Research On Blended Control Method For Missile With Lateral Thrust And Aerodynamic Of Attitude And Orbit Control

In recent years,the performance of missiles has been improved rapidly,and the emergence of high-speed and large maneuvering targets has put forward higher requirements for air defense interception system.,the tradit ional interceptor operated by aerodynamic control can not hit the target accurately.In addit ion to the aerodyna mic control mode,the blended control system wit h lateral thrust and aerodynamic can also turn on the direct force when necessary,which improves the tracking performance of missiles to signals,and attracts extensive attention of military powers.In this paper,the research of the blended control system with lateral thrust and aerodynamic is carried out,and the attitude-orbit control composite method is studied for attitude-control and orbit-control missiles.The research contents mainly include the fo llow ing aspects:Firstly,the mathemat ical model of blended control system with lateral thrust and aerodynamic is establis hed,the kine matics and dynamics equations are deduced and simplified,then the relative motion equation of the projectile and the target is deduced,which lays the foundation for the follow-up control research.Secondly,based on a variety of common control methods,a ttitude stabilization controllers are designed.First ly,for the control system,the attitude control problem is described and the corresponding controller is designed.Then,the design idea of ADRC control is given in combinat ion with specific problems.Then,several controllers including ADRC controllers are simulated and compared.The simulat ion results show that ADRC has the advantages of small response time,high tracking accuracy and good stability,especially for non-linear system.In addit ion,the lateral thrust and aerodynamic composite algorit hm of attitude control is studied,and a variety of allocation algorit hms are proposed.For each algorithm,its effect is verified by simulation.After comparing these algorithms,the lateral thrust-aerodyna mic allocation algor ithm is selected according to the actual situat ion.Thirdly,a variety of lateral thrust opening strategies of orbit control are designed.According to the simulation results,the ideal control strategy is selected.Combined with the attitude control stability control method,the attitude-orbit blended control system is compared with the single attitude control and the single orbit control respectively.Compared wit h the single attit ude control system,the tracking accuracy of the composite attit ude-orbit control system is higher;compared wit h the single orbit control system,the tracking speed of the composite attit ude-orbit control system is faster and the stability is better.The simulation results show that the attit ude-orbit blended control system has more obvious advantages in tracking high-speed and large maneuvering targets.Finally,a new integrated simulation platform for flight control system is designed by using LabVIEW and Simulink software.,which can directly modify control parameters in user interface and display simulat ion curves.The platform shows good vis ibility and easy operation.