Purpose–The purpose of this paper is to present a sliding mode attitude controller for reusable launch vehicle(RLV)which is nonlinear,coupling,and includes uncertain parameters and external disturbances.Design/method...Purpose–The purpose of this paper is to present a sliding mode attitude controller for reusable launch vehicle(RLV)which is nonlinear,coupling,and includes uncertain parameters and external disturbances.Design/methodology/approach–A smooth second-order nonsingular terminal sliding mode(NTSM)controller is proposed for RLV in reentry phase.First,a NTSM manifold is proposed for finite-time convergence.Then a smooth second sliding mode controller is designed to establish the sliding mode.An observer is utilized to estimate the lumped disturbance and the estimation result is used for feedforward compensation in the controller.Findings–It is mathematically proved that the proposed sliding mode technique makes the attitude tracking errors converge to zero in finite time and the convergence time is estimated.Simulations are made for RLV through the assumption that aerodynamic parameters and atmospheric density are perturbed.Simulation results demonstrate that the proposed control strategy is effective,leading to promising performance and robustness.Originality/value–By the proposed controller,the second-order sliding mode is established.The attitude tracking error converges to zero in a finite time.Meanwhile,the chattering is alleviated and a smooth control input is obtained.展开更多
文摘Purpose–The purpose of this paper is to present a sliding mode attitude controller for reusable launch vehicle(RLV)which is nonlinear,coupling,and includes uncertain parameters and external disturbances.Design/methodology/approach–A smooth second-order nonsingular terminal sliding mode(NTSM)controller is proposed for RLV in reentry phase.First,a NTSM manifold is proposed for finite-time convergence.Then a smooth second sliding mode controller is designed to establish the sliding mode.An observer is utilized to estimate the lumped disturbance and the estimation result is used for feedforward compensation in the controller.Findings–It is mathematically proved that the proposed sliding mode technique makes the attitude tracking errors converge to zero in finite time and the convergence time is estimated.Simulations are made for RLV through the assumption that aerodynamic parameters and atmospheric density are perturbed.Simulation results demonstrate that the proposed control strategy is effective,leading to promising performance and robustness.Originality/value–By the proposed controller,the second-order sliding mode is established.The attitude tracking error converges to zero in a finite time.Meanwhile,the chattering is alleviated and a smooth control input is obtained.
