Design And Analysis Of Control System For Radar Detection Guided Projectile

The capability of air defense and anti missile is the guarantee of ship safety.As an important means of air defense and anti missile,it is an important research topic for naval gun ammunition all over the world to improve its hit and damage probability to maneuvering target.From the research progress at home and abroad,the command guidance system based on shipborne radar detection is a feasible technical scheme for developing shipborne air defense and anti missile guided projectile.In this paper,theoretical analysis and simulation verification are carried out for the design of guidance and control system of command guided projectile under radar detection system.Firstly,we established the mathematical model of its motion process on the basis of analyzing the stress of guided projectile in each trajectory phase to analyze the influence of initial velocity and angle of fire on the uncontrolled trajectory.Then,we derived the transfer function of the missile body and analyzed the open-loop dynamic characteristics.Aiming at the poor dynamic stability when guided projectile is not calibrated,we designd a three loop overload autopilot.According to the time domain and frequency domain of autopilot,the gain coefficients of three loops were adjusted,and the design results were verified by simulation.In the midcourse guidance,in order to track the altitude deviation command with large aerodynamic variation and large maneuver stably,quickly and accurately,a fuzzy PD controller is adopted.In addition,we used the particle swarm optimization algorithm to optimize its parameters to obtain satisfactory control performance.In the terminal guidance,we improved the design of the example guidance law.A generalized proportional guidance law with gravity compensation is introduced to carry out the derivation and simulation analysis.The results showed that the method could increase the drop angle effectively and avoid the impact of the terminal overload by the attack angle.Finally,we simulated and verified the response ability and hit point correction ability of the designed guidance and control system and quantitatively analyzed the influence of gravity compensation coefficient and the handover time of midcourse and terminal guidance.Then,we carried out the digital simulation analysis,which was aimed at the error factors such as launching trajectory parameters,detection system measurement,rendezvous target information and control system actuator.To verify the reliability of the guidance and control system design,we used the Monte Carlo simulation method.This paper provides a technical basis for the design of the guidance and control system of command guided projectile under radar detection system.