基于新型趋近律的AABS积分滑模控制系统设计  

Design of aircraft anti-skid braking system integral sliding mode control system based on novel reaching law

作　　者：徐萌 李艳 高洁 徐海 高冰 XU Meng;LI Yan;GAO Jie;XU Hai;GAO Bing(School of Electronic Information and Automation,Civil Aviation University of China,Tianjin 300300,China;Key Laboratory of Technology and Equipment of Tianjin Urban Air Transportation System,Tianjin 300300,China;Shenyang Aircraft Airworthiness Certification Center of CAAC,Shenyang 110043,China;Engineering Techniques Training Center,Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学电子信息与自动化学院,天津300300 [2]天津市城市空中交通系统技术与装备重点实验室,天津300300 [3]中国民用航空沈阳航空器适航审定中心,沈阳110043 [4]中国民航大学工程技术训练中心,天津300300

出　　处：《北京航空航天大学学报》2025年第4期1107-1116,共10页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(51707195,62173331);中央高校基本科研业务费专项资金(3122023016)。

摘　　要：针对飞机防滑刹车系统(AABS)具有强时变性、强不可测性、内外干扰因素多的特点,提出一种变指数分数阶指数趋近律的AABS积分滑模控制(ISMC)方法。建立飞机着陆滑跑时系统的动力学模型;以提高系统快速性和鲁棒性为目标,引入变结构控制实现最佳滑移率和最大结合系数的跟踪问题;改进分数阶指数趋近律的积分滑模控制律,在抑制抖振现象的同时加快跟踪到最佳滑移率的速度;设计滑模观测器观测飞机速度,以减少存在的内外界非线性干扰;利用MATLAB仿真平台,对所提方法的可行性及有效性进行仿真验证。仿真结果表明:所设计的变指数分数阶指数趋近律的积分滑模控制器整体控制效果优于传统线性滑模控制器,滑模观测器可以精准估计飞机速度,所提方法提高了系统整体设计的鲁棒性,缩短了刹车时间和刹车距离,控制效果良好。Aircraft anti-skid braking system(AABS)has the characteristics of strong time variability,strong unpredictability,and many internal and external interference factors.Therefore,an integral sliding mode control(ISMC)method of AABS with variable exponential fractional order exponential reaching law was proposed.Firstly,the dynamics model of the aircraft landing system was established.Secondly,in order to improve the rapidity and robustness of the system,a variable structure control method was introduced to realize the tracking of optimal slip rate and optimal binding coefficient.Then,by improving the ISMC law of the exponential fractional order reaching law,the chattering phenomenon was suppressed,and the tracking speed to the optimal slip rate was accelerated.In addition,a sliding mode observer was designed to observe the aircraft speed to reduce the internal and external nonlinear interference.Finally,the feasibility and effectiveness of the algorithm were verified by the MATLAB simulation platform.The simulation results show that the overall control effect of the designed integral sliding mode controller with variable exponential fractional order reaching law is better than the traditional linear sliding mode controller,and the sliding mode observer can accurately estimate the aircraft speed.The method improves the robustness of the overall system design and shortens the braking time and braking distance,and the control effect is great.

关 键 词：飞机防滑刹车系统 分数阶 积分滑模控制 滑移率 鲁棒性 

分 类 号：V227.5[航空宇航科学与技术—飞行器设计]