| 超高速动能导弹控制器的设计与仿真 |
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| 引用本文： | 康长赓,雷成,刘藻珍.超高速动能导弹控制器的设计与仿真[J].北京理工大学学报(英文版),2000,9(1):107-112. |
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| 作者姓名： | 康长赓 雷成 刘藻珍 |
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| 作者单位： | 1. 北京理工大学,机电控制工程系,北京,100081
2. 中国科学院,自动化所,北京,100080 |
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| 摘 要： | 研究超高速动能导弹 (HVKEM )控制器的设计和数字仿真 .建立弹道对瞄准线 (LOS)偏差的数学模型 ;闭环制导回路用相位超前 滞后校正网络补偿 ;设计出用于控制弹道姿态的姿态控制发动机 (ACMs)的选择算法 .在存在多种干扰条件下 ,控制器数字仿真结果满足圆形误差概率(CEP)小于 0 5m .用ACMs作为执行机构控制HVKEM姿态的控制方案是可行的
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| 关 键 词： | 超高速导弹 导弹控制 姿态控制发动机 仿真 |
| 收稿时间： | 9/7/1999 12:00:00 AM |
Design and Simulation of Controller for Hyper Velocity Kinetic Energy Missile |
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| KANG Chang-geng,LEI Cheng and LIU Zao-zhen.Design and Simulation of Controller for Hyper Velocity Kinetic Energy Missile[J].Journal of Beijing Institute of Technology,2000,9(1):107-112. |
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| Authors: | KANG Chang-geng LEI Cheng and LIU Zao-zhen |
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| Affiliation: | Department of Flight Vehicle and Control, Beijing Institute of Technology, Beijing 100081;Automation Institute, Chinese Academy of Sciences, Beijing 100080;Department of Flight Vehicle and Control, Beijing Institute of Technology, Beijing 100081 |
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| Abstract: | The controller design and digital simulation for the hyper velocity kinetic energy missile is investigated. A mathematical model of the trajectory deviation from the line of sight was established, the guidance closed loop was compensated with a phase advance lag corrective network, a selecting algorithm of the attitude control motors used to steer the missile's attitude was presented. In the presence of a wide variety of disturbances the results of digital simulation are satisfactory to circular error probability(CEP) being less than 0 5?m. The steering scheme utilizing attitude control motors as actuators to control the attitude of the missile is feasible. |
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| Keywords: | hyper velocity missile guidance missile control attitude control motor simulation |
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