| 引用本文: | 常雨芳,张闯闯,高鹏,严怀成,黄文聪.考虑非匹配扰动的飞机EMA伺服系统的改进滑模复合控制[J].控制理论与应用,2025,42(7):1407~1416.[点击复制] |
| CHANG Yu-fang,ZHANG Chuang-chuang,GAO Peng,YAN Huai-cheng,HUANG Wen-cong.Improved sliding mode compound control of aircraft EMA servo system considering non-matching disturbances[J].Control Theory & Applications,2025,42(7):1407~1416.[点击复制] |
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| 考虑非匹配扰动的飞机EMA伺服系统的改进滑模复合控制 |
| Improved sliding mode compound control of aircraft EMA servo system considering non-matching disturbances |
| 摘要点击 2590 全文点击 246 投稿时间：2023-05-26 修订日期：2025-05-04 |
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| DOI编号 10.7641/CTA.2024.30362 |
| 2025,42(7):1407-1416 |
| 中文关键词 机电作动器 非匹配扰动 级联扩张状态观测器 非奇异全局终端滑模 |
| 英文关键词 electro-mechanical actuator non-matching disturbances cascaded extended state observers: non-singular global terminal sliding mode |
| 基金项目 国家自然科学基金项目(61903129)资助. |
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| 中文摘要 |
| 飞机机电作动器(EMA)伺服系统中普遍存在的非匹配扰动会降低系统状态的跟踪精度. 针对此问题, 本文
提出了一种基于级联扩张状态观测器的改进非奇异全局终端滑模和非匹配扰动估计反馈补偿的复合控制方法. 首
先, 在对非匹配扰动进行精确定义的基础上建立了系统的优化数学模型, 设计了级联扩张状态观测器对非匹配和匹
配扰动进行实时估计; 其次, 基于扰动估计信息设计了改进非奇异全局终端滑模面和控制律, 使系统制动压力可以
精确跟踪其期望输出值; 再次, 通过非匹配扰动估计反馈补偿抵消了系统转子角速度输出的跟踪误差, 抑制了非匹
配扰动对系统状态的负面影响; 最后, 在3类期望输出制动压力下进行了仿真分析, 验证了本文提出的飞机EMA伺
服系统复合控制方法能够有效处理非匹配扰动的影响, 使系统状态获得更快的收敛速度以及更高的跟踪精度. |
| 英文摘要 |
| Aiming at the problem of non-matching disturbances common in the aircraft electro-mechanical actuator
(EMA) servo system, which will reduce the tracking accuracy of the system state, a composite control method for improved
non-singular global terminal sliding mode and non-matching disturbances estimation feedback compensation based on
cascaded extended state observers is proposed. Firstly, an optimization mathematical model of the system was established
based on the precise definition of non-matching disturbances, and a cascade extended state observer is designed to estimate
non-matching and matching disturbances in real-time. Secondly, an improved non-singular global terminal sliding surface
and control law are designed based on the disturbance estimation information so that the system braking pressure can
be accurately tracked. Its expected output value. Thirdly, through the non-matching disturbance estimation feedback
compensation, the tracking error of the system rotor angular velocity output is offset, and the negative impact of the nonmatching disturbance on the system state is suppressed; Finally, through simulation analysis under three types of expected
output braking pressures, it is verified that the composite control method of the aircraft EMA servo system proposed in
this article can effectively deal with the influence of non-matching disturbances, allowing the system state to achieve faster
convergence speed and higher tracking accuracy. |
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