Control Scheme Design And Ballistic Characteristics Analysis For Trajectory Correction Projectile Equipped With Pulses

The technology of trajectory correction is an important way of conventional ammunition simple guided achieved. In this thesis, a tape of trajectory correction projectile equipped with impulses is considered as the subject. The Problems of the ballistic characteristics and control tactics are investigated. The main work is listed as follows:(1) Study of the motion model for the projectile equipped with impulses. Contrary to its feature, the model of transient impulse control force and moment is established. According to the theory that impulse is equal, the model of equivalent average impulse control force and moment is also established. The6D grid model of the projectile is established by analyzing the force on the projectile.(2) Analysis on ballistic characteristics for the projectile equipped with impulses. Analyze the ballistic characteristics by the linearization of the small perturbations. The effete of the impulse parameters and aerodynamic parameters on the trajectory are analyzed.And provide the basis for the control scheme. Study the effect of the aerodynamic interference forced by the impulse on the ballistic characteristics.(3) Design the optimal for the trajectory correction projectile. According to the characteristics of the projectile, several optimal design variables are selected. Determine the constraint conditions and the objective function. Proposed a modified Particle Swarm Optimization to optimize the control parameters of the projectile and the flow chart of the algorithm is designed. The results indicated that the algorithm can devise the parameters quickly and provide the theoretical basis for the design of the projectile parameters.(4) Design the control scheme for the terminal trajectory projectile. A type of control scheme which is based on the measurement between the projectile and the target is proposed. A proportion guidance law which is based on gravity compensation is proposed and verification that the guidance law can apply the discrete and limited features is raised. According to the differences between conventional missile and the terminal trajectory projectile, a controller structure which can match the projectile is designed, and the control parameters and performance are analyzed. One type of ignition algorithm is designed which is based on the work above.