Fixed-time attitude tracking control for spacecraft without unwinding

Huang, Bing; Li, Aijun; Guo, Yong; Wang, Changqing

doi:10.1016/j.actaastro.2018.04.041

Cited by 73 publications

(48 citation statements)

References 29 publications

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“…The spacecraft control problems with fixed-time stabilization were studied in Refs. [16][17][18][27][28][29][30]. The attitude control problem with fixed-time stabilization is studied in Ref.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive Fixed-Time Terminal Sliding Mode Control on SE(3) for Coupled Spacecraft Tracking Maneuver

Gong

Liao

Wang

2020

International Journal of Aerospace Engineering

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In this paper, a reaching law-based adaptive fixed-time terminal sliding mode control law, which is used for coupled spacecraft tracking maneuver in the presence of large inertia parametric uncertainties and external disturbances, is proposed. The coupled 6-DOF kinematics and dynamics for spacecraft motion are modeled on Lie group SE(3). The relative configuration is expressed by a local coordinate (exponential coordinate) of SE(3). In order to estimate the inertia parameters and external disturbances, we also propose a novel adaptive update law, which can make the control law be applied without the inertia parameters of the spacecraft a priori. Fixed-time convergence property of the closed-loop feedback system is proved in the framework of Lyapunov. Numerical simulations are performed to demonstrate the performances of the proposed control scheme for coupled spacecraft tracking maneuver.

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Section: Introductionmentioning

confidence: 99%

“…The attitude control problem with fixed-time stabilization is studied in Ref. [27][28][29]. Hu et al [30] considered the fixed-time convergence of position control for the spacecraft rendezvous mission.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Fixed-Time Terminal Sliding Mode Control on SE(3) for Coupled Spacecraft Tracking Maneuver

Gong

Liao

Wang

2020

International Journal of Aerospace Engineering

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“…Specifically, the discontinuous control torques required in [24], [30], [31] may lead to chattering phenomenon, which can damage the actuators and excite unmodeled high-frequency dynamics. In general, this problem could be eliminated through the saturation function (boundary layer method), which is suggested in [24], [29]. However, the cost is the degradation of the steady control accuracy, since the sliding mode function can only converge to the boundary layer in finite or fixed time.…”

Section: Introductionmentioning

confidence: 99%

“…Although high-order sliding mode control and full-order sliding mode control are applied in [32], [33] to design finite-time continuous nonsingular attitude controller, to the best of authors' knowledge, there are still few works which can ensure fixed-time convergence and provide continuous control torques for the disturbed rigid spacecraft without using disturbance observers. Furthermore, feedback linearization or state transformation used in the controllers [24]- [27] brings heavy computation burden, since these controllers need real-time calculation of the complicated accurate compensation terms and the inverse of the Jacobian matrix. Therefore, it is interesting and necessary to design robust high-precision fixed-time attitude controllers without causing singularity or chattering.…”

Section: Introductionmentioning

confidence: 99%

Continuous Fixed-Time Sliding Mode Attitude Controller Design for Rigid-Body Spacecraft

Wang

Song

2020

IEEE Access

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Fast and high-precision attitude control for the rigid spacecraft is important for its broad applications in astronautics. In this paper, we address this problem via continuous nonsingular fixed-time sliding mode control approach. At first, by improving the adding power integral technique, a nonsingular nominal attitude controller is presented to achieve fixed-time convergence of the unperturbed attitude system, which underpins the basics for design of the sliding mode motion and surfaces for the subsequent proposed main results. Then, a fixed-time full-order sliding mode controller with an explicit bound of settling time is proposed to track the desire attitude even in the presence of external disturbances. However, this controller requires the angular acceleration signals which is usually unmeasurable. To this end, an integral sliding mode controller is further presented to achieve fixed-time attitude tracking without using any acceleration information. This proposed integral sliding mode controller can realize second-order sliding mode with rigorous proof of fixed-time convergence. Both the proposed fixed time full-order and integral sliding mode controller are inherent nonsingular and chattering-free. Numerical examples are illustrated to demonstrate the effectiveness of the results given herein in practical scenarios. INDEX TERMS Attitude control, sliding mode control, fixed-time convergence.

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“…However, it is still a challenging work to construct such kind of controllers owing to the complexity of the external disturbance, unknown system dynamics and unexpected actuator faults. Despite of these difficulties, researchers have developed numerous strategies for spacecraft tracking control, including adaptive control [1][2][3][4][5], backstepping control [11][12][13], output feedback control [25,26] and sliding mode control [4,18,19,[31][32][33].…”

Section: Introductionmentioning

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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Fixed-time attitude tracking control for spacecraft without unwinding

Cited by 73 publications

References 29 publications

Adaptive Fixed-Time Terminal Sliding Mode Control on SE(3) for Coupled Spacecraft Tracking Maneuver

Adaptive Fixed-Time Terminal Sliding Mode Control on SE(3) for Coupled Spacecraft Tracking Maneuver

Continuous Fixed-Time Sliding Mode Attitude Controller Design for Rigid-Body Spacecraft

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

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