MIMO变结构飞行重构控制系统设计

苏媛; 王柯

MIMO变结构飞行重构控制系统设计

苏媛,
王柯

北京航空航天大学航空科学与工程学院, 北京 100191

计量
- 文章访问数: 1524
- HTML浏览量: 86
- PDF量: 503
- 被引次数: 0
出版历程
- 收稿日期: 2011-05-19
- 修回日期: 2011-09-05
- 刊出日期: 2012-04-28

MIMO reconfigurable flight control system design based on sliding mode control

SU Yuan,
WANG Ke

School of Aeronautical Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 基于滑模变结构控制,提出一种MIMO(multiple input multiple output)的飞行重构控制系统的频域设计方法.将滑模变结构控制与飞行重构控制相结合,解决了飞行重构控制技术中故障检测和系统参数辨识的问题.引入渐近观测器和hedge模型增加重构控制系统对衍生未建模动态的鲁棒性;引入作动器模型、输出饱和限制和驾驶员模型,使变结构重构控制系统设计方法变得更为有效和实用;以某型飞机的横航向飞行控制系统为例,进行设计模拟.结果表明:在飞机气动参数大幅突变和操纵面严重受损的情况下,飞机仍能保持良好的性能.
- 滑模变结构控制 /
- 渐近观测器 /
- hedge模型 /
- MIMO(multiple input multiple output)重构控制 /
- 作动器输出饱和
Abstract: A frequency domain design method based on sliding mode control for MIMO(multiple input multiple output) reconfigurable flight control system was presented.Combining the sliding mode control with the flight reconfigurable control solved the problems of fault detection and system parameter identification in flight reconfigurable control system.Raised the robustness of the control system to parasitic dynamics and unmodeled dynamics through the introduction of asymptotic observer and hedge model;made the design method become more effective and practical through the introduction of actuator model,output saturation and pilot model;the proposed scheme was applied to the design of lateral motion of an aircraft.The results show that good dynamic performance in the condition of significant changes of aerodynamic parameters and control surface failures.
- sliding mode control /
- asymptotic observer /
- hedge model /
- MIMO(multiple input multiple output) reconfigurable control /
- actuator output saturation

HTML

参考文献(12)

[1]	张明涛,安锦文,李中健.重构飞行控制技术研究综述[J].飞行力学,2009,27(2):7-10. ZHANG Mingtao,AN Jinwen,LI Zhongjian.Survey of reconfigurable flight control[J].Flight Dynamics,2009,27(2):7-10.(in Chinense)
[2]	高为炳.变结构控制理论基础[M].北京:中国科学技术出版社,1990.
[3]	姚琼荟,黄继起,吴汉松.变结构控制系统[M].重庆:重庆出版社,1997.
[4]	Wells S R,Hess R A.Multi-input/multi-output sliding mode control for a tailless fighter aircraft[J].Journal of Guidance,Control,and Dynamics,2003,26(3):463-173.
[5]	David K Y,Vadim I U.A control engineer’s guide to sliding mode control[J].IEEE Transactions on Control Systems Technology,1999,7(3):328-342.
[6]	Ronald A H,Gianluca C.An example of flight control system design for inherent damage tolerance.AIAA-2008-7432,2008.
[7]	Anthony B P,Marc L S.A closed-loop comparison of control allocation methods.AIAA-2000-4538,2000.
[8]	Snell S A.Decoupling control design with application to flight[J].Journal of Guidance,Navigation,and Control,1997,21(6):1141-1148.
[9]	Shtessel Y B,Buffington J M,Banda S S.Multiple timescale flight control using reconfigurable sliding modes[J].Journal of Guidance,Control,and Dynamics,1999,22(6):873-883.
[10]	Seshagirl S,Promtun E.Sliding mode control of F-16 longitudinal dynamics //Proceedings of American Control Conference.Seattle,WA:IEEE,2008,1770-1775.
[11]	胡兆丰.人机系统和飞行质量[M].北京:北京航空航天大学出版社,1994.
[12]	Hess R A.United theory for aircraft handling qualities and adverse aircraft:pilot coupling[J].Journal of Guidance,Control,and Dynamics,1997,20(6):1141-1148.