| Robust Graded Sliding Mode Tracking Control for Low Speed Spinning Ballistic Missiles |
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| 引用本文： | 周军 王志 周凤歧. Robust Graded Sliding Mode Tracking Control for Low Speed Spinning Ballistic Missiles[J]. 兵工学报(英文版), 2007, 3(1): 15-19 |
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| 作者姓名： | 周军 王志 周凤歧 |
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| 作者单位： | Institute of Precision Guidance and Control, Northwestern Polytechnical University, Xi＇ an 710072, China |
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| 摘 要： | The nonlinear dynamic model of spinning ballistic missiles is established during the first boosting phase of the missile. Based on the conventional backstepping sliding mode control and the assumption of a two time-scale separation of missile dynamics, a graded sliding mode controller is designed with two sub-sliding surfaces which have invariability to external disturbances and parameter perturbations, and a matrix which comprises three first order low pass filters is introduced to prevent ＂explosion of terms＂. Owing to the upper bounds of the uncertainties are difficult to obtain in advance, adaptive laws are introduced to estimate the values of the uncertainties in real-time. Eventually, the numerical simulation results given to show the proposed controller can ensure the steady flight of missiles.
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| 关 键 词： | 低速旋转 弹道导弹 飞行控制 分级滑动模 跟踪控制 鲁棒 |
| 文章编号： | 1673-002X（2007）01-0015-05 |
| 收稿时间： | 2006-05-22 |
Robust Graded Sliding Mode Tracking Control for Low Speed Spinning Ballistic Missiles |
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| ZHOU Jun,WANG Zhi,ZHOU Feng-qi. Robust Graded Sliding Mode Tracking Control for Low Speed Spinning Ballistic Missiles[J]. Journal of China Ordnance, 2007, 3(1): 15-19 |
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| Authors: | ZHOU Jun WANG Zhi ZHOU Feng-qi |
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| Abstract: | The nonlinear dynamic model of spinning ballistic missiles is established during the first boosting phase of the missile. Based on the conventional backstepping sliding mode control and the assumption of a two time-scale separation of missile dynamics, a graded sliding mode controller is designed with two sub-sliding surfaces which have invariability to external disturbances and parameter perturbations, and a matrix which comprises three first order low pass filters is introduced to prevent "explosion of terms". Owing to the upper bounds of the uncertainties are difficult to obtain in advance,adaptive laws are introduced to estimate the values of the uncertainties in real-time. Eventually, the numerical simulation results given to show the proposed controller can ensure the steady flight of missiles. |
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| Keywords: | flight control ballistic missile spin backstepping graded sliding mode adaptive law Missiles Spinning Speed Tracking Control Sliding Mode numerical simulation results show controller steady flight adaptive laws estimate values upper bounds uncertainties advance explosion |
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