Fault-tolerant controller design for one hypersonic aircraft with sensor failure

Abstract

Compared with traditional aircraft, the near space hypersonic aircraft control system has a very prominent strong coupling, strong nonlinear, time-varying dynamics characteristics. In its research and design process, the following factors must be considered: plant elastic deformation, multi-inputs multi-outputs, aerodynamatic parameters uncertain, and a variety of temperature sensor failure and other causes of fever and some actuator failures and other issues, so the research and design of aircraft control systems faces unprecedented difficulties and challenges of the Institute. To solve the angular rate sensor failure problems encountered for hypersonic aircraft during flight, the nonlinear observer and controller are designed respectively. Under the condition of output measureable only, the dissertation designs a new standard expanded Luenberger observer to estimate convergence state vector, and brings forward a new strong adaptive control law based on dynamic surface adaptive backstepping control to guarantee the system boundedness. In the course of adaptive backstepping design, the dissertation employes the dynamic surface control strategy to eliminate the traditional inversion of the dimesion explosion question by introducing a series of first order filters to obtain the differentiation of the virtual control inputs. The six degrees of freedom simulation of hypersonic aircraft is used to verify the above theory.