Investigations On Some Problems Of Missile With Lateral Jet And Aerodynamic Surfaces

With the miniaturization,agile and high speed tendency of air-attack weapon,air defense missile need a higher maneuvering capability and guidance precision.Traditional air defense missile rely only on aerodynamic rudders to control,response delay is large and the control efficiency will decrease when dynamic pressure is low,so it's unable to meet the requirement of hit-to-kill.The use of lateral jet and aerodynamic compound control technology can make up the shortage of aerodynamic rudders effectively,which improve missile's mobility and intercept precision,so it is of great value to research guidance and control problems for compound control missile.In this paper,some problems of guidance and control system are researched for endo-atmospheric missile with lateral jet and aerodynamic surfaces.The main contents include as follow:Mathematical model is deduced for missile with lateral jet and aerodynamic surfaces.Aerodynamic configuration and attitude control engines layout is analyzed,the basic layout of the missile used in this paper is determined;the calculating model of jet interaction factors and thrust of attitude control engines are established,based on this,the kinematics and dynamics model of compound control missile are finally derived.These works provide the basis for further researches.Finite time convergence terminal guidance law for missile with lateral jet and aerodynamic surfaces is studied.Principles of some kinds of sliding mode controls are introduced and analyzed;According to the relative kinematic model between missile and target,a finite time convergence guidance law based on second-order non-singular terminal sliding mode is proposed.The stability and convergence time are analyzed,and the effectiveness of guidance law is verified by simulation.Control allocation algorithm for the compound control missile is studied.Several commonly used control allocation strategies are analyzed respectively,considering theproblems of current allocation strategies,a new integrated allocation principle considering the overload track error and the remaining flight time is proposed.Fuzzy control theory is used to design allocation parameters for the two subsystems according to the principle;Adaptive genetic algorithm based on hormone regulation principles is used to optimize the allocation parameters,and simulation is used to verify the convergence speed and accuracy of algorithm.Ignition algorithm and implementation for attitude control engines are researched.Fuzzy control theory is used to design ignition algorithm tracking the overload command,and variable universes adaptive strategy is used to change universe adaptively,which improve the control accuracy;Considering the application of ignition algorithm,finite time converge differentiator,PWPF modulator for rolling stable missile,and an improved superimposed ignition method for rolling missile are designed respectively.Simulation result verified the effectiveness of algorithm.Integrated guidance and control design method is researched for air defense missile.Mathematical model of integrated guidance and control in pitch channel is deduced,integrated controller is designed based on backstepping theory,and the shortcomings of the controller are analyzed.Based on this,a novel integrated guidance and control systems design method is proposed based on dynamic surface method combined with nonlinear disturbance observer and integral control.System stability is analyzed by Lyapunov function,and simulation is used to verify the effectiveness of algorithm.