Research on Guidance Control Method for Target Missile
ZHENG Xu
YANG Suochang
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.
Keywords：target missileguidance control methodprogram flightballistic trackingsemi-physical simulation
Publication Date：2019-01-01
Online Publishing Date：2025-08-15(First online date of this platform, not the publication date of the document)
Pages：5( 40-44 )