Research on Trajectory Tracking Guidance Method Based on Particle Swarm Optimization

The projectile launched by large caliber artillery has parabolic flight characteristics, and its trajectory contains rich coordinate information and attitude information, which is an important reference information source. Aiming at the situation that the pulse engine is located at the tail of the projectile, the trajectory tracking guidance method is studied. On the basis of establishing the dynamics and kinematics model of the projectile, this paper proposes a guidance method of advance correction based on the trajectory perspective, and optimizes the pulse ignition time and advance correction time based on the particle swarm optimization algorithm with decreasing inertia weight, and designs the optimization model. The simulation results show that the proposed algorithm can effectively reduce the error between the landing point and the target point, and the trajectory tracking effect is good.