Multi-dimensional Taylor Network Optimal Control Of The Axisymmetric Cruise Missile Flight For Attacking Moving Target

Cruise missiles are modern high-tech weapons with the advantages of strong penetration,good economy,high consumption ratio and diversification of tactics.They are mainly used to strike a precise attack on the target.A significant feature of missiles compared with ordinary weapons is that missiles have guidance systems.Guidance system is the core technology of the missile which determines the missile's combat performance to a great extent.It is also the key that the missile can achieve stable flight and precise attack.The design principle in this thesis is based on spectrum separation.And in this thesis,the cruise missile guidance circuit and the control circuit are designed separately.The cruise missile model is characterized by strong coupling,nonlinearity and complicated mechanism.In this thesis,the gravity compensation proportional guidance law and the adaptive sliding guidance law are used.And the PID optimal control,the integral sliding mode optimal control(SMC)requiring the accurate mechanism model of controlled object,and the multi-dimension Taylor network(MTN)optimal control not requiring the accurate mechanism model of controlled object just as the PID optimal control does not,are used to design controller,achieving axisymmetric cruise missile to attack dynamic target and using MATLAB software to simulate the experiment.First of all,a nonlinear and fully coupled six degrees of freedom equations of motion are established based on the forces and moments of the axisymmetric cruise missile.Then a maneuvering target model is established.It lays the foundation for the design of missile guidance control system by analyzing the missile guidance control system and expounding the existing guidance methods and the classical guidance law.In this thesis,the design method of the guidance control system of the attacking moving target of the axisymmetric cruise missile is proposed based on the MTN optimal control,the guidance system is adopted in the design with gravity compensation proportional guidance law and the adaptive sliding guidance law as the guidance law.Proportional steering law is applicable to the situation where the goal is not maneuvering or the maneuverability is not big.For the maneuvering goal,the proportional guidance performance is greatly reduced.Sliding mode guidance law is a guidance law designed by using variable structure theory based on proportional guidance law.Variable structure theory is robust to external disturbance and parameter perturbation.In the control system design,the PID optimal controller,the integral sliding mode controller and the MTN optimal controller are adopted.The simplex method is used to optimize the controller parameters,and the guidance control effects of the three optimal controllers under different guidance modes are compared.Missile flight control system simulation platform is designed based on GUI with MATLAB.Simulation experiments under windless conditions were conducted to compare the guidance control effects of the three kinds of optimal controllers under the gravity compensation proportional guidance law and the adaptive sliding guidance law.Then,the wind disturbance model is introduced and added into the mathematical model of the missile.The guidance control effects of the three kinds of optimal controllers under different guidance modes are compared.Under the same conditions,the simulation results show that the optimal control performance and wind resistance of the MTN optimal control is the best.