Multi-dimensional Taylor Network Optimal Control Of The Plane Symmetrical Cruise Missile Flight For Attacking Static Target

Cruise missile is a new high-tech weapons and long-range precision guided equipment,which has a strong penetration ability,tactical diversification,good economy and highly consumption ratio etc.,after the Gulf War lots of countries attempt to develop a new type of cruise missile.The guidance and control system is the core of the cruise missile and is the key to get stable flight and precision strike.This thesis adopts the design principle of spectrum separation based on the guidance loop and control loop of the cruise missile is designed separately.The mathematical model of cruise missile has the characteristics of complicated mechanism,strong coupling and nonlinear,this thesis adopts PID control,sliding mode control(SMC),multi-dimension Tayler network(MTN)control to design the controller,thus the attitude and guidance of cruise missile are controlled,the results are analyzed by MATLAB simulation.Firstly,analysis and comparison of the axisymmetric missile and the plane symmetrical missile of the difference,considering the characteristics of the plane symmetrical cruise missile,according to the analysis of force and torque is established of nonlinear and coupling six degrees of freedom motion equations of missile,finally introduce the missile maneuverability and overload.Based on the analysis of missile guidance and control system,the existing guidance method and the classical guidance law are proposed.The above three control methods are used to design the cruise missile attitude controller,and the controller parameters are optimized by the improved simplex method.And this thesis focuses on optimization of SMC controller and MTN optimal controller design process and control of longitudinal and lateral channel of missile attitude,full channel simulation finally across the symmetry of cruise missile,the missile control effect analysis in the different optimization controller.In this thesis,the design method of the guidance control system of the attacking static target of the plane symmetrical cruise missile is proposed based on the multi-dimension Taylor network optimal control,the guidance system is adopted in the design with gravity compensation proportional guidance law as the guidance law,the control system used in the design of BTT missile roll angle and method to control the overload,which introduces the angular velocity feedback compensation method can improve the anti-jamming performance of the missile and fast response performance.The integral sliding mode controller is designed and the MTN optimization controller is used to control the missile’s dive section.Thus,the effect of the above three optimal controllers is analyzed and compared.Finally,the design of the missile simulation system and the simulation algorithm are introduced,and then the wind interference model is introduced into the missile’s mathematical model,and the effect of the above three optimal controllers in attitude control and guidance control is compared.Missile flight control system simulation platform is designed based on GUI with MATLAB.Under the same conditions,the simulation results show that the optimal control performance and wind resistance of the MTN optimal control is the best.