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基于滑模观测器的机翼颤振主动抑制设计

宋晨 王诗其 杨超

宋晨, 王诗其, 杨超等 . 基于滑模观测器的机翼颤振主动抑制设计[J]. 北京航空航天大学学报, 2017, 43(6): 1098-1104. doi: 10.13700/j.bh.1001-5965.2016.0453
引用本文: 宋晨, 王诗其, 杨超等 . 基于滑模观测器的机翼颤振主动抑制设计[J]. 北京航空航天大学学报, 2017, 43(6): 1098-1104. doi: 10.13700/j.bh.1001-5965.2016.0453
SONG Chen, WANG Shiqi, YANG Chaoet al. Active flutter suppression design of a wing based on sliding mode observer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(6): 1098-1104. doi: 10.13700/j.bh.1001-5965.2016.0453(in Chinese)
Citation: SONG Chen, WANG Shiqi, YANG Chaoet al. Active flutter suppression design of a wing based on sliding mode observer[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(6): 1098-1104. doi: 10.13700/j.bh.1001-5965.2016.0453(in Chinese)

基于滑模观测器的机翼颤振主动抑制设计

doi: 10.13700/j.bh.1001-5965.2016.0453
基金项目: 

国家自然科学基金 11402013

中央高校基本科研业务费专项资金 YWF-14-WRJS-004

详细信息
    作者简介:

    宋晨, 男, 博士, 讲师。主要研究方向:气动弹性与主动控制、结构强度

    通讯作者:

    宋晨, E-mail:songchen@buaa.edu.cn

  • 中图分类号: V215.3

Active flutter suppression design of a wing based on sliding mode observer

Funds: 

National Natural Science Foundation of China 11402013

the Fundamental Research Funds for the Central Universities YWF-14-WRJS-004

More Information
  • 摘要:

    颤振主动抑制(AFS)是国际上普遍推崇的颤振问题解决方案,对现代飞行器设计具有重要意义。基于国际上滑模观测器的二维机翼AFS应用,以双后缘控制面真实机翼模型为对象,发展一种低阶滑模观测器的三维机翼AFS设计方法。该观测器性能优越、特点鲜明,但传统的设计流程繁琐,限制了其在高阶模型对象上的使用。本文借助线性二次型高斯(LQG)方法中的最优滤波器增益矩阵,提出一种简化的滑模观测器设计流程。结合气动弹性物理背景,使本文方法理论上能够应用于实践。算例对比分析结果表明,本文方法比LQG方法具有更好的抵抗噪声能力。

     

  • 图 1  某机翼风洞试验模型结构示意图

    Figure 1.  Schematic of wind-tunnel test model of a wing

    图 2  LQG方法的估计器实现框图

    Figure 2.  Realization block diagram of estimator of LQG method

    图 3  滑模观测器方法的估计器实现框图(半输出反馈)

    Figure 3.  Realization block diagram of estimator of sliding mode observer (half output feedback)

    图 4  舵偏指令的三角脉冲激励

    Figure 4.  Flap deflection command excited by delta impulse

    图 5  无控状态开环系统输出响应

    Figure 5.  Open-loop output responses of system without control

    图 6  有控状态闭环系统输出响应(1#传感器)

    Figure 6.  Closed-loop output responses of system with control (Sensor No.1)

    图 7  有控状态的舵偏指令时间历程

    Figure 7.  Time histories of flap deflection command with control

    图 8  输入指令有噪声干扰时的闭环响应(1#传感器)

    Figure 8.  Closed-loop responses of system with noise disturbance in input commands (Sensor No.1)

    图 9  输入指令有噪声干扰时的舵偏指令时间历程(舵面Ⅱ)

    Figure 9.  Time histories of flap deflection command with noise disturbance in input commands (FlapⅡ)

    图 10  各阶状态变量对滑模观测器输入指令贡献量

    Figure 10.  Contributions of different-order state variables to input commands of sliding mode observer

    图 11  滑模观测器方法的全输出反馈实现

    Figure 11.  Full output feedback realization of sliding mode observer

    图 12  全输出反馈控制下的输入、输出均有噪声时域响应对比(1#传感器)

    Figure 12.  Comparison of time domain responses of system with noise disturbance in both inputs and outputs under full output feedback control (Sensor No.1)

    表  1  动力学模型模态列表(翼根固支约束)

    Table  1.   List of vibration modes of dynamic model (cantilever restriction)

    序号 模态名称 模态频率/Hz 试验值/Hz
    1 一阶弯曲 1.61
    2 二阶弯曲 6.21 6.19
    3 一阶扭转 14.75 14.85
    4 三阶弯曲 16.48 16.65
    5 四阶弯曲 27.60 27.91
    6 二阶扭转 33.71
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出版历程
  • 收稿日期:  2016-05-26
  • 录用日期:  2016-06-20
  • 刊出日期:  2017-06-20

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