Hypersonic Aircraft Nonlinear Fault-tolerant Controller Design

One hypersonic aircraft nonlinear observer and controller are designed synthetically to solve the part of actuator failure problem. The research model is developed based on a SISO output feedback nonlinear unobservered minimum phase system. K - filter is adopted to reconstruct state vectors, adaptive control law is designed to guarantee the system boundedness. Dynamic surface control is employed strategy to eliminate the explosion of terms by introducing a series of first order filters to obtain the differentiation of the virtual control inputs. Both theory analysis and simulation verification show the simpleness and effective of this method.