| 基于SMOD的滑模控制器设计 |
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| 引用本文： | 顾文锦,范作娥,毕兰金,王晓杰.基于SMOD的滑模控制器设计[J].飞行力学,2010,28(1). |
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| 作者姓名： | 顾文锦 范作娥 毕兰金 王晓杰 |
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| 作者单位： | 1. 海军航空工程学院控制工程系,山东,烟台,264001
2. 中国人民解放军61267部队52分队,北京,101114 |
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| 基金项目： | 总装武器装备重点创新基金资助(6140511) |
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| 摘 要： | 针对高性能飞航导弹过载控制系统,从便于工程实现的角度出发,应用滑模观测/区分器(SMOD),通过角速度对角加速度进行估计,然后利用角速度和角加速度与过载的一阶、二阶导数间的近似关系,设计了一种滑模变结构控制律,滑模面由过载误差及误差的一阶、二阶导数组成。仿真结果验证了方法的正确性和有效性。
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| 关 键 词： | 飞行器控制 滑模控制 滑模观测/区分器 |
Sliding mode controller design based on SMOD |
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| GU Wen-jin,FAN Zuo-e,BI Lan-jin,WANG Xiao-jie.Sliding mode controller design based on SMOD[J].Flight Dynamics,2010,28(1). |
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| Authors: | GU Wen-jin FAN Zuo-e BI Lan-jin WANG Xiao-jie |
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| Institution: | 1.Department of Control Engineering;Naval Aeronautical and Astronautical University;Yantai 264001;China;2.The 52th Element;The 61267 Unit of PLA;Beijing 101114;China |
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| Abstract: | For an agile winged missile control system,using the sliding mode observer/differentiator(SMOD) to estimate the pitch acceleration by pitch rate,a variable structure control law is designed in the point of view of engineering application,and the sliding mode surface consists of overload signals error and its first-order and second-order derivatives,which are further replaced by pitch rate and pitch acceleration respectively.Simulation results show the validity and effectiveness of the proposed method. |
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| Keywords: | vehicle control sliding mode control sliding mode observer/differentiator |
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