一种混合式电控旋翼操纵特性

田季声; 陆洋; 王鹏; 许细策

doi:10.13224/j.cnki.jasp.20250437

一种混合式电控旋翼操纵特性

doi: 10.13224/j.cnki.jasp.20250437

田季声^1,,
陆洋^1,*, ,,
王鹏²,
许细策¹

1.
南京航空航天大学直升机动力学全国重点实验室，南京 210016
2.
中国人民解放军 63898部队，河南济源 459000

基金项目: 国家自然科学基金（12404514）；航空科学基金（2024M009052002）；国家资助博士后研究人员计划（GZB20240969）；中国博士后科学基金（2024M754135）；江苏省自然科学基金（BK20241375）；江苏省卓越博士后计划

详细信息

作者简介:
田季声（2001-），男，硕士生，主要研究方向为直升机动力学。E-mail：sx2301189@nuaa.edu.cn

通讯作者:
陆洋（1977-），男，教授，博士，主要研究方向为直升机动力学及其控制、直升机设计。E-mail：luyang@nuaa.edu.cn

中图分类号: V215.3
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出版历程
- 收稿日期: 2025-09-22
- 网络出版日期: 2025-12-20

Handling characteristics of a hybrid electronically controlled rotor

TIAN Jisheng^1
,,
LU Yang^{1,*
, ,},
WANG Peng²,
XU Xice¹

1.
National Key Laboratory of Helicopter Aeromechanics，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Unit 63898 of the Chinese People’s Liberation Army，Jiyuan Henan 459000，China

摘要

摘要:
提出了一种基于宏纤维复合材料（MFC）结合桨根作动器的混合式电控旋翼。为探索这种混合式电控旋翼基于MFC进行周期变距的可行性，首先基于中等变形梁理论，结合MFC压电本构方程，建立了混合式电控旋翼气弹动力学分析模型。并通过与试验结果和CFD计算结果进行对比，初步验证了该模型的正确性。之后基于该分析模型，以MFC模型旋翼为对象，仿真研究了混合式电控旋翼主要控制参数与设计参数对旋翼操纵响应的影响规律。并以±12°的旋翼周期变距范围为设计目标，分析了利用MFC实现混合式电控旋翼周期变距的可行性。仿真结果表明：通过提高MFC驱动电压、增加MFC铺设量、降低桨叶扭转刚度等措施，可有效提高该混合式电控旋翼的弹性扭转操纵量；同时模型桨叶最大可产生约±12°的1 Ω扭转角，达到了周期变距设计目标。
- 电控旋翼 /
- 宏纤维复合材料 /
- 气弹耦合 /
- 压电方程 /
- 操纵特性
Abstract:
A hybrid electrically controlled rotor based on macro-fiber composite (MFC) was proposed. To explore the feasibility and control characteristics of this hybrid ECR, an aeroelastic dynamics analysis model was first established based on moderate deflection beam theory combined with the piezoelectric constitutive equations of MFC. Subsequently, using this analytical model and focusing on the MFC model rotor, simulation studies were conducted to investigate the influences of key control and design parameters on the rotor’s control response. With a design target of achieving a cyclic pitch range of ±12°, the feasibility of utilizing MFC for cyclic pitch control in the hybrid electrically controlled rotor was analyzed. The simulation results indicated that by increasing the MFC driving voltage, adding more MFC layers, and reducing blade torsional stiffness, the elastic torsional control authority of the hybrid electrically controlled rotor can be effectively enhanced. Meanwhile, the model rotor blade tip can achieve a maximum 1 Ω torsional angle of approximately ±12°, meeting the initial cyclic pitch design objective.
- electrically controlled rotor /
- marco fiber composite /
- aerodynamic/elastic coupling /
- piezoelectric equations /
- handling characteristics

HTML

图 1 采埃孚公司混合式电控旋翼概念^[16]

Figure 1. Hybrid electronically controlled rotor of ZFL^[16]

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图 2 基于MFC的混合式电控旋翼示意图

Figure 2. Hybrid electronically controlled rotor based on MFC

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图 3 桨根坐标系与变形后坐标系

Figure 3. Blade root coordinate system and deformed coordinate system

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图 4 单元节点与自由度配置

Figure 4. Configuration of Unit nodes and degrees of freedom

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图 5 MFC材料方向定义

Figure 5. Definition of MFC material orientation

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图 6 MFC铺设示意与翼型表面MFC微元上的驱动应力

Figure 6. Actuation stress on the MFC element over the airfoil

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图 7 主动扭转模型桨叶示意图（单位：m）

Figure 7. Active-twist model blade （unit：m）

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图 8 扭转试验用MFC模型桨叶^[32]

Figure 8. Model blade for torsional testing^[32]

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图 9 静止状态下桨尖扭转角计算验证

Figure 9. Computational validation of blade tip twist angle in stationary state

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图 10 MFC驱动下的主动扭转角变化

Figure 10. Active-twist angle variation under MFC actuation

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图 11 旋转状态下桨叶升力验证

Figure 11. Lift validation of rotor blades in rotating state

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图 12 部分参数定义与MFC铺设示意图

Figure 12. Schematic diagram of MFC layout and parameter definitions

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图 13 不同驱动电压下的MFC弹性扭转变距操纵量

Figure 13. Pitch control from MFC-induced elastic twist under varying actuation voltages

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图 14 不同驱动电压峰峰值下的操纵响应

Figure 14. Control response under varying peak-to-peak driving voltages

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图 15 不同驱动频率下的MFC弹性扭转变距操纵量

Figure 15. Pitch control from MFC-induced elastic twist under varying driving frequencies

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图 16 不同驱动频率下的操纵响应

Figure 16. Control response under varying driving frequencies

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图 17 不同初始相位下的MFC弹性扭转变距操纵量

Figure 17. Pitch control from MFC-induced elastic twist under varying initial phases

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图 18 不同初始相位下的操纵响应

Figure 18. Control response under varying initial phases

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图 19 不同MFC铺设范围下的弹性扭转变距操纵量

Figure 19. Pitch control from MFC-induced elastic twist under varying MFC coverage ranges

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图 20 不同MFC铺设范围下的操纵响应

Figure 20. Control response under varying MFC coverage ranges

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图 21 不同MFC铺设位置下的弹性扭转变距操纵量

Figure 21. Pitch control from MFC-induced elastic twist under varying MFC placement positions

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图 22 不同MFC铺设位置下的操纵响应

Figure 22. Control response under varying MFC placement positions

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图 23 不同MFC纤维铺设角度下的弹性扭转变距操纵量

Figure 23. Pitch control from MFC-induced elastic twist under varying MFC fiber orientation angles

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图 24 不同MFC纤维铺设角度下的操纵响应

Figure 24. Control response under varying MFC fiber orientation angles

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图 25 不同桨叶扭转刚度下的弹性扭转变距操纵量

Figure 25. Pitch control from MFC-induced elastic twist under varying blade torsional stiffness

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图 26 不同桨叶扭转刚度下的操纵响应

Figure 26. Control response under varying blade torsional stiffness

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图 27 参数优化配置下的桨叶弹性扭转角时间历程

Figure 27. Time history of blade elastic torsion angle under optimized parameter configuration

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图 28 施加偏置电压后的弹性扭转角时间历程

Figure 28. Time history of blade elastic torsion angle after applying bias voltage

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表 1 模型旋翼主要物理参数

Table 1. Main physical parameters of the rotor

参数	数值
直径/m	2.8
弦长/m	0.121
根切半径/m	0.2
转速/（r/min）	600
桨叶片数	2
总距/（°）	2

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表 2 混合式电控旋翼基本参数

Table 2. Fundamental parameters of the HECR rotor

参数	数值
直径/m	2.8
弦长/m	0.121
根切半径/m	0.2
转速/（r/min）	600
桨叶片数	2
总距/（°）	5
翼型	NACA23012
MFC沿弦向长度/m	0.08
MFC压电常数d₃₃/（pC/N）	487.9
MFC压电常数d₃₁/（pC/N）	−195.8

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表 3 单晶MFC材料特性^[34]

Table 3. Optimized material properties of MFC^[34]

参数	数值
弹性模量E₃/GPa	6.23
弹性模量E₁/GPa	11.08
切变模量G₃₁/GPa	2.01
泊松比ν₃₁	0.229
压电常数d₃₃/（pC/N）	1896.52
压电常数d₃₁/（pC/N）	−861.20

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