| 导弹姿态控制伺服系统的变结构控制 |
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| 引用本文： | 刘根旺,许化龙.导弹姿态控制伺服系统的变结构控制[J].上海航天,2004,21(6):15-17,35. |
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| 作者姓名： | 刘根旺 许化龙 |
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| 作者单位： | 西安第二炮兵工程学院,陕西,西安,710025 |
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| 摘 要： | 为消除导弹姿态控制伺服系统变结构控制中的抖振，在状态轨迹与滑动平面夹角变结构控制律的基础上，将原来的二阶系统扩展为n阶。所设计的控制律兼具连续控制律与非连续控制律的优点，动态品质优良。仿真结果验证了理论分析的有效性。
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| 关 键 词： | 导弹姿态控制 伺服系统 变结构 控制律 渐近夹角 |
| 文章编号： | 1006-1630(2004)06-0015-03 |
Application of VSC to Missile Attitude Control Servo System |
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| LIU Gen-wang,XU Hua-long.Application of VSC to Missile Attitude Control Servo System[J].Aerospace Shanghai,2004,21(6):15-17,35. |
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| Authors: | LIU Gen-wang XU Hua-long |
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| Abstract: | To eliminate the chattering of variable structure control (VSC) in missile servo system for attitude control, the control law was expanded from second-order to n order on the basis of status trace and variable plane included angle. The control law designed which dynamic quality was very well had characteristics both of continuous and non-continuous control laws. The simulation results verified the effectiveness of theory analysis. |
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| Keywords: | Missile attitude control Servo system Variable structure Control law Approach angle |
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