Hyperbolic Tangent Function-Based Finite-Time Sliding Mode Control for Spacecraft Rendezvous Maneuver Without Chattering

Shi, Z.; Deng, Chao; Zhang, Sai; Xie, Yaen; Cui, Hongtao; Hao, Yong

doi:10.1109/access.2020.2983316

Cited by 24 publications

(20 citation statements)

References 35 publications

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“…To obtain better collaboration of the proposed method's efficiency, a comparative simulation example is presented here. The controller presented in [1] is applied for illustration. The basic simulation parameters are inherited from this reference.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…Considering the external disturbance, actuator saturation, parameter uncertainty and other factors, the design of rendezvous maneuver controller for spacecraft becomes more challenging. Through protracted and unremitting efforts, some scientific methods have aroused great research interest for spacecraft tracking control in recent years, such as adaptive control [1,2], backstepping control [3][4][5], neural network-based control [5,6], fault-tolerant control [7][8][9] as well as SMC [10,11].…”

Section: Introductionmentioning

confidence: 99%

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Adaptive Sliding Mode Control for Spacecraft Rendezvous With Unknown System Parameters and Input Saturation

Zhang

et al. 2021

IEEE Access

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In this study, we investigated the sliding mode control (SMC) for the spacecraft rendezvous maneuver under unknown system parameters and input saturations. On the basis of the attitude and position tracking subsystem, two anti-saturation sliding mode surfaces (SMSs) are constructed to guarantee the exponential convergence of tracking errors between the target spacecraft and the pursuer spacecraft. In connection with hyperbolic tangent, a modified auxiliary system is established to compensate the nonlinear constraint caused by the actuator saturation. Meanwhile, in order to enhance the practicability and reliability of the controller, unknown inertial information is taken into consideration. The resulting system uncertainties are estimated accurately via adaptive laws. Additionally, it is concluded that the designed controller is capable of ensuring the boundedness of the closed-loop signals with reasonable selection of control parameters. Finally, the effectiveness and advantages of the proposed methods are verified through numerical simulations.INDEX TERMS spacecraft rendezvous maneuver; asymptotic tracking control; sliding mode control; input saturation; adaptive control.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Adaptive Sliding Mode Control for Spacecraft Rendezvous With Unknown System Parameters and Input Saturation

Zhang

et al. 2021

IEEE Access

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“…Citation information: DOI 10.1109/ACCESS.2020.3014220, IEEE Access VOLUME XX, 2017 1 Fig. 23 Relative attitude under the second controller in [34] Fig. 24 Relative position under the second controller in [34] To better show the superiority of this paper, the second controller in [34] is adopted under the same actuator faults and external disturbances as that in case B.…”

Section: A Simulation Results Of the Basic Controllermentioning

confidence: 99%

Minimum-Learning-Parameter-Based Fault-Tolerant Control for Spacecraft Rendezvous With Unknown Inertial Parameters

Liu

Zhang

et al. 2020

IEEE Access

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In this paper, robust control strategies are explored to solve the problem of rendezvous maneuver for rigid spacecraft exposed to the external disturbance, actuator faults and unknown inertial parameters. To pursue the control objective, two adaptive controllers are constructed via the sliding mode control (SMC) technology. Firstly, a basic control scheme is designed in the event of unknown inertial parameters and external disturbance, where the Minimum-learning-parameter (MLP) algorithm is adopted for approximating the unknown system dynamics. Though effective, the basic controller is not applicable in the actuator fault scenarios. Considering this drawback, adaptive laws are designed in the second controller to tackling the actuator faults. It is illustrated that the proposed controllers will endow tracking errors with asymptotic stability and strong robustness to actuator faults. Finally, the effectiveness of the control strategies is verified by numerical simulations.

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“…where tanh(•) is the hyperbolic tangent function which can degree the chattering well [23] and μ is the boundary and results from the continuous approximation of the hyperbolic tangent function. e CISMC by means of the conditional integrator ensures an improvement in transient response of ISMC and recovers the SMC performance without chattering.…”

Section: Attitude Loop Controller Designsmentioning

confidence: 99%

Disturbance Rejection Trajectory Tracking Control for an Unmanned Quadrotor Based on Hybrid Controllers

Ji¹,

Cai

2021

Journal of Robotics

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The purpose of this article is to explore a dual-loop problem regarding the trajectory tracking control of a quadrotor unmanned aerial vehicle, applying a linear active disturbance rejection and conditional integrator sliding mode controller, namely, LARC-CISMC. The quadrotor system model is derived through Newton–Euler method and consists of two subsystems. The hybrid controller for position and attitude loops is constructed. An evaluation of the proposed controller is presented in comparison with the linear active disturbance rejection controller. Simulation comparisons and experimental tests illustrate that the proposed controller has a satisfied robustness and accuracy under lumped disturbances.

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Hyperbolic Tangent Function-Based Finite-Time Sliding Mode Control for Spacecraft Rendezvous Maneuver Without Chattering

Cited by 24 publications

References 35 publications

Adaptive Sliding Mode Control for Spacecraft Rendezvous With Unknown System Parameters and Input Saturation

Adaptive Sliding Mode Control for Spacecraft Rendezvous With Unknown System Parameters and Input Saturation

Minimum-Learning-Parameter-Based Fault-Tolerant Control for Spacecraft Rendezvous With Unknown Inertial Parameters

Disturbance Rejection Trajectory Tracking Control for an Unmanned Quadrotor Based on Hybrid Controllers

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