Design and Simulation of Controller for Hyper Velocity Kinetic Energy Missile  

超高速动能导弹控制器的设计与仿真(英文)

作　　者：康长赓[1] 雷成[2] 刘藻珍[1] 

机构地区：[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

出　　处：《Journal of Beijing Institute of Technology》2000年第1期107-112,共6页北京理工大学学报（英文版）

摘　　要：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.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 .

关 键 词：hyper velocity missile guidance missile control attitude control motor SIMULATION 

分 类 号：TJ76[兵器科学与技术—武器系统与运用工程]