刚性旋翼参数对纵向动稳定性影响分析

陈金鹤; 索谦; 张威; 李春华; 康磊

doi:10.13224/j.cnki.jasp.20240847

刚性旋翼参数对纵向动稳定性影响分析

doi: 10.13224/j.cnki.jasp.20240847

中国航空工业集团有限公司中国直升机设计研究所，天津 300300

详细信息

作者简介:
陈金鹤（1989-），男，高级工程师，硕士，主要从事直升机飞行动力学方面的研究。E-mail：cjhe08034105@163.com

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出版历程
- 收稿日期: 2024-12-19
- 网络出版日期: 2025-04-25

Influence of rigid rotor parameters on longitudinal dynamic stability

China Helicopter Design and Research Institute，Aviation Industry Corporation of China，Limited，Tianjin 300300，China

摘要

摘要:
共轴刚性旋翼直升机前飞状态的纵向动稳定性特征受旋翼设计参数影响较大。针对刚性旋翼主要设计参数进行计算分析。采用CAMRAD Ⅱ建立XH-59A共轴高速直升机模型，探讨旋翼桨叶挥舞频率、变距-挥舞、桨叶质量分布、桨叶重心-气动中心（CG-AC）位置、扭转刚度等对共轴刚性旋翼直升机纵向长周期模态的影响，计算结果表明：刚性桨叶的挥舞频率越高，旋翼迎角不稳定性越强，且随前飞速度增强；正的变距-挥舞耦合、较大挥舞惯性距、桨叶剖面重心（CG）位于气动中心（AC）之前等有效降低迎角不稳定性，可有效改善共轴刚性旋翼直升机纵向动稳定性；较大的扭转刚度会抑制桨叶扭转模态，从而抑制桨叶重心-气动中心对纵向长周期模态的影响。
- 刚性旋翼 /
- 共轴直升机 /
- 旋翼参数 /
- 迎角稳定性 /
- 纵向动稳定性
Abstract:
The longitudinal dynamic stability characteristics of a coaxial rigid rotor helicopter in forward flight are greatly affected by the rotor design parameters. The main design parameters of advancing blade concept rotor were calculated and analyzed. CAMRAD Ⅱ was used to establish XH-59A coaxial high speed helicopter model. The effects of rotor blade flapping frequency, pitch-flapping, blade mass distribution, the position between blade center of gravity-aerodynamic center (CG-AC) and torsional stiffness on the longitudinal long period modes of coaxial helicopter were analyzed. The results showed that: the higher flapping frequency of a rigid blade indicated the stronger rotor angle-of-attack instability and increased with forward flight speed. Positive pitch-flap coupling, large flapping inertia moment and center of gravity (CG) located in front of aerodynamic center (AC) effectively reduced angle of attack instability for rigid rotor and improved the longitudinal dynamic stability of the helicopter; the large torsional stiffness suppressed the blade torsional modes, thus suppressing the influence of the blade CG-AC on the longitudinal long-period modes.
- rigid rotor /
- coaxial helicopter /
- rotor parameters /
- angle of attack stability /
- longitudinal dynamic stability

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图 1 XH-59A 桨叶剖面挥舞刚度和扭转刚度

Figure 1. XH-59A blade section flap stiffness and torsional stiffness

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图 2 计算与试飞数据对比

Figure 2. Comparison of calculation and test flight data

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图 3 荷兰滚模态

Figure 3. Dutch roll mode

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图 4 不同频率的旋翼迎角稳定性导数

Figure 4. Rotor angle of attack stability derivatives at different frequencies

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图 5 不同挥舞频率对纵向长周期模态影响

Figure 5. Influence of different flapping frequencies on longitudinal long-period modes

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图 6 变距-挥舞系数对纵向长周期模态影响

Figure 6. Effect of pitch-flap coefficient on longitudinal long period modes

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图 7 桨叶质量分布

Figure 7. Blade mass distribution

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图 8 挥舞惯性距对旋翼迎角稳定性影响

Figure 8. Effect of flapping inertia moment on rotor angle-of-attack stability

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图 9 桨尖距分布（V=80 m/s）

Figure 9. Tip clearance distribution （V=80 m/s）

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图 10 不同质量分布的长周期模态

Figure 10. Long-period modes with different mass distributions

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图 11 纵向长周期模态特征根

Figure 11. Longitudinal long-period mode root

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图 12 扭转刚度的影响

Figure 12. Influence of torsional stiffness

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表 1 XH-59A共轴刚性旋翼直升机参数

Table 1. Parameters of XH-59A coaxial rigid rotor helicopter

参数	数值及说明
旋翼半径/m	5.5
桨叶片数	3×2（双旋翼）
旋翼转速/（rad/s）	36.1
预锥角/（°）	3
轴倾角/（°）	0
上下旋翼轴间距/m	0.77
平尾面积/m²	5.57
垂尾面积/m²	2.79
起飞质量/kg	5500
下旋翼坐标/m	（0, 0, −0.89）
重心位置/m	（0, 0, 0）

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