| 再入弹头大攻角俯仰运动的非线性状态反馈控制 |
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| 引用本文： | 史小平.再入弹头大攻角俯仰运动的非线性状态反馈控制[J].上海航天,2006,23(1):8-11. |
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| 作者姓名： | 史小平 |
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| 作者单位： | 哈尔滨工业大学,控制与仿真中心,黑龙江,哈尔滨,150001 |
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| 摘 要： | 为提高大攻角飞行时具有非线性特性的姿态系统的控制精度,在弹头俯仰运动的非线性数学模型基础上,以弹头攻角为被控制信号,尾翼偏角指令为输入信号,设计了一种全状态反馈非线性姿态控制律,并进行了仿真试验。结果表明,所设计的控制律的稳态精度高、动态响应快。
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| 关 键 词： | 再入弹头 姿态控制 俯仰运动 非线性控制律 攻角 尾翼偏角 |
| 文章编号： | 1006-1630（2006）01-0008-04 |
| 收稿时间： | 2005-06-28 |
| 修稿时间： | 2005-06-282005-07-11 |
Nonlinear State Feedback Control of Pitch Motion for Reentry Missile with a Large Attack Angle |
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| SHI Xiao-ping.Nonlinear State Feedback Control of Pitch Motion for Reentry Missile with a Large Attack Angle[J].Aerospace Shanghai,2006,23(1):8-11. |
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| Authors: | SHI Xiao-ping |
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| Institution: | Control and Simulation Center, Harbin Institute of Technology, Harbin Heilongjiang 150001, China |
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| Abstract: | To improve the control precision of attitude system with nonlinear characteristic in large angle of attack flying,a nonlinear full state attitude control law was designed based on the nonlinear model of pitch motion for reentry missile in this paper,in which the angle of attack was served as the output and command of the tail fin deflection as its input.The analysis of simulation results showed that the control law designed had high steady precision and fast dynamic response. |
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| Keywords: | Reentry missile Attitude control Pitch motion Nonlinear control law Angle of attack Tail fin deflection |
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