Flight control for hypersonic vehicle based on quasi-continuous integral high-order sliding mode

摘要

This paper first applied integral sliding mode concept to design of nonlinear robust controller for hypersonic vehicle model which is nonlinear, multivariable, and includes uncertain parameters. Firstly, the multi-input and multi-output (MIMO) quasi-continuous integral high-order sliding mode controller is proposed to track the responses of the vehicle to a step change in altitude and velocity. Furthermore, based on the simulation results, the virtual control is introduced into the design of fourth-order velocity and fifth-order altitude quasi-continuous integral sliding mode controller in order to reduce the control chattering. The arbitrary order robust sliding mode differentiator is used to calculate the missing differential which is used in the design of controller. Finally, Simulation results show that the proposed methodology guarantees the whole robustness of the system throughout an entire response of the system and achieves excellent tracking performances in spite of parameter uncertainties.