On Ballistic Missile Attitude Control Based On Sliding Mode Control Method

Ballistic Missile is playing an irreplaceable role in modern warfare and is an important military force.Since the appearance of Ballistic Missile,various countries are committed to the research of Ballistic Missile in order to enhance its tactical and technical abilities.The attitude system of Ballistic Missile is the research object of this article,and it is strong coupling,nonlinearity and uncertainty.The missile's parameters vary very large and it has the trendy characters including random interference and system unmodeling.This article based on sliding mode variable structure control,because of its predominant robustness,after decades'development,it has possessed academic foundation and been widely applied in many kinds of projects.Sliding mode control is an unusual nonlinearity control essentially,the nonlinearity shows the uncomtinuity of the control.The sliding mode design approach consists of two components.The first involves the design of a switching function so that the sliding motion satisfies design specifications.The second is concerned with the selection of a control law which will make the switching function attractive to the system state.Based on sliding mode control of the attitude system of Ballistic Missile were studied.The main works are as follows:First of all,based on the depth analysis of the missile attitude motion,the complex missile attitude equations are reasonably simplified to three subsystems including the pitch channel,the yaw channel and the roll channel.The sliding mode controller is respectively designed for each of three subsysytems.Then,use the designed controller to make control simulation,it's the simulation results validate the effectiveness of sliding mode variable structure control algorithm.Secondly,considering the global robust of the missile attitude control,the global sliding mode controller is designed for each of three subsysytems,then use the designed controllers to make control simulation,and let the control effect contrast to that of ordinary sliding mode controller.The simulation results show that the global sliding mode controller have more advantages than the ordinary one.Thirdly,considering the following response time of the missile attitude,the Backstepping sliding mode controller is designed for each of three subsysytems,then use the designed controller to make control simulation,and let the control effect contrast to that of ordinary one and global one.The simulation results show that the Backstepping sliding mode controllers have more advantages than the ordinary one and the global one in response time.At last,the thesis is summarized and the open problems for further research are also discussed.The controller is simple and easy to implement.