Abstract
A nonlinear attitude control method is proposed for hypersonic re-entry vehicle by using a sliding mode dynamic inversion control approach. The objective of this control scheme is to deal with external disturbance and strong couplings during the flight of the hypersonic vehicle. Based on the attitude dynamic and kinetic equations of hypersonic vehicle, a nonlinear model for the attitude control design is established. A dynamic inversion control is then adopted to design the hypersonic vehicle attitude control law by using a sliding mode approach. The stability conditions of hypersonic gliding vehicle attitude control system are obtained by means of the Lyapunov function method. Simulation results demonstrate excellent performances of the proposed controller in terms of rapidity, accuracy and stability, meanwhile, the influence of the sliding mode parameter on the performances is discussed in detail.
Published Version
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