Simple finite-time attitude stabilization laws for rigid spacecraft with bounded inputs

Gui, Haichao; Jin, Lei; Xu, Shengyuan

doi:10.1016/j.ast.2015.01.020

Cited by 71 publications

(74 citation statements)

References 18 publications

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“…In the work of Lu and Xia, 22 an adaptive fast nonsingular terminal sliding mode controller was presented to achieve the finite-time attitude tracking performance for spacecraft systems with inertia uncertainties and external disturbances. The similar results were also done by combining the Chebyshev neural network with the sliding mode control in the work of Zou et al 23 In the works of Gui et al 24 and Lu et al, 25 by replacing the nonsmooth saturation function by a smooth nonaffine function, a proportional-derivative-type controller and a sliding mode controller were proposed for rigid spacecraft with input constraint to realize the finite-time stabilization and tracking control, respectively. In the work of Hu et al, 26 a finite-time attitude control scheme was presented for rigid spacecraft with input constraint by introducing an auxiliary variable in the disturbance observer-based sliding mode control design.…”

Section: Introductionmentioning

confidence: 56%

“…However, in practice, the existence of uncertainties and external disturbances makes it difficult to achieve the attitude control with rapid convergence and high accuracy, simultaneously. Due to the good performance of finite‐time convergence and widely robustness, finite‐time control schemes have been gradually implemented in spacecraft attitude control . In the works of Zhu et al and Lu and Xia, finite‐time attitude stabilization controllers were presented for rigid spacecraft in the presence of inertia uncertainties and external disturbances.…”

Section: Introductionmentioning

confidence: 99%

“…Due to the good performance of finite-time convergence and widely robustness, finite-time control schemes have been gradually implemented in spacecraft attitude control. [15][16][17][18][19][20][21][22][23][24][25][26][27][28][29][30][31] In the works of Zhu et al 19 and Lu and Xia, 20 finite-time attitude stabilization controllers were presented for rigid spacecraft in the presence of inertia uncertainties and external disturbances. In the work of Song et al, 21 a fast terminal sliding mode control scheme was proposed to guarantee that both the inner-loop and the outer-loop tracking errors converge to zero in a finite time.…”

Section: Introductionmentioning

confidence: 99%

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Adaptive fixed‐time fault‐tolerant control for rigid spacecraft using a double power reaching law

Tao

Chen

et al. 2019

Intl J Robust & Nonlinear

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Summary In this paper, an adaptive fixed‐time fault‐tolerant control scheme is presented for rigid spacecraft with inertia uncertainties and external disturbances. By using an inverse trigonometric function, a novel double power reaching law is constructed to speed up the state stabilization and reduce the chattering phenomenon simultaneously. Then, an adaptive fixed‐time fault‐tolerant controller is developed for the spacecraft with the actuator faults, such that the fixed‐time convergence of the attitude and angular velocity could be guaranteed, and no prior knowledge on the upper bound of the lumped uncertainties is required anymore in the controller design. Comparative simulations are provided to illustrate the effectiveness and superior performance of the proposed scheme.

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Section: Introductionmentioning

confidence: 56%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Adaptive fixed‐time fault‐tolerant control for rigid spacecraft using a double power reaching law

Tao

Chen

et al. 2019

Intl J Robust & Nonlinear

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“…The terminal sliding mode (TSM) method belongs to the former but has a singularity problem . In contrast, the homogeneous method is singularity free but cannot deal with parametric uncertainties and unknown disturbances . The TSM method has been used to design fault‐free and fault‐tolerant attitude control laws.…”

Section: Introductionmentioning

confidence: 99%

Adaptive fault‐tolerant spacecraft attitude control using a novel integral terminal sliding mode

Gui

Vukovich

2017

Intl J Robust & Nonlinear

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Summary The attitude tracking of a rigid spacecraft is approached in the presence of uncertain inertias, unknown disturbances, and sudden actuator faults. First, a novel integral terminal sliding mode (ITSM) is designed such that the sliding motion realizes the action of a quaternion‐based nonlinear proportional‐derivative controller. More precisely, on the ITSM, the attitude dynamics behave equivalently to an uncertainty‐free system, and finite‐time convergence of the tracking error is achieved almost globally. A basic ITSM controller is then designed to ensure the ITSM from onset when an upper bound on the system uncertainties is known. Further, to remove this requirement, adaptive techniques are employed to compensate for the uncertainties, and the resultant adaptive ITSM controller stabilizes the system states to a small neighborhood around the sliding surface in finite time. The proposed schemes avoid the singularity intrinsic to terminal sliding mode‐based controllers and the unwinding phenomenon associated with some quaternion‐based controllers. Numerical examples demonstrate the advantageous features of the proposed algorithm. Copyright © 2017 John Wiley & Sons, Ltd.

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“…In [17], a saturated attitude controller for spacecraft subject to actuator constraints and bounded disturbances has been proposed. Finite-time attitude stabilization has been studied in [18]. Using the theory 2 Journal of Control Science and Engineering of homogeneous system, finite-time stability of the attitude control system can be guaranteed.…”

Section: Introductionmentioning

confidence: 99%

Output Feedback Control for Asymptotic Stabilization of Spacecraft with Input Saturation

Pukdeboon

2017

Journal of Control Science and Engineering

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This paper investigates the attitude stabilization problem of rigid spacecraft subject to actuator constraints, external disturbances, and attitude measurements only. An output feedback control framework with input saturation is proposed to solve this problem. The general saturation function is utilized in the proposed controller design and a unified control method is developed for the asymptotic stabilization of rigid spacecraft without velocity measurements. Asymptotic stability is proven by Lyapunov stability theory. Moreover, a new nonlinear disturbance observer is designed to compensate for external disturbances. Then, a composite controller is presented by combining a unified saturated output feedback control with a nonlinear disturbance observer. Desirable features of the proposed control scheme include the intuitive structure, robustness against external disturbances, avoidance of model information and velocity measurements, and ability to ensure that the actuator constraints are not violated. Finally, numerical simulations have been carried out to verify the effectiveness of the proposed control method.

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Simple finite-time attitude stabilization laws for rigid spacecraft with bounded inputs

Cited by 71 publications

References 18 publications

Adaptive fixed‐time fault‐tolerant control for rigid spacecraft using a double power reaching law

Adaptive fixed‐time fault‐tolerant control for rigid spacecraft using a double power reaching law

Adaptive fault‐tolerant spacecraft attitude control using a novel integral terminal sliding mode

Output Feedback Control for Asymptotic Stabilization of Spacecraft with Input Saturation

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