Research on Missile Guidance Based on Three-Loop Autopilot Device

Abstract

In order to improve the speed of the guide head capturing the target in the case of guided missiles with large landing angle and reduce the angular deviation of the start point of terminal guidance, a high control method of missile autopilot design is proposed and the trajectory programming method-constraints of seeker (TPM-CS) is considered with multiple constraints of the guide head. The constraints of end-guidance start point are established according to the maximum detection distance of the seeker. The attack path constraints are established according to the geometric relationship between the projectile and the field of view angle of the guide head, and the objective function of minimizing the front angle and the amplitude of the control variables is established. In order to realize the optimal matching of the initial trajectory inclination and declination of the guided missile, the rocket ignition time, the glide start and control time, the guide head opening time and other parameters, a 5-stage ballistic planning model is established. And Simulink is utilized to simulate the guidance process. The design model of three-loop autopilot, the frequency response of the projectile, the proportional guidance system, the Seeker/Tracker subsystem and the Guidance subsystem model design are considered. The final simulation results show that this missile can operate well compared to conventional methods. The simulation system can show good results.