倾转旋翼飞行器运动稳定性变化规律及其影响机理

王梓旭; 李攀; 王冰; 朱振华; 刘诚

doi:10.13224/j.cnki.jasp.20230755

倾转旋翼飞行器运动稳定性变化规律及其影响机理

doi: 10.13224/j.cnki.jasp.20230755

南京航空航天大学直升机动力学全国重点实验室，南京 210016

详细信息

作者简介:
王梓旭（1995-），男，博士生，主要从事直升机飞行力学与控制研究。E-mail：wangzixu@nuaa.edu.cn

中图分类号: V212.4
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出版历程
- 收稿日期: 2023-11-29
- 网络出版日期: 2025-05-14

Variation of tilt-rotor aircraft motion stability and its influence mechanism

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

摘要

摘要:
为摸清运动模态稳定性变化规律，以XV-15为例，深入分析了短舱倾转角、飞行速度、旋翼/机翼气动干扰等因素对运动模态特征根、特征向量、稳定性导数等影响规律及产生机理。研究表明：旋翼倾转对主要运动模态特征根、荷兰滚和纵向长周期模态特征向量产生显著影响，其背后主要影响因素是机体角速度在旋翼坐标系投影、旋翼桨盘与飞行速度夹角和旋翼桨毂中心距重心距离等因素随短舱倾角成正弦或余弦变化。在低速飞行时，旋翼/机翼间气动干扰恶化了纵向长周期模态的不稳定性，但随短舱倾转角减小和飞行速度增加，稳定性得以改善。为能倾转过渡路径选择提供指导，提出了倾转走廊内运动稳定性综合评估指标，基于等值图直观反映出运动稳定性的综合变化规律。
- 倾转旋翼飞行器 /
- 稳定性 /
- 运动模态 /
- 根轨迹 /
- 稳定性导数 /
- 特征向量
Abstract:
To elucidate the variation of stability during transition flight, the XV-15 model was taken as the research object. A comprehensive analysis was conducted to understand how factors such as nacelle angle, flight speed, and rotor/wing aerodynamic interactions, influenced the eigenvalues and eigenvectors of motion modes, and stability derivatives, along with their underlying mechanisms. The findings revealed that nacelle angle primarily influenced the eigenvalues of main motion modes and the eigenvectors of Dutch roll and phugoid modes. The underlying key factors included the body’s angular velocity projection onto the rotor axis, the angle between the rotor disc and flight velocity, and the distance from the rotor hub center to the center of gravity, which changed sine or cosine with the nacelle angle. During low-speed flight, the aerodynamic interference between the rotor and wing exacerbated the instability of phugoid mode. The instability was alleviated as the nacelle angle decreased and the flight speed increased. To facilitate the selection of transition paths for tiltable mechanisms, a comprehensive evaluation metric for assessing motion stability within tilting corridors was introduced. This metric in contour mapping visually represented the aggregate trends in motion stability, offering an intuitive understanding of its variations.
- tilt-rotor aircraft /
- stability /
- motion modes /
- root loci /
- stability derivatives /
- eigenvectors

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图 1 倾转旋翼飞行器坐标系示意图

Figure 1. Comparison of trim calculation results

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图 2 配平计算结果对比

Figure 2. Comparison of trim calculation results

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图 3 倾转过渡走廊计算结果

Figure 3. Calculation results of conversion corridor

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图 4 不同飞行状态下主要稳定性导数和运动阻尼

Figure 4. Main stability derivatives and damping in different flight conditions

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图 5 不同短舱倾转角时特征根轨迹

Figure 5. Eigenvalues loci under different nacelle angles

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图 6 不同短舱倾转角时横向静稳定性

Figure 6. Lateral static stability derivative at different nacelle angles

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图 7 不同短舱倾转角时速度静稳定性

Figure 7. Speed static stability derivative at different nacelle angles

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图 8 不同短舱倾转角时航向稳定性

Figure 8. Directional stability derivative at different nacelle angles

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图 9 不同短舱倾转角时迎角稳定性

Figure 9. Incidence stability derivative at different nacelle angles

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图 10 不同短舱倾转角下的滚转阻尼

Figure 10. Roll damping derivative at different nacelle angles

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图 11 不同短舱倾转角时俯仰阻尼

Figure 11. Pitch damping derivative at different nacelle angles

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图 12 不同短舱倾转角时偏航阻尼

Figure 12. Yaw damping derivative at different nacelle angles

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图 13 不同短舱倾转角下运动模态对应特征向量的幅值比和相位角变化

Figure 13. Amplitude and phase variations of corresponding eigenvectors of motion modes at different nacelle angles

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图 14 倾转走廊内不同前飞速度下特征根轨迹

Figure 14. Eigenvalues loci at different flight speeds within conversion corridor

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图 15 极坐标下运动模态对应的特征向量变化

Figure 15. Variation of eigenvectors corresponding to motion modes in polar coordinates

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图 16 机翼和旋翼升力比值

Figure 16. Wing and rotor lift ratio

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图 17 对比有无气动干扰下的特征根根轨迹

Figure 17. Comparison of eigenvalues loci with and without aerodynamic interactions

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图 18 纵向（横向）振荡模态在悬停及低速飞行状态下的等级评估

Figure 18. Level evaluation of longitudinal （lateral） oscillation modes in hover and low-speed

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图 19 气动干扰下纵向长周期模态特征向量的幅值变化

Figure 19. Amplitude change of eigenvector of phugoid mode with aerodynamic interactions

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图 20 对比有无气动干扰下的速度稳定性

Figure 20. Comparison of speed stability with and without aerodynamic interactions

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图 21 机翼滑流区受纵向速度扰动变化示意图

Figure 21. Diagram of wing slipstream affected by longitudinal velocity perturbation

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图 22 对比有无气动干扰下的俯仰阻尼和迎角稳定性

Figure 22. Comparison of pitch damping and incidence stability derivatives with or without aerodynamic interactions

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图 23 倾转走廊内各运动模态阻尼比及螺旋、滚转收敛模态实部根

Figure 23. Damping ratio of each motion mode and real root of spiral and roll subsidence mode within conversion corridor

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图 24 倾转走廊内各运动模态频率图

Figure 24. Frequency of each motion mode within conversation corridor

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图 25 倾转走廊内的稳定性评估指数

Figure 25. Comprehensive evaluation index of stability within conversation corridor

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