Journal of Computer Applications ›› 2013, Vol. 33 ›› Issue (03): 874-877.DOI: 10.3724/SP.J.1087.2013.00874

• Typical applications • Previous Articles     Next Articles

Reconfiguration and optimization of flight control system based on multi-model adaptive method

SHI Zhibo1*, DONG Huifen1, LI Liyi2   

  1. 1.Aeronautical Automation College, Civil Aviation University of China, Tianjin 300300, China;
    2.School of Electrical Engineering and Automation, Harbin Institute of Technology, Harbin Heilongjiang 150001,China
  • Received:2012-08-20 Revised:2012-11-08 Online:2013-03-01 Published:2013-03-01
  • Contact: Zhi-Bo SHI

基于多模型自适应的飞行控制系统重构与优化

史志波1*,董慧芬1,李立毅2   

  1. 1.中国民航大学 航空自动化学院,天津 300300;
    2.哈尔滨工业大学 电气工程及自动化学院,哈尔滨 150001
  • 通讯作者: 史志波
  • 作者简介:史志波(1980-),男,江苏徐州人,讲师,硕士,主要研究方向:飞行器动力与控制、机载电子设备维修; 董慧芬(1970-),女,河北唐山人,副教授,博士,主要研究方向:导航制导与控制、飞机电传控制系统; 李立毅(1969-),男,黑龙江鹤岗人,教授,博士,主要研究方:电机作动器及相关控制。
  • 基金资助:

    新世纪人才支持计划项目(NCET-08-0158)。

Abstract: For the reconstruction problem of the flight control law when aircraft actuator was damaged or in failure cases, a new reconfiguration scheme of flight control system was proposed based on the linear quadratic optimal control theory and multi-model adaptive method. Based on fault diagnosis and detection technology, the reference model was obtained by the Linear Quadratic Regulator (LQR). Lyapunov stability theory was applied to ensure the strictly positive real parts and global asymptotic stability of the closed-loop control system. According to the vehicle dynamics control law for fault identification and model switching, the reconfiguration and optimization of vehicle control law based on the multi-model adaption was designed. Against the typical fault conditions, the reconfiguration simulation of the flight control system was made to verify the method, and the corresponding verification results were given, which can ensure that the aircraft effective operation.

Key words: Lyapunov stability theory, fault tolerant control, reconfiguration, multi-model reference adaption, Linear Quadratic Regulator (LQR)

摘要: 对飞行器执行机构受损或失效情况下其飞行控制规律重构的问题,提出一种基于线性二次最优控制理论的多模型自适应控制重构技术方案。利用线性二次调节器获得参考模型,基于故障诊断与检测技术,运用Lyapunov稳定性理论,确保闭环控制系统的严格正实性和全局渐进稳定性。根据飞行器的动力学控制规律,进行故障辨识和模型切换,实现故障状态下飞行控制规律的重构与优化设计。针对典型故障情况进行飞行器控制重构仿真验证,结果表明系统能够在舵面部分失效下完成控制重构,保证有效飞行器运行控制。

关键词: Lyapunov稳定性理论, 容错控制, 重构, 多模型参考自适应, 线性二次调节器

CLC Number: