Terminal Guidance Law Design Based On Side Jet And Aerodynamic Compound Control

The compound control with side Jet and aerodynamic force for advanced anti-aircraft missiles is a key technique of guidance and control in the terminal phase of interception. This thesis studies the solution of control and guidance about the trajectory compound control interceptor form two aspects:Which are normal overload directive decomposition and design of guidance law. The main work includes:Analysis of the two main reasons which could enlarge the quantity of off-target in the terminal phase of the interceptor missile guidance and gives their own solutions:At the time terminal guidance to start, change rate of sight angle were generally higher while the aerodynamic overload needs longer time to establish. Switches on the engine of lateral force and uses a threshold method for decomposition strategy. In regard to the failure of lead head at the last paragraph, takes advantage of the angular acceleration which provided before the guidance loop is disconnected to establish the control instructions of lateral force channel.The miss distance must be growing while uses the traditional guidance law for interception in the high-speed and great mobility incoming missile. The thesis proposed an improved optimal sliding mode guidance law On the basis of linearization of the model of the relative motion. The guidance law allows law-guided instructions can be directly made to the normal overload. Additional, the guidance law combines the advantages of optimal control and sliding-mode control and achieved very good control effect, which have valuable non-sensitive while cope with interference and changes in system parameters. At last the numerical simulation results verify the effectiveness of the design.Finally, a missile interception animated user graphical interface is developed under MATLAB simulation platform, which can show the process of missile intercept target vividly.