某型靶弹制导控制方法研究  

Research on Guidance Control Method for Target Missile

作　　者：郑旭 杨锁昌 ZHENG Xu;YANG Suochang(Shijiazhuang Campus,Army Engineering University,Shijiazhuang 050003)

机构地区：[1]陆军工程大学石家庄校区,石家庄050003

出　　处：《舰船电子工程》2019年第4期40-44,共5页Ship Electronic Engineering

摘　　要：针对某型火箭弹改制靶弹结构特点和飞行任务,对其制导控制方法进行研究。设计了以姿态角速度为阻尼回路反馈、以姿态角为控制回路反馈的靶弹姿态控制系统结构,为提高姿态控制系统对大空域飞行过程的适应性,采用变增益法设计姿态控制系统增益系数;采用程序控制和位置偏差反馈相结合的弹道跟踪制导律实现对方案弹道的跟踪;最后,在一定干扰条件下,对所设计靶弹制导控制方法进行了半实物仿真试验验证。结果表明,所设计靶弹制导控制方法能够有效实现对方案弹道的跟踪,对初始位置偏差和气动参数偏差等干扰因素有较好的抑制作用。Aiming at the structural characteristics and flight missions of a certain type of rocket projectile,the guidance control method is studied.The structure of the target attitude control system with the attitude angular velocity as the damping loop feedback and the attitude angle as the control loop feedback is designed.In order to improve the adaptability of the attitude control system to the large airspace flight process,the variable gain method is used to design the attitude control system gain coefficient.The ballistic tracking guidance law combined with program control and position deviation feedback is used to track the program trajectory.Finally,under the certain interference conditions,the semi-physical simulation test of the designed target missile guidance control method is verified.The results show that the designed target missile guidance control method can effectively achieve the tracking of the program trajectory,and has a good inhibitory effect on the interference factors such as initial position deviation and aerodynamic parameter deviation.

关 键 词：靶弹 制导控制 方案弹道 弹道跟踪 半实物仿真 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]