| 空射飞航导弹姿态控制的一种自适应方法 |
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| 引用本文： | 韩艳铧,黄攀峰,孟中杰. 空射飞航导弹姿态控制的一种自适应方法[J]. 弹箭与制导学报, 2009, 29(5) |
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| 作者姓名： | 韩艳铧 黄攀峰 孟中杰 |
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| 作者单位： | 1. 南京航空航天大学航天学院,南京,210016
2. 西北工业大学航天学院,西安,710072 |
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| 摘 要： | 为解决空射飞航导弹气动力矩导数不确定条件下姿态控制问题,基于动态逆和非线性系统无源性稳定理论设计了一种姿态自适应控制器.该控制器包括控制律和参数估计器两部分.控制律根据估计器提供的对象参数估值在线调整控制参数.采用李亚普诺夫稳定性理论证明了闭环系统的稳定性.数值仿真表明该方法在保证参数估计误差有界的同时实现了导弹对姿态角指令的快速无静差跟踪.
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| 关 键 词： | 导弹 姿态控制 无源性理论 自适应控制 |
An Adaptive Attitude Control Law for Air-launched Cruise Missile |
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| HAN Yanhua,HUANG Panfeng,MENG Zhongjie. An Adaptive Attitude Control Law for Air-launched Cruise Missile[J]. Journal of Projectiles Rockets Missiles and Guidance, 2009, 29(5) |
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| Authors: | HAN Yanhua HUANG Panfeng MENG Zhongjie |
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| Affiliation: | HAN Yanhua1,HUANG Panfeng2,MENG Zhongjie2(1 College of Astronautics,Nanjing University of Aeronautics , Astronautics,Nanjing 210016,China,2 School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China) |
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| Abstract: | An adaptive attitude controller was designed based on dynamic inversion and passivity theory for air-launched cruise missile to solve the problem of its uncertainty of aerodynamic moment derivatives.The controller includes control law and parameter estimator.The control law was adjusted online according to estimated values of missile's parameters.It is proved by Lyapunov theory that attitude tracking error may converge at zero while parameter's estimation error keeping bounded.Numerical simulation proved ef... |
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| Keywords: | missile attitude control passivity theory adaptive control |
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