Adaptive Control Of Missile Reaction-jet And Aerodynamics Compound Control System

With the application of high technology in ballistic missiles,ballistic missiles usually use large maneuvering circumvention to improve survival opportunities after reentry into the atmosphere,which requires that the new air defense missiles need to achieve direct interception accuracy when they intercept targets.The aerodynamic classical guidance law can not meet this requirement,so need to adopt the method of direct lateral force and aerodynamic compound control,in order to obtain stronger ability to intercept a Maneuvering Missile and faster response,the interceptor missile has two control force: missile tail aerodynamic rudder is generated,and the direct force to produce a solid engine installed in the vicinity of the missile.Due to aerodynamic compound control system is continuous,and the direct force part is discrete,so the controller design in the use of straight / aerodynamic control method,the stability of the missile control system is a great challenge,the direct force /aerodynamic compound control system as the research object,studies the problem of terminal composite control guidance,including the system stability analysis and controller design problem.The main contents of this paper are as follows:1.For the direct force / aerodynamic composite control system,the controller design is carried out by sliding mode variable structure method,and the controller design method with exponential convergence is used to improve the stability of the composite control system and realize the closed loop design of the whole control system.2.The adaptive sliding mode variable structure control method is used to improve the stability of the system,which is caused by the traditional variable structure control.3.In view of the external disturbance problem in the missile compound control system,the adaptive neural network sliding mode control method is adopted to eliminate the nonlinear term in the modeling.Secondly,the variable structure control is used to realize the composite control design of the missile.At the same time,the direct force part is designed by fuzzy control to improve the use efficiency of the pulse engine.Rate.4.In view of the disturbance problem in the missile compound control system,an observer is first constructed to estimate the system state.Secondly,the stability of the closed-loop system is guaranteed by the design of integral sliding surface and anobserver based adaptive sliding mode controller to eliminate all kinds of uncertainties in the missile compound control system.Finally,a simulation example shows that the control method can effectively improve the missile's corresponding speed and increase the overload capacity and stability of the missile.