Dynamic surface parameter estimation control of hypersonic aircraft with δ modification

In this paper, the robust adaptive controller is investigated for the longitudinal dynamics of a generic hypersonic aircraft in presence of uncertain parameters. The control-oriented model is adopted for design and stability analysis. By transferring the altitude command into the flight path angle trajectory, the dynamics are decomposed into velocity and attitude subsystems. Furthermore, the subsystems are written into the linearly parameterized form. Based on the δ modification parameter estimation, the dynamic inverse control is proposed via back-stepping for the attitude subsystem. The dynamic surface method is employed to provide the derivative information of the virtual control. The closed-loop system achieves uniformly ultimately bounded stability. The proposed methodology addresses the issue of controller design and stability analysis with respect to parametric model uncertainty. Simulation results show that the proposed approach achieves good tracking performance.