摘要
当飞行控制系统操纵面发生卡死或控制效率损伤故障时,采用自适应滑模控制方法进行容错跟踪飞行控制律的设计。采用单位向量法进行滑模控制器的设计,利用李雅普诺夫理论和Barbalat引理设计自适应滑模调节规律,同时能够保证闭环系统的渐近稳定性。利用某型飞机线性化模型进行仿真,结果表明,带有自适应调节规律的滑模控制方法不仅适合于正常情况下飞行控制律的设计,而且对操纵面损伤和卡死故障情况具有较强的适应能力,具有很好的跟踪控制效果和强鲁棒性。
An adaptive sliding mode scheme is adopted for the design of fault- tolerant tracking control laws in the presence of stuck faults or loss- of- effectiveness faults of the flight control system. The sliding mode controller is based on the unit vector approach. The sliding mode adaptation laws are designed by using the Lyapunov theory and Barbalat＇s lemma, and the stability of the closed- loop system is guaranteed. An aircraft linear model is used for the simulation to illustrate the proposed method. The simulation results show that this method not only can be fit for the design of normal flight conditions, but also has strong fault tolerant capability of adaptation for the damage faults and stuck faults, high tracking control performances and strong robustness.
出处
《航空计算技术》
2009年第3期8-12,共5页
Aeronautical Computing Technique
关键词
容错飞行控制系统
滑模控制
自适应控制
单位向量法
fault- tolerant flight control systems
sliding mode control
adaptive control
unit vector approach
