Research On Missile Autopilot Control Algorithm

With the development of Science and technology,especially the aerospace technology,the modern battlefield environment has been becoming more and more complex,the future tactical missiles is required to have higher technical indicators to solve a series of problems such as the larger target mobility,the larger airspace and the low altitude flight.The task of missile autopilot is to overcome all kinds of interference in the process of missile flight,and control the missile attitude accurately in time,so that the missile can fly stably and accurately strike the target.In order to improve the robustness,the anti-jamming ability and the tracking ability of missile automatic driving,the main works are summarized as follows:By analyzing the stress of the missile,the kinematics and dynamics equations of the missile are established in the case of coupling,and the closer to the actual mathematical model of the missile is obtained.Finally through linearization,the mathematical model of BTT missile is more suitable to design the controller.After the missile model is decoupled and linearized at the trajectory feature point,the mathematical model of each channel is obtained.The fuzzy control theory is used to design the fuzzy PID control autopilot;the fuzzy and variable universe theory is used to design the variable universe PID control autopilot;the state feedback H? control autopilot is designed by solving the linear matrix inequality(LMI).considering the interference and the perturbation of the aerodynamic parameters in the flight process,the control performance of the three autopilot designed is compared with each other in the more close to the actual situation.From the simulation results,the three autopilots all can achieve the effective guidance of the missile guidance instructions.Among them,State feedback H? controller is designed based on linear matrix inequality(LMI),without too much restriction on the system model,the controller is obtained only by solving the linear matrix inequality.Moreover,the dynamic response of the autopilot in the command tracking is fast,and the autopilot has a good immunity on the aerodynamic parameter perturbation and the interference in the missile flight,which is more suitable for missile attitude control.According to the established mathematical model of missile under the condition of coupling,regard the coupling between channels as interference,a three-channel state feedback H? control autopilot is designed by solving the linear matrix inequality(LMI),the three-channel simulation model of full coupling is established and combined with simulation research.The simulation results show that the design of the state feedback H? control can achieve tracking of the missile guidance command effectively and meet the requirements of the BTT missile control.In summary,compare fuzzy PID control with the variable universe fuzzy PID control and State feedback H? control,the state feedback H? control missile autopilot can achieve better control effect in condition of larger interference and variable parameters.