The present invention discloses a hypersonic 
flight vehicle adaptive fault-tolerant control method of considering 
attack angle constraint which is used to solve the technical problem that a conventional hypersonic 
flight vehicle control method is poor in practicality. The method of the technical scheme is characterized by limiting a 
flight vehicle attack angle within a given range to guarantee the normal work of a 
scramjet engine; aiming at the fault case of an 
actuator, giving out a robust adaptive adjusting and controlling strategy, and utilizing a redundancy control mechanism to effectively compensate the influence brought by the failure to guarantee the safety of a 
system. Aiming at the model uncertainty, the method of the present invention combines the amplitude limiting design and a Barrier type 
lyapunov function to give out a controller, thereby being able to guarantee that the 
attack angle can be restrained within the given range, and guaranteeing the normal work of the 
scramjet engine. By using a neural network to learn and process the model uncertainty to substitute for the linear parameterization 
processing, the model analysis is simplified, and the actual application is convenient. Aiming at the fault case of the 
actuator, the redundancy control mechanism is utilized to compensate the influence brought by the faults effectively and adaptively, thereby being good in practicality.