北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (6): 1263-1270.doi: 10.13700/j.bh.1001-5965.2015.0732

• 论文 • 上一篇    下一篇

二元机翼颤振的指令滤波反推自适应约束控制

苟义勇, 李洪波, 董新民, 石超, 孙超姣   

  1. 空军工程大学 航空航天工程学院, 西安 710038
  • 收稿日期:2015-11-09 出版日期:2016-06-20 发布日期:2016-07-06
  • 通讯作者: 董新民,Tel.:029-84787400-203 E-mail:dongxinmin@139.com E-mail:dongxinmin@139.com
  • 作者简介:苟义勇 男,硕士研究生。主要研究方向:非线性气动弹性分析与控制。Tel.:029-84787400-203 E-mail:gouyiyong@139.com;李洪波 男,博士,讲师。主要研究方向:非线性气动弹性分析与控制。Tel.:13379074349 E-mail:lhbfirst-81@163.com;董新民 男,博士,教授,博士生导师。主要研究方向:飞行控制。Tel.:029-84787400-203 E-mail:dongxinmin@139.com
  • 基金资助:
    国家自然科学基金(61473307,61304120);航空科学基金(20155896026)

Active flutter suppression for two-dimensional wing based on command filtered adaptive backstepping constrained control

GOU Yiyong, LI Hongbo, DONG Xinmin, SHI Chao, SUN Chaojiao   

  1. Aeronautics and Astronautics Engineering College, Air Force Engineering University, Xi'an 710038, China
  • Received:2015-11-09 Online:2016-06-20 Published:2016-07-06

摘要: 为有效抑制二元机翼颤振现象,设计了一个指令滤波反推自适应约束控制器。考虑二元机翼气动弹性系统存在多项式结构非线性特性以及系统不确定的情况,针对二元机翼控制面偏转角度限制以及系统外部阵风扰动等问题,将前/后缘双控制面布局的二元机翼动态方程以状态空间形式描述,采用反推控制技术进行控制律整体设计,通过指令滤波环节对虚拟/实际控制信号进行幅值限制,并将滤波前后的信号差引入到自适应约束控制律设计过程中。仿真结果表明,在一定来流速度下,开环系统出现极限环颤振现象,闭环控制系统能快速达到稳定状态,二元机翼颤振现象得到有效抑制。

关键词: 二元机翼, 颤振, 指令滤波, 反推控制, 自适应约束控制

Abstract: A command filtered adaptive backstepping constrained controller is designed to achieve active flutter suppression of a two-dimensional wing. In the presence of constraints on the control surface deflection and external gust load, the dynamic equations of a two-dimensional wing with leading-and trailing-edge control surfaces are described in state space considering polynomials structural nonlinearity and system uncertainties. The whole closed-loop control law is constructed by backstepping control technique. The magnitude of the virtual/actual control input can be bounded by command filter, and the error signal produced by command filter is introduced into the process of designing adaptive constrained control law. The simulation results show that the open-loop system exhibits limit-cycle oscillations at a critical freestream velocity, and the closed-loop system reaches to stability quickly. Active flutter suppression is accomplished effectively.

Key words: two-dimensional wing, flutter, command filter, backstepping control, adaptive constrained control

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