变旋翼转速对直升机飞行品质的影响分析

卫圆; 陈仁良; 王洛烽; 叶毅

doi:10.13224/j.cnki.jasp.20240174

变旋翼转速对直升机飞行品质的影响分析

doi: 10.13224/j.cnki.jasp.20240174

南京航空航天大学直升机动力学全国重点实验室，南京 210016

基金项目: 国家自然科学基金（11672128）；江苏高校优势学科建设工程资助项目

详细信息

作者简介:
卫圆（1994-），男，博士生，研究方向为直升机飞行力学与控制

通讯作者:
陈仁良（1964-），男，教授、博士生导师，博士，研究方向为直升机多学科优化设计、直升机飞行力学与控制、直升机空气动力学。E-mail：crlae@nuaa.edu.cn

中图分类号: V212.4
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出版历程
- 收稿日期: 2024-03-26
- 网络出版日期: 2024-11-06

Analysis on influence of variable rotor speed on helicopter handling quality

National Key Laboratory of Helicopter Aeromechanics，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

摘要

摘要:
为分析旋翼转速变化对飞行品质的影响，建立耦合了发动机动态特性的直升机飞行动力学模型。首先，建立发动机气动热力学模型与旋翼飞行力学模型。在此基础上，建立包含发动机动态特性，直升机各部件气动力特性与部件间气动干扰的直升机飞行动力学模型。最后，以UH-60A直升机为样例直升机，研究发动机动力涡轮输出引起的旋翼转速变化对直升机飞行品质的影响。研究表明：旋翼转速降低后，直升机需用功率减少，同时旋翼反扭矩与总距杆量增加。扭矩特性、高度特性与总距偏航耦合飞行品质均随旋翼转速下降而恶化。直升机滚转、俯仰与偏航3个通道带宽随旋翼转速降低而增大。
- 直升机 /
- 变旋翼转速 /
- 涡轴发动机 /
- 飞行品质 /
- 飞行动力学
Abstract:
To analyze the impact of rotor speed changes on handling quality, a helicopter flight dynamics model coupled with engine dynamic characteristics was established. Then, an engine aerodynamic thermodynamic model and a rotor flight mechanics model were established. On this basis, a helicopter flight dynamics model includeing the dynamic characteristics of the engine, aerodynamic characteristics of various components of the helicopter, and aerodynamic interference between components was established. Taking the UH-60A helicopter as an example, the impact of rotor speed changes caused by engine power turbine output on helicopter handling quality was studied. Research showed that when the rotor speed decreased, the power required by the helicopter decreased, while the rotor counter torque and total pitch increased. The torque characteristics, altitude characteristics, and total pitch yaw coupled with the handling quality all deteriorated with the decrease of rotor speed. The bandwidth of the three channels of helicopter roll, pitch, and yaw increased as the rotor speed decreased.
- helicopter /
- variable rotor speed /
- turboshaft engine /
- handling quality /
- flight dynamics

HTML

图 1 旋翼非定常气动力计算流程图

Figure 1. Flow chart of rotor unsteady aerodynamic calculation

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图 2 直升机显模型跟踪控制系统示意图

Figure 2. Schematic of helicopter explicit model following control system

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图 3 不同旋翼转速下直升机配平计算结果

Figure 3. Helicopter trim result with different rotor speeds

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图 4 直升机动态响应计算结果

Figure 4. Calculation result of helicopter dynamic response

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图 5 发动机动态响应曲线

Figure 5. Dynamic response of engine parameters

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图 6 直升机扭矩特性飞行品质

Figure 6. Handling quality of helicopter torque response characteristic

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图 7 直升机高度特性飞行品质

Figure 7. Handling quality of helicopter height response characteristic

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图 8 直升机总距偏航耦合特性飞行品质

Figure 8. Handling quality of helicopter collective-yaw coupling characteristic

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图 9 直升机中幅姿态快捷性

Figure 9. Helicopter moderate-amplitude attitude change

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图 10 直升机带宽/相位延迟

Figure 10. Helicopter bandwidth and phase delay

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表 1 样例直升机参数

Table 1. Parameters of baseline helicopter

参数	数值
旋翼直径/m	8.177
旋翼设计转速/（rad/s）	27.0
直升机质量/kg	7257.48
重心位置（相对机头）/m	−8.91, 0, −5.88
滚转惯性矩/（kg·m²）	7406.16
滚转偏航耦合惯性矩/（kg·m²）	2133.83
俯仰惯性矩/（kg·m²）	53512.6
偏航惯性矩/（kg·m²）	50012.3

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表 2 高度响应计算结果

Table 2. Height response calculation result

参数	旋翼转速/%
参数	85	90	95	100
K	3.4162	3.5022	3.6851	4.1982
τ/s	0.15917	0.18419	0.18419	0.20714
$\tilde T$/s	2.2295	2.3390	2.5800	3.2495
r²	0.99751	0.99682	0.99635	0.99517

下载: 导出CSV

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