基于自抗扰控制方法的自动着陆飞行控制律设计  

Design for Automatic Landing Flight Control Law Based on Active Disturbance Rejection Control Method

作　　者：张祥 李广文[1] 曹睿婷 薛广龙[3] ZHANG Xiang;LI Guangwen;CAO Ruiting;XUE Guanglong(School of Automation,Northwestern Polytechnical University,Xi’an 710072,China;Xi’an Flight Automatic Control Research Institute,Xi’an 710065,China;China National Aeronautical Radio Electronics Research Institute,Shanghai 200233,China)

机构地区：[1]西北工业大学自动化学院,西安710072 [2]西安飞行自动控制研究所,西安710065 [3]中国航空无线电电子研究所,上海200233

出　　处：《弹箭与制导学报》2020年第5期98-104,共7页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：工业和信息化部民机专项(MJ-2016-S-41;MJ-2017-S-44)资助。

摘　　要：为解决强干扰情况下飞机着陆控制的抗扰动问题,引入自抗扰控制方法来设计飞机姿态和自动油门控制律。针对自抗扰控制算法中不光滑的非线性fal函数在分段点处引发控制器震荡问题,利用连续可导条件重新构造非线性函数提高控制器性能。以某运输机为对象,在紊流干扰和参数摄动条件下进行自动着陆仿真。仿真结果表明,基于自抗扰的自动着陆控制律具有良好的鲁棒性。In order to solve the anti-disturbance problem of aircraft landing control under strong disturbance, a design method of attitude and automatic throttle control law based on active disturbance rejection control method was given in this paper. In the active disturbance rejection control theory, if the nonlinear fal function is not smooth, the controller oscillation problem is induced at the subsection point, in this paper, the nonlinear function is reconstructed by using the continuous and derivable condition, by this method, the controller performance is improved. Taking a transport aircraft as an object, the automatic landing simulation is carried out under the condition of turbulence disturbance and parameter perturbation. The simulation results show that automatic landing control law designed by the active disturbance rejection method has good robustness.

关 键 词：姿态控制 自动油门 自抗扰控制 鲁棒性 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]