Unknown control direction hypersonic aircraft adaptive fault-tolerant control

To solve the rudder fault problem caused by saturation input, 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 rubber fault of the hypersonic aircraft, adopt K-filter to reconstruct state vectors, apply Nussbaum plus function to resolve the unknown control direction problem caused by rubber fault, 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.