): 1-13.
[6]	ANUBHAV D,HYEOSOO YEO,THOMAS R N. Experimental investigation and fundamental understanding of a slowed UH-60A rotor at high advance ratios[J]. Journal of the American Helicopter Society,2013,58(2): 1-17.
[7]	BEN B, INDERJIT C. Wind tunnel testing for performance and vibratory loads of a variable-speed mach-scale rotor[C]// Proceedings of the American Helicopter Society 67th Annual Forum. Virginia Beach, Virginia: the American Helicopter Society International, 2011: 137.1-137.14.
[8]	韩东. 变转速旋翼直升机性能和配平研究[J]. 航空学报,2012,34(6): 1241-1248. HAN Dong. Study on the performance and trim of a helicopter with a variable speed rotor[J]. Acta Aeronautica et Astronautica Sinica,2012,34(6): 1241-1248. (in Chinese)
[9]	刘士明,杨卫东,董凌华,等. 优化转速旋翼性能分析与应用[J]. 南京航空航天大学学报,2014,46(6): 888-894. doi: 10.3969/j.issn.1005-2615.2014.06.011 LIU Shiming,YANG Weidong,DONG Linghua,et al. Performance investigation and applications of optimum speed rotors[J]. Journal of Nanjing University of Aeronautics & Astronautics,2014,46(6): 888-894. (in Chinese) doi: 10.3969/j.issn.1005-2615.2014.06.011
[10]	吴裕平,董凌华,解望. 变转速旋翼直升机的续航性能与变速策略[J]. 南京航空航天大学学报,2018,50(2): 193-199. doi: 10.16356/j.1005-2615.2018.02.007 WU Yuping,DONG Linghua,XIE Wang. Endurance performance and rotational speed change of variable speed rotor helicopter[J]. Journal of Nanjing University of Aeronautics & Astronautics,2018,50(2): 193-199. (in Chinese) doi: 10.16356/j.1005-2615.2018.02.007
[11]	池骋,陈仁良. 旋翼转速变化对直升机需用功率、配平、振动及噪声的影响分析[J]. 南京航空航天大学学报,2018,50(5): 629-639. doi: 10.16356/j.1005-2615.2018.05.007 CHI Cheng,CHEN Renliang. Influence of rotor speed variation on required power, trim, vibration and noise of helicopter[J]. Journal of Nanjing University of Aeronautics & Astronautics,2018,50(5): 629-639. (in Chinese) doi: 10.16356/j.1005-2615.2018.05.007
[12]	余智豪,周云,宋彬. 大前进比变转速旋翼气弹动力学建模与载荷特性分析[J]. 振动与冲击,2021,40(4): 17-22. YU Zhihao,ZHOU Yun,SONG Bin. Aeroelastic modeling and load analysis of a variable speed rotor in high advance ratio[J]. Journal of Vibration and Shock,2021,40(4): 17-22. (in Chinese)
[13]	杨悦. 变旋翼转速直升机飞行特性研究[D]. 南京: 南京航空航天大学, 2017. YANG Yue. Research on helicopter flight characteristics of variable speed rotor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2017. (in Chinese)
[14]	孙宇. 变转速刚性旋翼载荷分析与试验研究[D]. 南京: 南京航空航天大学, 2015. SUN Yu. Loads analysis of variable speed rigid rotor[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2015. (in Chinese)
[15]	吴凯华, 吴裕平, 孙宇, 等. 变转速刚性旋翼风洞试验研究[C]// 第32届全国直升机年会. 四川绵阳: 中国航空学会直升机分会, 2016: 2.21-2.24.
[16]	黄东盛,吴世杰,韩东. 变转速模型旋翼挥舞摆振低阶载荷试验研究[J]. 航空学报,2016,37(3): 873-882. HUANG Dongsheng,WU Shijie,HAN Dong. Experimental investigation of flapwise and lagwise lower harmonic loads of a variable speed model rotor[J]. Acta Aeronautica et Astronautica Sinica,2016,37(3): 873-882. (in Chinese)
[17]	徐明,韩东,李建波. 变转速旋翼气动特性分析及试验研究[J]. 航空学报,2013,34(9): 2047-2056. XU Ming,HAN Dong,LI Jianbo. Analysis and experimental investigation on the aerodynamic characteristics of variable speed rotor[J]. Acta Aeronautica et Astronautica Sinica,2013,34(9): 2047-2056. (in Chinese)
[18]	WENBIN Y,VITALI V V,DEWEY H H,et al. Validation of the variational asymptotic beam sectional analysis (VABS)[J]. AIAA Journal,2002,40(10): 2105-2113. doi: 10.2514/2.1545