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This work presents a nonlinear adaptive dynamic surface air speed and a flight path angle control design procedure for the longitudinal dynamics of a generic hypersonic flight vehicle. The proposed design scheme takes into account the magnitude, rate, and bandwidth constraints on the actuator signals. A new approach is used to enhance tracking performance and avoid a large initial control signal. The uncertain nonlinear functions in the flight vehicle model are approximated by using radial basis function neural networks. A detailed stability analysis of the designed controllers shows that all the signals of the closed‐loop system are uniformly ultimately bounded. The robust performance of the design scheme is verified through numerical simulations of the flight vehicle model for various parameter variation test cases. Copyright © 2011 John Wiley and Sons Asia Pte Ltd and Chinese Automatic Control Society

In this brief, we propose a dynamic surface control with actuator failure compensation for a class of feedback linearizable systems with locally Lipschitz nonlinearities. First, a dynamic surface state feedback control scheme is designed, which incorporates radial basis function networks in a novel approach, to compensate system uncertainties and dynamic changes induced by actuator failures. Then, an output feedback controller is obtained by means of high-gain observers. It is proved that our control schemes guarantee the uniform ultimate boundedness of the system, and that the output tracking error converges to an arbitrarily small residual set. Finally, a simulation is carried out to illustrate the performance of the designed control schemes.

A Dynamic Surface Control (DSC) technique combined with Neural Network adaptive framework is presented, to design a robust longitudinal dynamics controller for a generic nonlinear air-breathing hypersonic flight vehicle (AHFV) model. The dynamic model of the AHFV is transformed into a pure feedback form with uncertainties included in the formulation. A detailed stability analysis is carried out to prove that all the signals of the closed loop system are uniformly ultimately bounded. The robustness and performance of the designed controller is validated through numerical simulation of the AHFV model for trimmed cruise condition of 110,000 ft and Mach 15, in which the responses of the vehicle to a step change in air speed and altitude are analyzed for nominal and worst case parameter uncertainties.