Research On Multi-dimensional Heterogeneous Compound Control Method Of Missile

With the development of missile technology,in order to more effectively intercept large-maneuvering and high-speed incoming targets,the response speed of air defense missiles and the available overload requirements are higher.Traditional air defense missiles only rely on pneumatic rudder as a single actuator for control,which results in a large response time delay and low efficiency of aerodynamic rudder when the dynamic pressure is low.The use of multi-dimensional heterogeneous compound control technology and the addition of actuators such as attitude and orbit control thrusters can effectively overcome the deficiencies of aerodynamic rudder control,so that air defense missiles can quickly respond to command signals to achieve precise guidance.Therefore,the study of multi-dimensional heterogeneous compound control technology is the missile One of the important issues in precision guidance and control research.The main research in this paper is axisymmetric missiles.The focus of the research is on the compound control strategy of aerodynamic rudder,attitude control thrusters,orbit control thrusters multi-actuating mechanism,and the research of attitude and orbit control thrusters startup strategy.First,the coordinate system and the conversion relationship between the coordinate systems are introduced,and the three-channel mathematical model of the compound control system of the liquid fuel thrusters with attitude and orbit control is derived.Then,the design of the control law of the attitude and orbit control liquid fuel thrusters is introduced in detail,and the linear state feedback control law of the deflection angle of the elevator rudder is designed with the longitudinal channel as an example.Then design a sliding mode controller with a boundary layer,and use the switch control of the attitude orbit control thrusters to improve the response speed of the system overload and eliminate the system chattering phenomenon.For the attitude and orbit control solid pulse thrusters compound control system,the exponential reaching law is adopted to design the starting strategy of the attitude and orbit control thrusters,and the ignition logic of pulse thrusters is introduced.Finally,the simulation results at25 km and 35 km altitude are obtained through numerical simulation.The research results realize the overload coordinated and fast response control technology of the missile multi-dimensional heterogeneous compound control system.The final simulation results show that the higher the missile height,the lower the efficiency of the aerodynamic rudder,the slower the response speed of the aerodynamic control system,and the more frequent the use of the attitude and orbit control thruster of the multi-dimensional heterogeneous compound control system.The overload response speed of the direct force and aerodynamic control system has been significantly improved compared to only the aerodynamic control.Compared with the composite control system of the liquid fuel thruster with attitude and orbit control,the composite control system of the attitude and orbit control solid pulse thrusters will track the overload command more smoothly in the actual guidance process,and the thrust generated by thrusters will not change drastically.