| 导弹姿态的反演法控制器设计 |
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| 引用本文： | 彭南楠,孙明玮,魏毅寅,马洪忠,杨明. 导弹姿态的反演法控制器设计[J]. 兵工自动化, 2006, 25(3): 6-7,10 |
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| 作者姓名： | 彭南楠 孙明玮 魏毅寅 马洪忠 杨明 |
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| 作者单位： | 北京机电工程研究所,北京,100074;山东财政学院,计算机系,山东,济南,250014 |
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| 摘 要： | 反演法控制器,将导弹姿态角作为系统控制对象.控制器根据给定的俯仰角、偏航角和滚动角参考信号得出相应的舵偏输入,使导弹能按给定姿态角确定的轨迹飞行.定点及全空间仿真结果证明,该控制器设计可行.
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| 关 键 词： | 姿态控制 反演法 动态性能 |
| 文章编号： | 1006-1576（2006）03-0006-02 |
| 收稿时间： | 2005-08-22 |
| 修稿时间： | 2005-08-222005-10-06 |
Design of Backstepping Method Controller for Missile Attitude |
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| PENG Nan-nan,SUN Ming-wei,WEI Yi-yin,MA Hong-zhong,YANG Ming. Design of Backstepping Method Controller for Missile Attitude[J]. Ordnance Industry Automation, 2006, 25(3): 6-7,10 |
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| Authors: | PENG Nan-nan SUN Ming-wei WEI Yi-yin MA Hong-zhong YANG Ming |
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| Affiliation: | 1. Bcijing Electromcchanical Engineering Research Institute, Bcijing 100074, China; 2. Dept. of Computer, Shandong Finance Institute, Jinan 250014, China |
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| Abstract: | The missile attitudes were taken as the control objects of system by backstepping method controller. According to given reference signals of pitching angle, drifting angle and rolling angle, the relative rudder deviation inputs were calculated by backstepping controller. So the missile could be flied along the trace in decided attitude angle. The controller was approved feasibly by fixed point and total space simulation. |
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| Keywords: | Attitude control Backstepping method Dynamic performance |
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