L1 Adaptive integrated guidance and control for flexible hypersonic flight vehicle in the presence of dynamic uncertainties

Abstract

In this article, an integrated guidance and control design method for general nonlinear flexible hypersonic flight vehicles in the presence of dynamic uncertainties based on the [Formula: see text] adaptive state feedback control approach is presented. Initially, the 6-degree-of-freedom integrated guidance and autopilot dynamic model is organized using the combination of flexible uncertain hypersonic flight vehicle dynamic model and hypersonic flight vehicle-target relative motion model whereas aerodynamic and model uncertainties, cross-coupling effects, and disturbances are considered. The proposed integrated guidance and control method based on [Formula: see text] adaptive control scheme afterward is designed to realize control objectives including closed-loop stability, high-performance target interception, state regulation, uncertainties compensation, and reduction of the adverse flexibility effects on the overall performance. The whole Targets are proven thereupon based on the Lyapunov theory. Finally, the three-dimensional simulation results confirm the effectiveness of suggested integrated guidance and control law not only in closed-loop stability but also in high-performance target interception using the smooth control input.