一类高超声速飞行器自适应容错控制器设计

Abstract

The hypersonic aircraft control system design must deal with the extra prominent dynamics characteristics: highly coupled, strongly nonlinear, time variational and so on. Thus, during the course of control system study and design for the hypersonic aircraft, the following factors must be considered: plant elastic deformation, multi-inputs multi-outputs, uncertain aerodynamatic parameters, sensors and actuator failures, which is differ from the traditional aircrafts control system design. To solve the failure problem of the actuator in the course of the hypersonic aircraft flight, one kind of adaptive backstepping fault-tolerant control method based on the observer and controller designed synthetically is brought up. At first, 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, then adopt K -filter to reconstruct state vectors. When only the output is measureable, the dissertation designs one new observer to estimate convergence state vector and design the adaptive control law to guarantee the system boundedness. In the course of adaptive backstepping design, the dissertation employes the dynamic surface control 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. Both theory analysis and simulation verification show the simplicity and effectiveness of this method. At last the pitch channel of hypersonic aircraft is studied as an example to validate the above theory.