Adaptive fault-tolerant controller design for a class of hypersonic aircraft with actuator failure

To solve the part of actuator failure problem, the nonlinear observer and controller are designed synthetically. We develop the research model based on a SISO output feedback nonlinear unobservered minimum phase system under the condition of single channel actuator failure of the hypersonic aircraft, adopt K - filter to reconstruct state vectors, design the adaptive control law to guarantee the system boundedness. The pitch channel of hypersonic aircraft is studied as an example to validate above theory.