共轴刚性旋翼直升机旋翼控制相位角问题分析

袁野; 陈仁良; 李攀; 鲁可

doi:10.13700/j.bh.1001-5965.2016.0812

共轴刚性旋翼直升机旋翼控制相位角问题分析

doi: 10.13700/j.bh.1001-5965.2016.0812

袁野¹,
陈仁良^1, ,,
李攀¹,
鲁可²

1.
南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016
2.
中国直升机设计研究所直升机旋翼动力学重点实验室, 景德镇 333001

基金项目:

国家自然科学基金 51405227

航空科学基金 20145752034

江苏高校优势学科建设工程资助项目 BBBB

详细信息

作者简介:
袁野男, 博士研究生。主要研究方向:直升机飞行动力学

陈仁良男, 博士, 教授, 博士生导师。主要研究方向:直升机飞行动力学、直升机空气动力学

通讯作者:
陈仁良, E-mail: crlae@nuaa.edu.cn

中图分类号: V212.4
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- 被引次数: 0
出版历程
- 收稿日期: 2016-10-19
- 录用日期: 2016-11-25
- 网络出版日期: 2017-10-20

Rotor control phase angle analysis for coaxial rigid rotor helicopter

YUAN Ye¹,
CHEN Renliang^{1
, ,},
LI Pan¹,
LU Ke²

1.
National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Science and Technology on Rotorcraft Aeromechanics Laboratory, Chinese Helicopter Research & Development Institute, Jingdezhen 333001, China

Funds:

National Natural Science Foundation of China 51405227

Aeronautical Science Foundation of China 20145752034

the Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions BBBB

More Information

Corresponding author: CHEN Renliang, E-mail:crlae@nuaa.edu.cn

摘要

摘要:
利用共轴刚性旋翼直升机飞行动力学模型，以XH-59A共轴刚性旋翼直升机为研究对象，分析了旋翼控制相位角对纵向配平特性、需用功率以及上、下旋翼桨毂弯矩的影响。基于分析结果，提出了一种针对共轴刚性旋翼直升机的旋翼控制相位角的配置方法。该配置方法以降低直升机需用功率为目标，并保证上、下旋翼桨毂弯矩和配平特性满足要求。通过该方法能使XH-59A直升机在0~80 m/s的飞行速度范围内满足上、下旋翼最大桨毂弯矩和纵向操纵限幅的要求，并且能最多降低8%的直升机需用功率，为共轴刚性旋翼直升机的设计提供了参考依据。
- 双旋翼共轴式直升机 /
- 需用功率 /
- 旋翼控制相位角 /
- 配平特性 /
- 桨毂弯矩
Abstract:
Adopting the flight dynamic model of coaxial rigid rotor helicopter, this paper sets the XH-59A coaxial rigid rotor helicopter as research object and analyzes the influence of rotor control phase angle on longitudinal trim characteristics, helicopter power required and hub bending moment of upper and lower rotor. Based on the analysis results, this paper proposes the allocation method of coaxial rigid rotor helicopter's rotor control phase angle. It aims to decrease the helicopter power required and make upper and lower rotor's hub bending moment and trim characteristics meet the requirement. The method can make the XH-59A helicopter satisfy the requirements of hub bending moment of upper and lower rotor and longitudinal cyclic pitch limitation within the flight speed scope of 0-80 m/s, and can minimize up to 8% power required. This method provides reference for design of coaxial rigid rotor helicopter.
- coaxial twin helicopter /
- power required /
- rotor control phase angle /
- trim characteristics /
- hub bending moment

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图 1 共轴刚性旋翼纵向周期变距操纵挥舞

Figure 1. Control flapping of longitudinal cyclic pitch on coaxial rigid rotor

下载: 全尺寸图片幻灯片

图 2 稳定平飞时的纵向周期变距

Figure 2. Longitudinal cyclic pitch in steady level flight

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图 3 稳定平飞时的俯仰姿态

Figure 3. Pitch attitude in steady level flight

下载: 全尺寸图片幻灯片

图 4 稳定平飞时的需用功率

Figure 4. Power required in steady level flight

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图 5 稳定平飞时的上、下旋翼最大桨毂弯矩

Figure 5. Maximum hub bending moment of upper and lower rotor in steady level flight

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图 6 旋翼控制相位角配置流程图

Figure 6. Flowchart of rotor control phase angle allocation

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图 7 旋翼控制相位角配置结果

Figure 7. Results of rotor control phase angle allocation

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表 1 XH-59A共轴刚性旋翼直升机参数^[15]

Table 1. Parameters of XH-59A coaxial rigid rotor helicopter^[15]

参数	数值
旋翼半径/m	5.5
桨叶片数	3×2
预扭角/(°)	-10
旋翼速度/(rad·s^-1)	36.1
桨叶根梢比	2
一阶挥舞固有频率	1.4Ω
上、下旋翼轴间距/m	0.77
平尾面积/m²	5.57
垂尾面积/m²	2.79
起飞重量/kg	5 500
下旋翼坐标/m	(0, 0, -0.89)
重心坐标/m	(0, 0, 0)
平尾坐标/m	(-6.80, 0, 0.20)
垂尾坐标/m	(-6.80, 0, -0.50)

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