舰船电子工程2019，Vol.39Issue(4)：40-44,5.DOI:10.3969/j.issn.1672-9730.2019.04.009
某型靶弹制导控制方法研究
Research on Guidance Control Method for Target Missile
郑旭 1杨锁昌1
作者信息
- 1. 陆军工程大学石家庄校区 石家庄 050003
- 折叠
摘要
Abstract
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Key words
target missile/guidance control method/program flight/ballistic tracking/semi-physical simulation分类
军事科技引用本文复制引用
郑旭,杨锁昌..某型靶弹制导控制方法研究[J].舰船电子工程,2019,39(4):40-44,5.
