The Experts below are selected from a list of 309 Experts worldwide ranked by ideXlab platform

Yongzhi Sheng - One of the best experts on this subject based on the ideXlab platform.

  • neural network based adaptive fuzzy pid type sliding mode attitude control for a Reentry Vehicle
    International Journal of Control Automation and Systems, 2017
    Co-Authors: Zhen Jin, Yongzhi Sheng, Jiabin Chen, Xiangdong Liu
    Abstract:

    This work investigates the attitude control of Reentry Vehicle under modeling inaccuracies and external disturbances. A robust adaptive fuzzy PID-type sliding mode control (AFPID-SMC) is designed with the utilization of radial basis function (RBF) neural network. In order to improve the transient performance and ensure small steady state tracking error, the gain parameters of PID-type sliding mode manifold are adjusted online by using adaptive fuzzy logic system (FLS). Additionally, the designed new adaptive law can ensure that the closed-loop system is asymptotically stable. Meanwhile, the problem of the actuator saturation, caused by integral term of sliding mode manifold, is avoided even under large initial tracking error. Furthermore, to eliminate the need of a priori knowledge of the disturbance upper bound, RBF neural network observer is used to estimate the disturbance information. The stability of the closed-loop system is proved via Lyapunov direct approach. Finally, the numerical simulations verify that the proposed controller is better than conventional PID-type SMC in terms of improving the transient performance and robustness.

  • Improved nonsingular terminal sliding mode attitude tracking control for Reentry Vehicle
    2016 35th Chinese Control Conference (CCC), 2016
    Co-Authors: Yifeng Cheng, Yongzhi Sheng
    Abstract:

    This paper investigates the attitude tracking control problem of Reentry Vehicle with modeling inaccuracies and external disturbances. An improved nonsingular terminal sliding mode control method is presented, and a faster convergence rate is obtained in comparison with the conventional nonsingular terminal sliding mode control (NTSM). By the proposed control strategy, the possible singularity during the control phase is avoided, and robustness is also guaranteed. Simulation is made for a Reentry Vehicle in the condition aerodynamic parameters and atmospheric density are perturbed. The results show the effectiveness of the proposed strategies.

  • nonsingular finite time second order sliding mode attitude control for Reentry Vehicle
    International Journal of Control Automation and Systems, 2015
    Co-Authors: Yongzhi Sheng, Jie Geng, Liang Wang
    Abstract:

    This paper presents nonlinear robust flight control strategies for the Reentry Vehicle which is nonlinear, coupling, and includes parameter uncertainties and external disturbances. Firstly, a finite-time second order sliding mode attitude control strategy is pointed out with the introduction of a nonsingular finite-time sliding mode manifold. By the proposed controller, the attitude tracking errors are mathematically proved to converge to zero within finite time and the chattering of sliding mode controller is alleviated without any deterioration of robustness and accuracy. For further alleviation of chattering, a smooth second order sliding mode attitude control strategy is then designed based on an improved nonsingular finite-time sliding mode manifold. Finally, the proposed strategies are applied to the attitude control of X-33 RLV in the Reentry phase to verify the validity and robustness of the proposed strategies.

  • continuous time varying sliding mode based attitude control for Reentry Vehicle
    Proceedings of the Institution of Mechanical Engineers Part G: Journal of Aerospace Engineering, 2015
    Co-Authors: Liang Wang, Yongzhi Sheng
    Abstract:

    The attitude control for Reentry Vehicle is responsible for the robust operation to avoid the major deterioration from parametric uncertainties and external disturbances. Targeting these practical issues, both the cases with and without a priori knowledge of upper bound on the lumped uncertainty (i.e. the joint effect caused by external disturbance and inertia matrix uncertainty) are addressed, and correspondingly two continuous time-varying sliding mode based attitude controller design strategies are proposed to achieve the robust tracking of the attitude commands while alleviating the control chattering. Firstly, to deal with the case where the upper bound on the second derivative of the lumped uncertainty is known in advance, a nonlinear disturbance observer based continuous time-varying sliding mode control algorithm is developed so that the asymptotic stability of the closed system is guaranteed. Furthermore, in order to address the more practical case that the upper bound on the lumped uncertainty i...

  • finite time sliding mode attitude control for a Reentry Vehicle with blended aerodynamic surfaces and a reaction control system
    Chinese Journal of Aeronautics, 2014
    Co-Authors: Jie Geng, Yongzhi Sheng
    Abstract:

    Abstract This paper proposes a finite-time robust flight controller, targeting for a Reentry Vehicle with blended aerodynamic surfaces and a reaction control system (RCS). Firstly, a novel finite-time attitude controller is pointed out with the introduction of a nonsingular finite-time sliding mode manifold. The attitude tracking errors are mathematically proved to converge to zero within finite time which can be estimated. In order to improve the performance, a second-order finite-time sliding mode controller is further developed to effectively alleviate chattering without any deterioration of robustness and accuracy. Moreover, an optimization control allocation algorithm, using linear programming and a pulse-width pulse-frequency (PWPF) modulator, is designed to allocate torque commands for all the aerodynamic surface deflections and on–off switching-states of RCS thrusters. Simulations are provided for the Reentry Vehicle considering uncertain parameters and external disturbances for practical purposes, and the results demonstrate the effectiveness and robustness of the attitude control system.

Honglun Wang - One of the best experts on this subject based on the ideXlab platform.

  • fault tolerant control for over actuated hypersonic Reentry Vehicle subject to multiple disturbances and actuator faults
    Aerospace Science and Technology, 2019
    Co-Authors: Yue Yu, Honglun Wang, Na Li
    Abstract:

    Abstract In this paper, a fault-tolerant control scheme is proposed for attitude tracking problem of hypersonic Reentry Vehicle subjected to multiple disturbances and time-varying actuator faults. For convenience of fault-tolerant controller design, conventional hypersonic Reentry Vehicle model is transformed into control-oriented model by incorporating actuator faults into lumped disturbance. Based on the lumped disturbance estimate provided by high order sliding mode observer, fault-tolerant controllers are developed within the frame of active disturbance rejection control in attitude loop and angular rate loop according to time-scale separation and singular perturbation principle. Then, the desired control moment is allocated to actuators based on recurrent neural network. With the well-designed fault-tolerant controllers and control allocation, a novel meta-heuristic dynamic adaptation salp swarm algorithm is employed to optimize control parameters to achieve minimum attitude tracking error. Comparative simulations are conducted to verify the effectiveness of the developed dynamic adaptation salp swarm algorithm and the investigated fault-tolerant control scheme.

  • reduced order linear extended state observer based trajectory linearization control for hypersonic Reentry Vehicle under high maneuver flight with multiple disturbances
    2018 IEEE CSAA Guidance Navigation and Control Conference (CGNCC), 2018
    Co-Authors: Huiping Zhang, Yue Yu, Honglun Wang
    Abstract:

    In this paper, attitude tracking problem of hypersonic Reentry Vehicle (HRV) under high maneuver flight with multiple disturbances is considered. To enhance the anti-disturbance ability of traditional trajectory linearization control (TLC) and retain a simple control structure, a novel reduced-order linear extended state observer (RLESO) based TLC scheme is proposed. The system is divided into attitude loop and angular rate loop. In each loop, nominal control and feedback linearization (FL) control are designed in the framework of TLC. In FL control law design, the lumped disturbance is estimated and compensated by RLESO to counteract the effects of disturbance. Extensive simulations are conducted to verify the efficacy of the proposed RLESO based TLC scheme.

  • finite time model assisted active disturbance rejection control with a novel parameters optimizer for hypersonic Reentry Vehicle subject to multiple disturbances
    Aerospace Science and Technology, 2018
    Co-Authors: Yue Yu, Honglun Wang, Na Li, Huiping Zhang, Zikang Su, Xingling Shao
    Abstract:

    Abstract In this paper, a scheme which combines finite-time model-assisted active disturbance rejection control and novel greedy criterion-based salp swarm algorithm is developed for attitude tracking problem of hypersonic Reentry Vehicle with multiple disturbances. To simplify control structure, the control scheme is designed within the framework of active disturbance rejection control completely. To lessen tuning parameters, a sigmoid function-based tracking differentiator is employed to generate a more realizable attitude transient profile instead of utilizing conventional nonlinear tracking differentiator. Taking known model information as model-assisted term, finite-time model-assisted extended state observers are constructed to estimate the lumped disturbance in attitude and angular rate loop with employment of function fal. To achieve rapid response and strong robustness, finite-time model-assisted control laws are derived by utilizing function fhan. Finally, a novel greedy criterion-based salp swarm algorithm is used to optimize control parameters in finite-time model-assisted control laws to achieve optimal solution that minimizes the tracking error and energy consumption. Comparative simulations are conducted to illustrate the effectiveness of the proposed scheme.

  • back stepping robust trajectory linearization control for hypersonic Reentry Vehicle via novel tracking differentiator
    Journal of The Franklin Institute-engineering and Applied Mathematics, 2016
    Co-Authors: Xingling Shao, Honglun Wang
    Abstract:

    Abstract This paper proposes a back-stepping robust trajectory linearization control (TLC) design for hypersonic Reentry Vehicle (HRV) attitude tracking problem from a novel tracking differentiator perspective. First, the attitude kinematics and dynamics for HRV is formulated and rewritten in feedback form with mismatched and matched uncertainties introduced by variations of various aerodynamic coefficients. Second, a sigmoid function based novel tracking differentiator (STD) with global fast convergence property, simple structure and chattering-free in differential estimation is developed to handle the “explosion of term” problem in back-stepping TLC design. In addition, dynamical performance and noise-attenuation ability of STD are analyzed in frequency domain by describing function method. Third, how to convert between sigmoid function based disturbance observer (SDO) and STD is given, and based on the estimates of uncertainties provided by SDO in attitude and angular rate loop, the back-stepping robust TLC is synthesized to track the respective commands in dual-loop. Then, the stability of the composite SDO-enhanced back-stepping TLC approach is established. Finally, extensive simulation results are presented to demonstrate the effectiveness of the proposed control strategy in improving disturbance attenuation ability and performance robustness against multiple uncertainties.

  • enhanced trajectory linearization control based advanced guidance and control for hypersonic Reentry Vehicle with multiple disturbances
    Aerospace Science and Technology, 2015
    Co-Authors: Xingling Shao, Honglun Wang, Huiping Zhang
    Abstract:

    Abstract In this paper, the guidance and control problem for hypersonic Reentry Vehicle (HRV) in the presence of control constraints and multiple disturbances is handled based on unified enhanced trajectory linearization control (TLC) framework under reference-tracking methodology. First, based on the nominal trajectory and open-loop command generated by Gauss pseudo-spectral method (GPM), a time-varying feedback guidance law with integral action is synthesized to stabilize the tracking error dynamics along the nominal trajectory under the framework of TLC. Second, to improve the robustness of attitude and angular rate loop, variations of various aerodynamic coefficients and external disturbances are considered as lumped uncertainties, reduced-order linear extended state observers (LESO) with given model information are constructed to estimate the lumped uncertainties in each loop, respectively. In addition, comparisons between the estimation efficiency of LESO and reduced-order LESO are carried out. Then augmented with the disturbance estimates and TLC control law, tracking errors of the rotational dynamics can be actively rejected without sacrificing nominal performances. More importantly, fewer control consumption and smooth transient performances are achieved by using nonlinear tracking differentiator (TD) in attitude loop. The stability of the resulting closed-loop system is well established based on Lyapunov stability theory. Finally, the effectiveness of the proposed advanced guidance and control strategy is verified through extensive simulations on the six-degree-of-freedom Reentry flight.

Xingling Shao - One of the best experts on this subject based on the ideXlab platform.

  • finite time model assisted active disturbance rejection control with a novel parameters optimizer for hypersonic Reentry Vehicle subject to multiple disturbances
    Aerospace Science and Technology, 2018
    Co-Authors: Yue Yu, Honglun Wang, Na Li, Huiping Zhang, Zikang Su, Xingling Shao
    Abstract:

    Abstract In this paper, a scheme which combines finite-time model-assisted active disturbance rejection control and novel greedy criterion-based salp swarm algorithm is developed for attitude tracking problem of hypersonic Reentry Vehicle with multiple disturbances. To simplify control structure, the control scheme is designed within the framework of active disturbance rejection control completely. To lessen tuning parameters, a sigmoid function-based tracking differentiator is employed to generate a more realizable attitude transient profile instead of utilizing conventional nonlinear tracking differentiator. Taking known model information as model-assisted term, finite-time model-assisted extended state observers are constructed to estimate the lumped disturbance in attitude and angular rate loop with employment of function fal. To achieve rapid response and strong robustness, finite-time model-assisted control laws are derived by utilizing function fhan. Finally, a novel greedy criterion-based salp swarm algorithm is used to optimize control parameters in finite-time model-assisted control laws to achieve optimal solution that minimizes the tracking error and energy consumption. Comparative simulations are conducted to illustrate the effectiveness of the proposed scheme.

  • back stepping robust trajectory linearization control for hypersonic Reentry Vehicle via novel tracking differentiator
    Journal of The Franklin Institute-engineering and Applied Mathematics, 2016
    Co-Authors: Xingling Shao, Honglun Wang
    Abstract:

    Abstract This paper proposes a back-stepping robust trajectory linearization control (TLC) design for hypersonic Reentry Vehicle (HRV) attitude tracking problem from a novel tracking differentiator perspective. First, the attitude kinematics and dynamics for HRV is formulated and rewritten in feedback form with mismatched and matched uncertainties introduced by variations of various aerodynamic coefficients. Second, a sigmoid function based novel tracking differentiator (STD) with global fast convergence property, simple structure and chattering-free in differential estimation is developed to handle the “explosion of term” problem in back-stepping TLC design. In addition, dynamical performance and noise-attenuation ability of STD are analyzed in frequency domain by describing function method. Third, how to convert between sigmoid function based disturbance observer (SDO) and STD is given, and based on the estimates of uncertainties provided by SDO in attitude and angular rate loop, the back-stepping robust TLC is synthesized to track the respective commands in dual-loop. Then, the stability of the composite SDO-enhanced back-stepping TLC approach is established. Finally, extensive simulation results are presented to demonstrate the effectiveness of the proposed control strategy in improving disturbance attenuation ability and performance robustness against multiple uncertainties.

  • enhanced trajectory linearization control based advanced guidance and control for hypersonic Reentry Vehicle with multiple disturbances
    Aerospace Science and Technology, 2015
    Co-Authors: Xingling Shao, Honglun Wang, Huiping Zhang
    Abstract:

    Abstract In this paper, the guidance and control problem for hypersonic Reentry Vehicle (HRV) in the presence of control constraints and multiple disturbances is handled based on unified enhanced trajectory linearization control (TLC) framework under reference-tracking methodology. First, based on the nominal trajectory and open-loop command generated by Gauss pseudo-spectral method (GPM), a time-varying feedback guidance law with integral action is synthesized to stabilize the tracking error dynamics along the nominal trajectory under the framework of TLC. Second, to improve the robustness of attitude and angular rate loop, variations of various aerodynamic coefficients and external disturbances are considered as lumped uncertainties, reduced-order linear extended state observers (LESO) with given model information are constructed to estimate the lumped uncertainties in each loop, respectively. In addition, comparisons between the estimation efficiency of LESO and reduced-order LESO are carried out. Then augmented with the disturbance estimates and TLC control law, tracking errors of the rotational dynamics can be actively rejected without sacrificing nominal performances. More importantly, fewer control consumption and smooth transient performances are achieved by using nonlinear tracking differentiator (TD) in attitude loop. The stability of the resulting closed-loop system is well established based on Lyapunov stability theory. Finally, the effectiveness of the proposed advanced guidance and control strategy is verified through extensive simulations on the six-degree-of-freedom Reentry flight.

  • active disturbance rejection based trajectory linearization control for hypersonic Reentry Vehicle with bounded uncertainties
    Isa Transactions, 2015
    Co-Authors: Xingling Shao, Honglun Wang
    Abstract:

    Abstract This paper investigates a novel compound control scheme combined with the advantages of trajectory linearization control (TLC) and alternative active disturbance rejection control (ADRC) for hypersonic Reentry Vehicle (HRV) attitude tracking system with bounded uncertainties. Firstly, in order to overcome actuator saturation problem, nonlinear tracking differentiator (TD) is applied in the attitude loop to achieve fewer control consumption. Then, linear extended state observers (LESO) are constructed to estimate the uncertainties acting on the LTV system in the attitude and angular rate loop. In addition, feedback linearization (FL) based controllers are designed using estimates of uncertainties generated by LESO in each loop, which enable the tracking error for closed-loop system in the presence of large uncertainties to converge to the residual set of the origin asymptotically. Finally, the compound controllers are derived by integrating with the nominal controller for open-loop nonlinear system and FL based controller. Also, comparisons and simulation results are presented to illustrate the effectiveness of the control strategy.

Wang Honglun - One of the best experts on this subject based on the ideXlab platform.

  • sliding mode based trajectory linearization control for hypersonic Reentry Vehicle via extended disturbance observer
    Isa Transactions, 2014
    Co-Authors: Shao Xingling, Wang Honglun
    Abstract:

    Abstract This paper proposes a novel hybrid control framework by combing observer-based sliding mode control (SMC) with trajectory linearization control (TLC) for hypersonic Reentry Vehicle (HRV) attitude tracking problem. First, fewer control consumption is achieved using nonlinear tracking differentiator (TD) in the attitude loop. Second, a novel SMC that employs extended disturbance observer (EDO) to counteract the effect of uncertainties using a new sliding surface which includes the estimation error is integrated to address the tracking error stabilization issues in the attitude and angular rate loop, respectively. In addition, new results associated with EDO are examined in terms of dynamic response and noise-tolerant performance, as well as estimation accuracy. The key feature of the proposed compound control approach is that chattering free tracking performance with high accuracy can be ensured for HRV in the presence of multiple uncertainties under control constraints. Based on finite time convergence stability theory, the stability of the resulting closed-loop system is well established. Also, comparisons and extensive simulation results are presented to demonstrate the effectiveness of the control strategy.

Jie Geng - One of the best experts on this subject based on the ideXlab platform.

  • nonsingular finite time second order sliding mode attitude control for Reentry Vehicle
    International Journal of Control Automation and Systems, 2015
    Co-Authors: Yongzhi Sheng, Jie Geng, Liang Wang
    Abstract:

    This paper presents nonlinear robust flight control strategies for the Reentry Vehicle which is nonlinear, coupling, and includes parameter uncertainties and external disturbances. Firstly, a finite-time second order sliding mode attitude control strategy is pointed out with the introduction of a nonsingular finite-time sliding mode manifold. By the proposed controller, the attitude tracking errors are mathematically proved to converge to zero within finite time and the chattering of sliding mode controller is alleviated without any deterioration of robustness and accuracy. For further alleviation of chattering, a smooth second order sliding mode attitude control strategy is then designed based on an improved nonsingular finite-time sliding mode manifold. Finally, the proposed strategies are applied to the attitude control of X-33 RLV in the Reentry phase to verify the validity and robustness of the proposed strategies.

  • finite time sliding mode attitude control for a Reentry Vehicle with blended aerodynamic surfaces and a reaction control system
    Chinese Journal of Aeronautics, 2014
    Co-Authors: Jie Geng, Yongzhi Sheng
    Abstract:

    Abstract This paper proposes a finite-time robust flight controller, targeting for a Reentry Vehicle with blended aerodynamic surfaces and a reaction control system (RCS). Firstly, a novel finite-time attitude controller is pointed out with the introduction of a nonsingular finite-time sliding mode manifold. The attitude tracking errors are mathematically proved to converge to zero within finite time which can be estimated. In order to improve the performance, a second-order finite-time sliding mode controller is further developed to effectively alleviate chattering without any deterioration of robustness and accuracy. Moreover, an optimization control allocation algorithm, using linear programming and a pulse-width pulse-frequency (PWPF) modulator, is designed to allocate torque commands for all the aerodynamic surface deflections and on–off switching-states of RCS thrusters. Simulations are provided for the Reentry Vehicle considering uncertain parameters and external disturbances for practical purposes, and the results demonstrate the effectiveness and robustness of the attitude control system.

  • second order time varying sliding mode control for Reentry Vehicle
    International Journal of Intelligent Computing and Cybernetics, 2013
    Co-Authors: Jie Geng, Yongzhi Sheng
    Abstract:

    Purpose – The purpose of this paper is to design a global robust and continuous control scheme for the attitude tracking control problem of the Reentry Vehicle with parameter uncertainties and disturbances. Design/methodology/approach – First, feedback linearization is applied to the model of Reentry Vehicle, resulting in three independent uncertain subsystems. Then a new second-order time-varying sliding function is proposed, based on which a continuous second-order time-varying sliding mode control (SOTVSMC) law is proposed for each subsystem. The global robustness and convergence performance of the closed-loop Reentry Vehicle control system under the proposed control law are proved. Findings – Simulation is made for a Reentry Vehicle through the assumption that there is external disturbance to aerodynamic moment and the aerodynamic parameters as well as the atmospheric density are perturbed. The results verify the validity and robustness of the proposed strategy. Originality/value – The SOTVSMC attitud...