Abstract:

A novel matched sliding mode attitude control method is proposed for near-space hypersonic vehicle with mismatched uncertainties. Firstly, a model with matched uncertainties is derived from matching transformation, and the derivative of system output is compensated by the estimated uncertainties from an extended disturbance observer. Secondly, a compound derivator with asymptotic stability is designed based on the disturbance observer and the frequency domain filter to obtain the derivative of system output. A novel matched sliding mode attitude control method is proposed based on variable structure control theory. Finally, the performances are assessed through a numerical simulation, and the proposed attitude control system has faster tracking performance and better robustness compared with the backstepping control system.