Multi-Dimensional Taylor Network Optimal Control Of Plane-Symmetrical Missile Flight Against Maneuvering Targets

As an important member of precision guided weapons,missile has gradually become an indispensable weapon in modern battlefields.Research and design of guidance and control system is the key to improve combat performance of missile.In this thesis,terminal guidance and control system against maneuvering targets is studied taking plane-symmetrical missile as the research object.A design method of plane-symmetrical missile terminal guidance and control system against maneuvering targets in three-dimensional space based on multi-dimensional Taylor network optimal control is proposed.At the same time,guidance and control systems based on PID optimal control and sliding mode variable structure optimal control are designed for comparison,and the systems are simulated and compared using MATLAB.The main contents of this thesis are as follows.Firstly,plane-symmetrical missile is briefly introduced.According to its characteristics and control mode,main problems in the design of guidance and control system are expounded,the composition and design idea of the terminal guidance control system are introduced,and the research status at home and abroad is summarized.Secondly,mathematical model of plane-symmetrical missile is established,which lays a foundation for the design and simulation of guidance and control system in the following sections.Based on the analysis of the forces and moments of the missile,six-degree-of-freedom nonlinear equations of motion of plane-symmetrical missile are established.Considering the key factors of plane-symmetrical missile control,a missile nonlinear control system model is established.Considering the environmental disturbance,the wind field model and the missile kinematics model under wind disturbance are established.Then,terminal guidance law is designed.In order to combat maneuvering targets in three-dimensional space,the adaptive sliding mode terminal guidance law is designed,and thesimulation model is established.Simulations are conducted to verify the effectiveness of the designed guidance law.Next,control system is designed.In view of the characteristics of the motion and control mode of the plane-symmetrical missile,three-channel coordinated autopilots are designed based on PID,sliding mode variable structure which needs precise mechanism model and multi-dimensional Taylor network respectively considering nonlinear factors of steering engine and the coupling between channels caused by bank-to-turn.The designed guidance law and control system are integrated to conduct six-degree-of-freedom simulation of the guidance and control system against maneuvering targets.Besides,aerodynamic parameter perturbation experiment and wind disturbance experiment are carried out to test the performance of the system under different controllers.The simulation results under the same conditions show that the terminal guidance and control system based on multi-dimensional Taylor network optimal control has the best hit accuracy,wind resistance and robustness.Finally,MATLAB GUI is used to design the simulation platform of the plane-symmetrical missile guidance and control system for the convenience of communicating with users and displaying simulation results.