北京航空航天大学学报 ›› 2017, Vol. 43 ›› Issue (6): 1098-1104.doi: 10.13700/j.bh.1001-5965.2016.0453

• 论文 • 上一篇    下一篇

基于滑模观测器的机翼颤振主动抑制设计

宋晨1,2, 王诗其2, 杨超2   

  1. 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
  • 收稿日期:2016-05-26 出版日期:2017-06-20 发布日期:2016-10-17
  • 通讯作者: 宋晨,E-mail:songchen@buaa.edu.cn E-mail:songchen@buaa.edu.cn
  • 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。
  • 基金资助:
    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)

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

SONG Chen1,2, WANG Shiqi2, YANG Chao2   

  1. 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
  • Received:2016-05-26 Online:2017-06-20 Published:2016-10-17
  • Supported by:
    National Natural Science Foundation of China (11402013); the Fundamental Research Funds for the Central Universities (YWF-14-WRJS-004)

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。

关键词: 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.

Key words: aeroelasticity, active flutter suppression(AFS), linear quadratic optimal control, sliding mode control, sliding mode observer

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