Research On Finite-Time Switching Control For Compound Control Missile

To intercept the maneuverable Tactical Ballistic Missile(TBM)and other high-speed and high maneuvering aerial vehicles is one of the air defense missile systems developing trends of the world.In order to destroy the target by Hit-To-Kill(HTK)technology,it requires that the interceptor respond more rapidly,and have precise control performance.The compound control with lateral thrust and aerodynamic forces whose response time is very short is taken to improve the dynamic response speed of the interceptor's control system,and to intercept the high-speed and high-maneuvering target at high altitude.The compound control missile is a typical multiple actuators switching control system,and considering it requires that the missile intercept the target in finite time.Based on these characteristics,the research of the guidance and control system design method have more important theoretical significance and practical value of engineering applications.In this paper,the control system design of the compound control system is studied.According to the configuration of the Impulse Attitude Control Motors(IACM),the mathematical model of lateral force and moment are given.Then on the base of that,the kinematics and kinetic models of the compound control interceptor is established.And a brief contrastive analysis of aerodynamic force control and lateral force control,these two distinct means of control method are carried out,and the influence factors of their performance are pointed out,respectively.Considering the pure aerodynamic force control method,the double-loop controller of missile's overload tracking system is designed based on the classical control theory,and a novel overload tracking switched control strategy is proposed,which have two controllers with different gain.Through simulation these two control strategies are compared and analyzed.And in the Aerodynamic/Lateral Force Compound Control System(ALFCCS),we regard lateral force control system and aerodynamic control system as two subsystems on account of the switched system control theory.Then the switching controllers of ALFCCS are designed by using the linear discrete time switched system analysis and synthesis method.By solving feasibility problem of Linear Matrix Inequalities(LMIs),the state feedback control gain of the switching controllers is obtained;design result is verified with MATLAB.Taking the missile pitch channel as research subjects,the finite time switching control system design and implementation method is discussed.The instantaneous momentum of the IACM on the mass center of the missile is considered as exogenous disturbance,and then based on the Fast Terminal Sliding Mode Control(FTSMC),the fast convergence finite-time controller is designed,which ensures that the tracking error can be converge to zero in finite time and have good dynamic performances and meets the design requirements.Considering the discrete-time switched characters of lateral force and continuous characters of aerodynamic,the switching control implementation method of the ALFCCS is obtained using boundary layer techniques.In the view of the available overload constraint of the interceptor missile during the process of terminal guidance,and the miss distance constraint in the end of the terminal guidance.The finite time guidance law of the aerodynamic/lateral force compound control missile is proposed.Regarding the ALFCCS designed previously as a first order segment of inertia,and embeds it into the terminal guidance system which parameters are time-varying.The target maneuvering is considered as an external disturbance input,and then an Anti-saturation Guidance Law(ASGL)design method is presented.The method uses a pre specified time interval and several pre specified weighted matrix functions to characterize the constraints of the terminal guidance system dynamic,and The sufficient conditions are given to guarantee the terminal guidance system both Finite Time Boundedness(FTB)and Input-output Finite Time Stability(IO-FTS)using Differential Linear Matrix Inequalities(DLMIs).By comparing with Proportional Navigation(PN),the results show that the overload constrains and expected guidance precision were both met,and the correctness and feasibility of the guidance method is verified.