基于主动阻尼装置的机翼悬臂梁振动控制研究

朱皓哲; 何立东; 秦庆旺

doi:10.13224/j.cnki.jasp.20240412

基于主动阻尼装置的机翼悬臂梁振动控制研究

doi: 10.13224/j.cnki.jasp.20240412

北京化工大学化工安全教育部工程研究中心，北京 100029

基金项目: 中央高校基本科研业务费专项资金（JD2423）

详细信息

作者简介:
朱皓哲（1995-），男，博士生，研究方向为振动主动控制技术。E-mail：374208304@qq.com

通讯作者:
何立东（1963-），男，教授，博士，研究方向振动控制技术。E-mail：1963he@163.com

中图分类号: V22；TH113
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出版历程
- 收稿日期: 2024-06-26
- 网络出版日期: 2026-01-28

Study on vibration control of wing cantilever beam structure based on active damping device

Ministry of Chemical Safety Education Engineering Research Centre，Beijing University of Chemical Technology，Beijing 100029，China

摘要

摘要:
针对飞行器机翼的受迫激振以及共振问题，提出了一种采用主动阻尼装置（active damping device，ADD）对机翼悬臂梁模型施加作动力，抑制机翼受迫激振以及降低共振的方法，对机翼受迫振动抑制进行了理论推导、仿真分析与实验研究。首先，建立了ADD的作动器动力学模型，分析了ADD控制机翼受迫振动的有效性；之后使用数值模拟对机翼悬臂梁模型进行了模态分析、受力分析和谐响应分析，优化了ADD输出的作动力；最后搭建了基于ADD的机翼激振主动抑制实验台，对比了施加ADD控制前后机翼悬臂梁对模态振型和在宽频带激振力下的振动控制效果。结果表明：施加ADD控制能够有效改善机翼受力状态，大幅降低其应力与变形量；ADD可以显著降低机翼共振幅值，最高降幅74.22%；在30～120 Hz宽频带内，有效控制机翼振动，最高降幅61.8%。
- 主动阻尼装置 /
- 振动主动控制 /
- 飞行器机翼减振 /
- 作动器 /
- 力学仿真
Abstract:
In view of the problem of forced excitation and resonance of aircraft wings, a method was proposed to suppress the forced excitation and reduce the resonance of wings by applying the actuating force to the wing cantilever beam model using an active damping device (ADD), and theoretical derivation, simulation analysis, and experimental study were carried out for the suppression of forced vibration of the wings. Firstly, the actuator dynamics model of ADD was established to analyze the effectiveness of ADD in controlling the forced vibration of the wing; then, the modal analysis, force analysis and harmonic response analysis of the wing cantilever beam model were carried out using numerical simulation to optimize the actuator force output from the ADD; finally, the active suppression experimental bench of wing excitation based on ADD was constructed, and the effects of the control of modal vibration and vibration under wide-band excitation force of the wing cantilever beam before and after application of the ADD control were compared. The results showed that applying ADD control can effectively improve the wing force state and significantly reduce its stress and deformation; ADD significantly reduced the resonance amplitude of the wing, with a maximum reduction of up to 74.22%; within the 30—120 Hz frequency band, it effectively controlled wing vibrations, with a maximum reduction of up to 61.8%.
- active damping device /
- active control of vibration /
- aircraft wing vibration reduction /
- actuator /
- mechanical simulation

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图 1 ADD的控制系统模型

Figure 1. Control system model of ADD

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图 2 惯性作动器的动力学简化模型

Figure 2. Simplified model of the dynamics of inertial actuator

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图 3 ADD组成图

Figure 3. ADD Composition diagram

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图 4 ADD作动力输出力常数的幅频特性曲线

Figure 4. Amplitude-frequency characteristic curve of ADD as actuation force output constant

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图 5 ADD控制系统简化模型

Figure 5. Simplified model of the ADD control system

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图 6 ADD控制系统方框图

Figure 6. Block diagram of the ADD control system

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图 7 ADD对被控系统的控制效果图

Figure 7. Diagram of the control effect of ADD on the controlled system

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图 8 机翼悬臂梁模型前6阶固有频率和模态振型

Figure 8. First-sixth order intrinsic frequency and mode shapes of a wing cantilever beam model

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图 9 模型在ADD不同输出力下的应力与变形

Figure 9. Stress and deformation of the model under different output forces of ADD

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图 10 ADD控制前后机翼应力和变形变化对比

Figure 10. Comparison of wing stress and deformation changes before and after ADD control

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图 11 机翼模型谐响应分析曲线

Figure 11. Harmonic response analysis curve of the wing model

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图 12 机翼激振主动抑制实验原理图和实验台

Figure 12. Schematic diagram and experimental bench for active suppression experiment of wing excitation

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图 13 ADD控制第4阶固有频率（82 Hz）共振前后的频谱与时域图

Figure 13. Spectrum and time-domain plots before and after resonance at the fourth order intrinsic frequency （82 Hz） of ADD control

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图 14 ADD控制机翼在30 Hz和120 Hz激振力作用下的频谱与时域图

Figure 14. Spectrum and time-domain plots of ADD-controlled wing with 30 Hz and 120 Hz excitation forces

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表 1 ADD的主要参数

Table 1. Main parameters of ADD

参数	数值
惯性质量/kg	0.2
弹簧刚度/（N/m）	6150
阻尼比	0.15
输出力常数/（N/V）	3
控制电压峰值/V	±5
最大行程/mm	±2

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表 2 不同固有频率激振下机翼振动控制情况对比

Table 2. Comparison of wing vibration control under different intrinsic frequency excitations

阶次	固有频率/Hz	原始振幅/（m/s²）	ADD控制后振幅/（m/s²）	振动降幅/%
第1阶	5	6.27	4.25	32.22
第2阶	25	16.0	5.23	67.31
第3阶	71	72.14	67.84	6.79
第4阶	82	36.03	9.29	74.22
第5阶	85	32.5	24.23	25.45
第6阶	140	38.5	33.8	12.21

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表 3 宽频带激振力下机翼振动控制情况对比

Table 3. Comparison of wing vibration control under broadband excitation force

激振力频率/Hz	原始振幅/（m/s²）	ADD控制后振幅/（m/s²）	振动降幅/%
30	29.08	11.11	61.8
40	32.91	19.99	39.25
50	39.55	34.71	12.24
60	43.61	32.94	24.47
70	37.04	22.8	38.44
80	35.89	18.6	35.37
90	39.86	20.88	47.62
100	44.14	23.76	46.17
110	49.74	27.52	44.67
120	69.26	52.88	23.65

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