Switching control design for a hypersonic flight vehicle

Abstract

An adaptive switching controller is designed and analyzed for the longitudinal dynamics of a generic hypersonic air vehicle in the whole cruise phase rather than a trimmed working condition. This model is nonlinear, multivariable and unstable. The adaptive controller presented in this paper consists of a local linearization method, an adaptive switching law and a nonlinear feedback control law. Furthermore, a theorem is obtained that the closed-loop system under the adaptive switching control is stable.