Research On Integrated Guidance And Control Design Of Hypersonic Flight Vehicle

The guidance and control system plays an important part in hypersonic technology,and it is one of the core technologies that the vehicle can intercept/track the target accurately.With the development of aerospace technology,the target has higher maneuverability and anti-reconnaissance and the flight environment of the vehicle is more complicated,thus the requirements for the control law design for the vehicle system are higher.In this thesis,reasonable integrated guidance and control(IGC)algorithms are proposed to achieve accurate tracking for the vehicle in different airspaces or when the target has strong maneuvering.The main contents of the thesis are as follows:Firstly,the mathematical IGC models of hypersonic flight vehicle under different conditions are established.The coordinate systems commonly used in the description of vehicle and target motion as well as the relationship between them are introduced,and the corresponding equations of the movement of vehicle are analyzed and the relative motion equations between the vehicle and the target are combined,1)The IGC model of under the aerodynamic surface control is established;2)For the flight of the vehicle in near space,the direct force control generated by the pulse engines is introduced,and the movement of the vehicle under the direct force is analyzed and the IGC model under the direct force control is obtained by combining the previous motion equation;3)As the target has strong maneuvering,the aerodynamic force/direct force blending control is adopted,and the IGC model under the blending control is established.Secondly,the integrated control algorithms are proposed for the IGC under different actuator devices.For the IGC model under the aerodynamic force only,adopting dynamic surface(DS)method the adaptive DS control law is designed for online compensation the uncertainties and external disturbances in the model,then the integrated adaptive dynamic surface control law is obtained.The effectiveness of the algorithm is proved.For the IGC model under the direct force only,the adaptive dynamic surface control(ADSC)law is designed by considering the uncertainty of modeling,external disturbance and the uncertainty as entering into the near space.Then,the ignition logic of the pulse engines is designed by integer programming method to achieve the desired control force.Finally,the effectiveness of the control algorithm is analyzed by combining the quantitation technology with Lyapunov theory.Numerical simulations show that the proposed two control methods can achieve accurate interception of the target.Thirdly,according to the aerodynamic force/direct force blending control IGC model,the integrated required ADSC law for the blending control is designed firstly,and then the direct force and aerodynamic force control parts are allocated according to the optimized control weights while the direct force control is determined by integer programming.Both theoretical analysis and numerical simulations verified that the blending control law is better than the aerodynamic force control alone as the target takes strong maneuvering.Furthermore,in case of the loss of effectiveness of the aerodynamic surface,the required ADSC for the expected performance is designed according to the blending control model,and then the fault detection algorithm is designed to estimate the actuator fault online,and a reasonable fault-tolerant control allocation method is carried out via the allocation of the direct force for fault tolerance compensation of aerodynamic force.Both theoretical analysis and numerical simulation show that the fault-tolerant control method is necessary and effective.Finally,the content of the thesis is summarized and the directions that needs to be improved and studied are prospected in the future.There are 28 figures,1 table and 64 references in this thesis.