| 导弹机动突防滑模制导律 |
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| 引用本文： | 周荻,邹昕光,孙德波.导弹机动突防滑模制导律[J].宇航学报,2006,27(2):213-216. |
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| 作者姓名： | 周荻 邹昕光 孙德波 |
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| 作者单位： | 1. 哈尔滨工业大学航天学院,哈尔滨,150001
2. 哈尔滨工业大学自动控制与测试系339信箱,哈尔滨,150001 |
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| 摘 要： | 为了得到一种用于导弹机动突防的制导律,我们在制导律设计中令视线角速率跟踪正弦有界震荡信号.在导弹机动突防过程中,导弹自动驾驶仪的惯性滞后会影响制导精度.我们利用递推李雅普诺夫设计方法推导出了一种考虑自动驾驶仪惯性的运动跟踪滑模制导律,它可以令视线角速率跟踪给定的指令信号.仿真结果表明,这种制导律可以令导弹机动突防成功的概率提高到89%,而且在自动驾驶仪滞后情况下的制导精度很高,脱靶量仅有0.3mm.
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| 关 键 词： | 导弹机动突防 自动驾驶仪惯性 滑模制导律 |
| 文章编号： | 1000-1328（2006）02-0213-04 |
| 收稿时间： | 03 10 2005 12:00AM |
| 修稿时间： | 2005-03-102005-08-01 |
A Sliding-Mode Guidance Law for Homing-Missiles Breaking Through Defense with Maneuver |
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| ZHOU Di,ZOU Xin-guang,SUN De-bo.A Sliding-Mode Guidance Law for Homing-Missiles Breaking Through Defense with Maneuver[J].Journal of Astronautics,2006,27(2):213-216. |
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| Authors: | ZHOU Di ZOU Xin-guang SUN De-bo |
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| Institution: | 1. School of Aerospace, Harbin Institute of Technology, Harbin 150001, China; 2. Dept. of Automatic Measurement and Control, Mailbox339, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: | In order to steer a missile to break through defense with maneuver, a guidance law should force the angular rate of line-of-sight to track a given command, such as a bounded sinusoidal command. While a missile breaking through defense with maneuver, the lag of its autopilot is not negligible in guidance law design in order to reduce the final miss distance. Considering the lag, the recursive Lyapunov method is employed to design a motion-tracking sliding-mode guidance law, which makes the angular rate of line-of-sight to track a given signal. Simulation results show that under this guidance law the probability of missile breaking through defense is improved to 89%, and the miss distance is only 0.3mm in the presence of autopilot lag. |
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| Keywords: | Breaking through defense of maneuvering missiles Lag of autopilot Sliding-mode guidance |
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