一种新的气动伺服弹性失稳模式的机理分析

姜宇; 杨超; 吴志刚

doi:10.13700/j.bh.1001-5965.2021.0571

一种新的气动伺服弹性失稳模式的机理分析

doi: 10.13700/j.bh.1001-5965.2021.0571

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

通讯作者:
吴志刚, E-mail: wuzhigang@buaa.edu.cn

中图分类号: V211.47
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- 文章访问数: 241
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- PDF下载量: 21
- 被引次数: 0
出版历程
- 收稿日期: 2021-09-26
- 录用日期: 2021-12-19
- 网络出版日期: 2022-01-05
- 整期出版日期: 2022-07-20

Mechanism analysis of a new aeroservoelastic instability mode

School of Aeronautic Science and Engineering, Beihang University, Beijing 100083, China

More Information

Corresponding author: WU Zhigang, E-mail: wuzhigang@buaa.edu.cn

摘要

摘要:
某超声速导弹在飞行试验中发生了气动伺服弹性失稳导致的结构解体，通过对飞行试验数据的分析发现，气动伺服弹性失稳的振动频率高于弹体一阶弯曲模态频率，对导弹进行气动伺服弹性稳定性频域分析，并未发现该频率段发生气动伺服弹性失稳。针对该问题，建立了一种可以考虑数字式飞控系统采样过程影响的气动伺服弹性稳定性仿真分析方法，并对该导弹进行了建模分析，数值结果复现了该导弹的失稳现象。讨论了这一新型失稳现象发生的原因，包括连续结构滤波器离散化带来的移频现象和频率混叠问题。给出了对应的改进措施和相关的结论。
- 气动伺服弹性 /
- 离散化 /
- 结构滤波器 /
- 采样率 /
- 频率混叠
Abstract:
Recently, the structure of a supersonic missile disintegrated due to aeroservoelastic instability in flight test. Through the analysis of flight test data, it is found that the vibration frequency of aerodynamic servo elastic instability is higher than the first-order bending elastic modal frequency of missile body. Based on the frequency domain analysis of aerodynamic servo elastic stability of missile, it is not found that aeroservoelastic instability occurs in this frequency band. To solve this problem, a simulation analysis method of aeroservoelastic stability considering the influence of sampling process of digital flight control system is established, and the missile is modeled and analyzed. The numerical results reproduce the instability phenomenon of the missile. The causes of this new instability phenomenon are discussed, including the frequency shift phenomenon caused by the discretization of continuous structure filter and frequency aliasing. Finally, the corresponding improvement measures and relevant conclusions are given.
- aeroservoelastic /
- discretization /
- structure filter /
- sampling rate /
- frequency aliasing

HTML全文

图 1 弹性飞行器ASE系统框图

Figure 1. Block diagram of flexible flight vehicle aeroservoelasticity system

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图 2 飞控系统框图

Figure 2. Block diagram of flight control system

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图 3 有无滤波器导弹的开环传递函数曲线

Figure 3. Open-loop transfer function curves of missile with and without filter

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图 4 有数字式飞控系统的飞行器ASE系统开环Simulink模型

Figure 4. Simulink model of aircraft ASE open-loop system with digital flight control system

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图 5 有数字式飞控系统的飞行器ASE系统闭环Simulink模型

Figure 5. Simulink model of aircraft ASE close-loop system with digital flight control system

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图 6 无滤波器开环仿真结果(采样率400 Hz)

Figure 6. Open-loop simulation results without filter (sampling rate 400 Hz)

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图 7 无滤波器开环传递函数曲线(采样率400 Hz)

Figure 7. Open-loop transfer function curves without filter (sampling rate 400 Hz)

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图 8 有滤波器开环仿真结果(采样率400 Hz)

Figure 8. Open-loop simulation results with filter (sampling rate 400 Hz)

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图 9 有滤波器开环传递函数曲线(采样率400 Hz)

Figure 9. Open-loop transfer function curves with filter (sampling rate 400 Hz)

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图 10 有滤波器开环仿真结果(采样率200 Hz)

Figure 10. Open-loop simulation results with filter (sampling rate 200 Hz)

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图 11 有滤波器开环传递函数曲线(采样率200 Hz)

Figure 11. Open-loop transfer function curves with filter (sampling rate 200 Hz)

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图 12 系统闭环时域响应(采样率200 Hz)

Figure 12. Closed-loop time domain response of system (sampling rate 200 Hz)

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图 13 不同采样率离散化的结构滤波器频响曲线

Figure 13. Frequency response curves of discrete structured filters with different sampling rates

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图 14 系统辨识开环传递函数曲线(采样率200 Hz)

Figure 14. Open-loop transfer function curves for system identification(sampling rate 200 Hz)

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