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

doi:10.13700/j.bh.1001-5965.2016.0453

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

宋晨^{1, 2, ,},
王诗其²,
杨超²

1.
北京航空航天大学无人系统研究院, 北京 100083
2.
北京航空航天大学航空科学与工程学院, 北京 100083

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
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- 被引次数: 0
出版历程
- 收稿日期: 2016-05-26
- 录用日期: 2016-06-20
- 网络出版日期: 2017-06-20

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

SONG Chen^{1, 2
, ,},
WANG Shiqi²,
YANG Chao²

1.
Unmanned System Research Institute, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

Funds:

National Natural Science Foundation of China 11402013

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

More Information

Corresponding author: SONG Chen, E-mail: songchen@buaa.edu.cn

摘要

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。
- 气动弹性 /
- 颤振主动抑制(AFS) /
- 线性二次型最优控制 /
- 滑模控制 /
- 滑模观测器
Abstract:
Active flutter suppression (AFS) is a worldwide well proposed solution for the flutter of aircraft, which plays an important role in modern aircraft design. Many studies have shed some light on the AFS usage of sliding mode control strategy and the sliding mode observer, acting on two-dimensional wings. Herein, a wind-tunnel model of an actual wing which has two tailing-edge flaps is selected to examine the effectiveness of a low-order sliding mode observer which will be applied to AFS design of 3D wing. This observer has superior performance and distinctive features. However, the traditional complicated design routine limits its application to high-order objects. A new simplified design procedure is proposed by using a gain matrix of the Kalman filter in linear quadratic Gaussian (LQG) method. Then, considering the physical property of aeroelasticity, the new method can be put into practice theoretically. Comparison analyses are given. The results indicate that the sliding mode observer method has a better noise resistance ability than the LQG method.
- aeroelasticity /
- active flutter suppression(AFS) /
- linear quadratic optimal control /
- sliding mode control /
- sliding mode observer

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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

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图 2 LQG方法的估计器实现框图

Figure 2. Realization block diagram of estimator of LQG method

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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)

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图 4 舵偏指令的三角脉冲激励

Figure 4. Flap deflection command excited by delta impulse

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图 5 无控状态开环系统输出响应

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

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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)

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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

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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)

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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)

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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

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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

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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)

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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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参考文献(18)

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