Nonlinear observer and controller design with actuator failure for one hypersonic aircraft

To solve the part of actuator failure problem, the hypersonic aircraft nonlinear observer and controller are designed synthetically. We develop the research model based on a SISO output feedback nonlinear unobserved 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. 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. Lyapunov stability theorem guarantees the error uniformly bound. The pitch channel of hypersonic aircraft is studied as an example to validate above theory. Both theory analysis and simulation verification show the simpleness and effective of this method.