Dynamics Analysis And Control Of Cooperative Attack On Medium And Long Range Guided Rockets

In modern warfare,with the military demand prefer long range and high precision operational indexes,and considering the advantages of low cost and high cost-effectiveness ratio of rockets,the above military demand can be satisfied by improving the range efficiency of rockets in the gliding stage and the cooperative guidance effectiveness in the terminal guidance stage.Therefore,this article,according to the aerodynamic characteristics of rocketes and attitude stability control system in the glide phase and the terminal guidance phase of the coordinated control system,based on Fluent pneumatic simulation method,aerodynamic characteristics of the glide phase are analyzed,based on robust back-stepping control method and the adaptive control method,the attitude of the glide phase stability control are studied,and based on consistency protocol,distributed collaborative guidance of terminal guidance phase are further researched,the main contents include:First of all,for the attitude control system of the lift body in the glide phase,the dynamic equations of the three-channels attitude stability control system with attack Angle,sideslip Angle and velocity inclination Angle as state variables and the dynamic equations of the three-channels attitude angular velocity system with rudder deflection as control variables are derived and established in the Soviet coordinate system.For the cooperative control system in the terminal guidance stage,the dynamic equations of multi-missiles cooperative attack is established.In addition,the related graph theory and finite time stability theory are introduced to provide theoretical basis for controller design and stability analysis.Secondly,for the aerodynamic simulation of the lift body in the glide stage,the aerodynamic parameters at different angles of attack and Mach Numbers are obtained by setting the relevant parameters of Fluent at hypersonic speed,so as to analyze the relevant aerodynamic characteristics of the lift body and provide data and theoretical basis for the efficient gliding range extension.Again,for the attitude stabilization controller design in the glide stage of the lift body,the controller design problem under the known and unknown disturbance bounds is discussed,for the situation of known disturbance bound,perturbation operator is used to represent the disturbance produced by interference on the system state equation due to the aerodynamic parameters change,speed change external disturbance for the lift body under hypersonic flight condition,so that,the dynamic equations of the attitude system under disturbance is obtained.Based on robust back-stepping control method,the controller is designed to compensate for disturbance and stable track expected attitude angle,the problem of "differential explosion" in back-stepping control is solved by introducing a differential tracker,both the theoretical and simulation results have verified the effectiveness of the designed controller.for the situation of unknown disturbance bounds,the adaptive control method is used to estimate the upper bound of the disturbance accurately,and the back-stepping control method is used to track the desired attitude Angle.The effectiveness of the controller is verified by both theoretical and simulation results.Finally,for the cooperative guidance law of the lift body in the terminal guidance stage,the estimated flight time is selected as the consistency variable,by combining the consistency principle and the no-singular theory,a non-singular distributed cooperative guidance law without small Angle assumption is designed,both theoretical and simulation results have verified the effectiveness of collaborative guidance under the large heading Angle.