Adaptive Guidance & Disturbance-rejection Control Of High-speed High-altitude Missile

Compared with the conventional missiles,the air-to-ground/sea high-speed high-altitude missle owns a larger flight envelope,a stronger strike ability and a higher effectiveness-cost ratio,which makes it attract extensive research.In this paper,technology of the flight capability prediction,online trajectory designing,guidance and strong disturbance rejection control is explored to technically support the realization of high-altitude high-speed missile with automative and efficient task execution capability.The development trend of the air-to-ground/sea high-speed high-altitude missle is introduced at first,after which the existing ballistic planning,guidance methods and control methods are investigated and analyzed.Secondly,the overall scheme of the missle is introduced,including the parameters of the mass,launching position,mission profile,etc.The six degree of freedom dynamic model is established in the half speed system and the ballistic coordinate system,which lays the foundation for the following research.Thirdly,to satisfy the demand of flight capability prediction based on real-time flight states,the prediction model of the missile is established based on the optimal control theory,and the optimal law of the bank angle is derived.The solution of the maximum cross-range problem of given longitudinal range is transformed into a two-parameter-searching problem.In order to reduce the complexity,a solving method of the nearest distance of non reachable target point is designe d,resulting in the prediction problem transformed into a series of single-parameter-search problems,which significantly improves the feasibility of online flight capability prediction.The simulation results show that the pr oposed method can quickly predict the accessable flight envelope and have high practical application value.Then,Considering the possible initial deviations,the online trajectory design and closed-loop guidance method are studied.The performance index and constraint are analyzed to establish the optimization model at first,then an online trajectory design scheme based on pseudospectral feedback is designed.In order to achieve high-precision trajectory tracking,the adaptive dynamic surface method is utilized against large intial deviations and parameter uncertainties.Simulation results indicate the efficiency of the developed method.Trajectory tracking error is guaranteed small under user-defined initial deviations and uncertainties,which meets the accuracy requirements.Finally,In order to realize the precise attitude control against structure and aerodynamic uncertainties.Via the small perturbation methd,a linear control model is derived,and a DR-PID controller is designed.For purpose of reducing the offline design task,the active disturbance rejection attitude control s ystem is designed.Numerical simulation fully verify the effectiveness of two control systems.