Research On Aerodynamic Online Identification And Trajectory Optimization Based On Integrated Navigation For Boost-glide Missile

Boost gliding missile with its long range,high precision,flexible and flexible characteristics of the domestic and foreign research has become a hot topic.However,the main range of boost gliding missile is concentrated in the atmosphere,the flight environment is very complex,the difference of aerodynamic parameters is quite obvious,and the atmospheric disturbance is quite obvious.These factors have a significant bad influence on the flight stability and guidance precision of the missile.And because of the rapid development of the anti-missile system in recent years,under the deterrence of the anti-missile system,the trajectory planning based on the off-line planning is difficult to adapt to the long-term maneuvering and defensive transition of the gliding aircraft in the atmosphere,Maneuvering targets and the need for re-planning of ballistic trajectories after target change have constrained the flexibility,penetration performance and operational flexibility of missiles.Because the aerodynamic environment of the aerodynamic data acquisition method,such as ground wind tunnel test,numerical simulation calculation and flight test,can not be exactly equal to the aerodynamic parameters in the real environment of missile flight,So the missile in the design process used in the aerodynamic parameters and the actual flight of the aerodynamic parameters are inconsistent.In order to improve the flight performance of missiles,it is essential to obtain accurate aerodynamic parameters.Therefore,based on how to obtain accurate aerodynamic parameters,this paper puts forward the on-line identification and trajectory on-line optimization method of aerodynamic parameters based on integrated navigation.The navigation parameters calculated by the GPS-INS integrated navigation system are applied to the aerodynamic parameter identification,and then the aerodynamic parameters identified by the aerodynamic parameters are applied to the trajectory online planning so that the flight trajectories are based entirely on the real flight environment and The application of aerodynamic parameter identification results to the guidance control system can greatly improve the accuracy of missile guidance control system.And online planning a new trajectory will play an important role in the future of the war when the mission changes.In this paper,the navigation model and error propagation model of GPS-INS integrated navigation system are established in the navigation coordinate system.The observation equation of GPS-INS integrated navigation system is given,and an extended Kalman filter method based on robustness is proposed.The mathematical simulation of the integrated navigation system is carried out.It is proved that the GPS-INS integrated navigation system based on the extended Kalman filter method can effectively solve the navigation problem of the gliding section of the gliding glider.The aerodynamic parameter identification system equation,observation equation and aerodynamic parameter model are established.The extended Kalman filter method based on extended increment is used to study the on-line identification of aerodynamic parameters under under-observation conditions.The aerodynamic parameters were analyzed by on-line identification of pneumatic parameters using the navigation information such as speed and overload obtained by GPS-INS integrated navigation system.The results show that the aerodynamic parameter identification method based on extended incremental Kalman filter can effectively solve the problem of on-line identification of aerodynamic parameters.The results show that the Kalman filter method based on extended incremental Kalman filtering method and the extended Kalman filter method are used to analyze the aerodynamic parameters.TheThe three-degree-of-freedom reentry equation of the gliding section of the gliding glider is established,and the optimal angle-of-attack model is designed to determine the constraints of the gliding section to boost the gliding missile and determine the objective function of the trajectory on-line planning.A two-loop iterative optimization method based on outer loop as genetic algorithm and inner ring for improved Newton iteration method is used to simulate the trajectory on-line planning of gliding section of gliding glider.The results show that the double-loop iterative optimization method can effectively solve the problem of trajectory on-line programming,and the aerodynamic parameters are identified by the online identification method.The results show that the aerodynamic parameters based on the aerodynamic parameters of the aerodynamic parameters are compared with the results of the on-line planning simulation based on CAV aerodynamic parameters.Out of the aerodynamic parameters help to improve the accuracy of ballistic online planning.