Adaptive failure compensation tracking controller design for hypersonic vehicle based on high-order fully actuated system theory

Hypersonic vehicle has great application potential and economic value both in military and civil use. The design of the controller is the key and core part of realising hypersonic technology. This paper designs the height and speed tracking controller of the longitudinal model of the hypersonic aircraft cruise stage based on the theory of the hypersonic vehicle in the dynamic model of the NASA Langley laboratory and using the theory of the high-order fully actuated system. At the same time, when the avehicle has double rudder surface redundancy, considering the size of the fault, mode and time unknown jammed failure on the rudder surface, the parameter adaptive law is introduced to complete the height fault tolerance tracking control of the aircraft to ensure that the system can realise fault self-compensation and improve the reliability of the controller. According to Lyapunov stability theorem, the stability of the system is proved. Finally, the simulation is used to further verify the theoretical rationality and feasibility, and the tracking curve shows that the designed controller has a good control effect.