MIMO变结构飞行重构控制系统设计  

MIMO reconfigurable flight control system design based on sliding mode control

作　　者：苏媛[1] 王柯[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《航空动力学报》2012年第4期913-919,共7页Journal of Aerospace Power

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.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.

关 键 词：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 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]