Research On Guidance And Control Technology Of Air Defense Missile

It is symbolic for the new military revolution that the precision-guided ammunition appears in the battlefield,since the precise destruction plays an extremely important role in deterring the enemy and achieving the victory in the war quickly.Under this circumstance,the guidance and the control system is the guarantee for hitting targets by guided munitions accurately.Thus,to improve the performance of guidance and control system and to attack more precisely on maneuvering targets is the trend of the war in the future.Based on the back-stepping design method,dynamic surface control and the active disturbance rejection control theory,this paper studied and designed the autopilot,guidance law and integrated guidance and control technology of guided munitions,along with improving the response time of the system while enhancing the robustness of system.The strict Lyapunov function and mathematical simulation are used to verify the stability and practicability of the designed algorithm.The structure of classic autopilot is studied,and a method for optimizing the control parameters of the classic three loop autopilot based on genetic algorithm is proposed.Through the simulation comparison,it is verified that the optimized parameters are more robust than the parameters designed by the analytic design method.The design issue of considering the dynamic characteristics of the autopilot and the input saturation constraint guidance law are studied.In view of the problem about the lag of autopilot dynamics,the autopilot is considered as a second-order lag element to establish a mathematical model in the guidance system considering the dynamic characteristics of the autopilot.As to system input saturation problem,an auxiliary smoothing equation is designed to compensate for the effect of input saturation.An extended state observer is introduced to make online estimation and compensation of the target acceleration.The three-dimensional nonlinear guidance law is designed based on dynamic surface control method and command filter back-stepping method,and the practicality and robustness of the guidance law were verified by mathematical simulation.The design issue of integrated guidance and control controller is studied.A three-dimensional integrated guidance and control model was established which takes into account various un-certainties and disturbances such as aerodynamic forces and aerodynamic torque coefficient uncertainty,inertia uncertainty,three-channel coupling,and target maneuvering.Reduced-order extended state observer,based on the active disturbance rejection technology,is introduced to estimate and compensate a variety of errors and disturbance which exist inside and outside of the system.The swift tracking differentiator is introduced to track and differentiate the virtual control value.The swift tracking differentiator can avoid the”explosion of terms”problem that exists in the use of back-stepping method to design integrated guidance and control controller effectively.A three-dimensional robust integrated guidance and control controller is designed based on back-stepping method and active disturbance rejection control technology.The Lyapunov function is constructed to prove its stability and the simulation shows that the controller has strong robustness.