Adjutble Lateral Thrust And Aerodynamics Blended Control System Design

More and more target with high speed and large maneuver challenge the design of guided weapons with high accuracy. On one hand, the guidance control systems are supposed to have enough response speed; on the other hand, the guided weapon should require the good adaptability to the target’s maneuver. Missiles with lateral thrust can not only significantly improve the speed of response, but also highly improve maneuvering abilities. This is an effective method against high-altitude, high-speed and large maneuvering targets, and also a key technique for present aerial defense weapons. However, the control system becomes more complicated due to the lateral thrust, the traditional control methods are no longer applicable. Therefore, the research focuses intensively on the guidance and control problems of atmospheric missiles with dual control is very significant. This project mainly studies the guidance and control problems of the dual attitude control of intercept missiles. The concrete research content is as followsFirstly, mathematical model is built based on the configuration of lateral thrust in the attitude control system. Dynamic and kinematic equations of the missile with lateral thrust are constructed according to the mathematical description of turbulent effects of lateral thrust interactions. The operation problem of the lateral jets is analyzed based of finite time H2 method. The relationship of the noises, the miss distance with different maneuvers, and the lateral operation time is derived.Second, the attitude control design method of dual control system is studied. Considering the different response characters of the lateral jets and aerodynamic control fins, the overload error dynamic allocation algorithm is given. The control subsystems of dual attitude control of intercept missiles are designed based on MPC and ADRC, respectively. The simulation results prove the proposed algorithm and methods.Finally, on the premise that the response time of acceleration and random noise are taken into account, the required accelerations are analyzed with different target maneuvers. The relationship between the acceleration ratio of the target and the missile and the acceleration response characters is studied under different target maneuvers and different maneuver time. Furthermore, the flight control system is simplified into a first order system, and the guidance methods are designed based on ADRC and SMC.