Research On Guidance And Control Technology Of Terminal Guidance Section For Anti-ship Missile

There are two main trends of development in modern anti-ship missiles,and one of them is to develope supersonic cruise anti-ship missile.In order to improve the range and penetration ability of anti-ship missile,supersonic anti-ship missiles usually use high altitude cruise ballistic combined with dive attack trajectory or super low altitude sea skimming trajectory to approach the target.This paper takes the attack mode of high altitude cruise trajectory combined with low altitude sea skimming trajectory as the object of study.The guidance and control methods of the terminal guidance section of the supersonic cruise missile are studied.First of all,the mathematical modeling of anti-ship missile is carried out.The coordinate systems commonly used in the anti-ship missile motion equation is defined,the transformation relationship between coordinate systems is given.Through the Newtonian mechanics and related laws,we establish the kinematics and dynamics equation of the missile,give the calculation method of aerodynamic force and aerodynamic moment in the equation,get the mathematical model of the six degrees of freedom motion of the anti-ship missile,and lay the foundation for the following research and design.In the lateral trajectory plan,the main guidance purpose of the missile is to accurately hit the target and ensure the damage effect.A missile guidance method based on proportional guidance law and ballistic guidance law is proposed to ensure the guidance purpose.A proportional guidance law linearization model is established,and the proportional guidance guidance loop under ideal condition is analyzed.The optimal proportional guidance coefficient and the relationship between the standardized miss distance and the terminal guidance time is obtained.The trajectory shaping guidance law is mathematically derived,and the engineering realization way of trajectory shaping guidance law is studied.The influence of residual time estimation on guidance accuracy is analyzed.In view of the characteristics of the longitudinal trajectory with the angle of attack constraint and the rapid reduction of the height,a new guidance strategy that can achieve rapid deduction of height and ensure the smoothness of the ballistic is proposed.The longitudinal trajectory of the terminal guidance section of anti ship missile can be divided into four stages.The plan descent stage adopts the maximum overload method to reduce height.The first descent stage,the second descnt stage and the sea skimming attack stage use the height tracking control method.The longitudinal guidance scheme is designed for each stage.The lateral trajectory is divided into a non maneuverable stable flight section,a tracking guidance section with proportional guidance law and a maneuver guidance section with a trajectory shaping guidance law.The work flow of the guidance system and the conditions of the handover shift are studied.Aiming at the problem of altitude tracking control of anti ship missile,a design method of altitude control system based on two structures of attitude autopilot and three loop overload pilot is put forward,and the rapidity and stability of the system are analyzed.The influence of different static stability of the missile on the performance of the autopilots is studied.Finally,the simulation of the interference factor deflection is given,which verifies the correctness and robustness of the design results of the guidance and control system.