Observer-based fault-tolerant attitude tracking control for rigid spacecraft with actuator saturation and faults

Wu, Xia; Luo, Shibin; Wei, Caisheng; Liao, Yuxin

doi:10.1016/j.actaastro.2020.10.017

Cited by 37 publications

(21 citation statements)

References 42 publications

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“…And two observers proposed in [10, 19] are considered as comparisons. To quantitatively characterize the fault estimation performance and show the benefits of the proposed method, two metrics are introduced to evaluate the transient performance and the steady state performance of the fault tracking response, including

IAE = \int_{0}^{T}{{| {{e_f}(t)} |dt}}

(integrated absolute error) and

ITAE = \int_{0}^{T}{{t| {{e_f}(t)} |dt}}

(integrated time absolute error) [50].…”

Section: Numerical Simulationmentioning

confidence: 99%

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Fuzzy adaptive observer‐based fault estimation design with adjustable parameter for satellite under unknown actuator faults and perturbations

Chang

2022

IET Control Theory & Appl

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This study considers the problem of fault estimation for rigid satellite in the presence of external disturbances, parameter perturbations, and actuator time‐varying faults. Firstly, a Takagi‐Sugeno (T‐S) fuzzy model with interval matrix for satellite attitude system under large attitude angle scope is established, along with a detailed analysis of actuator faults in terms of additive and multiplicative descriptions. Then, a novel fuzzy adaptive observer with adjustable parameter is proposed to estimate both system states and actuator faults. The estimated errors are proved to be uniformly ultimately bounded, based on descriptor augmentation technique and Lyapunov stability theory. The proposed observer realizes a lower estimation performance index in terms of quantitative assessment compared to existing observer methods. Furthermore, an auxiliary optimization variable and the elimination method are applied to decrease the conservatism of the proposed design. And an intuitive quantitative performance index of fault estimation is introduced to obtain reliable evaluation and decision. Finally, numerical simulations and analyses of rigid satellite illustrate the effectiveness and benefit of the proposed strategy.

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IAE = \int_{0}^{T}{{| {{e_f}(t)} |dt}}

(integrated absolute error) and

ITAE = \int_{0}^{T}{{t| {{e_f}(t)} |dt}}

(integrated time absolute error) [50].…”

Section: Numerical Simulationmentioning

confidence: 99%

“…|e f (t )|dt (integrated absolute error) and ITAE = ∫ T 0 t |e f (t )|dt (integrated time absolute error)[50].…”

mentioning

confidence: 99%

Fuzzy adaptive observer‐based fault estimation design with adjustable parameter for satellite under unknown actuator faults and perturbations

Chang

2022

IET Control Theory & Appl

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“…[21]. It is noted that, as applied in literature [11–13, 16], actuator faults and disturbances are considered as a lumped disturbance. (c)In ref. [35], a nonsingular fast fixed‐time terminal sliding surface and a robust adaptive fixed‐time sliding mode control (RAFTSMC) scheme are considered.…”

Section: Numerical Simulationmentioning

confidence: 99%

“…[21]. It is noted that, as applied in literature [11][12][13]16], actuator faults and disturbances are considered as a lumped disturbance. (c) In ref.…”

Section: Fault Tolerant Controlmentioning

confidence: 99%

Fuzzy model based fault estimation and fault tolerant control for flexible spacecraft with unmeasurable vibration modes

Chang

2022

IET Control Theory & Appl

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This paper investigates the problem of anti‐disturbance fault estimation and attitude tracking fault tolerant control for a flexible spacecraft subject to actuator faults, external disturbances, input saturation, and configuration misalignment. Different form the traditional methods, both the nonlinear dynamics subsystem and attitude control system are reconstructed into Takagi–Sugeno fuzzy models, where partial nonlinear term is remained to assist the design of fuzzy controller. A fuzzy fault estimation observer with proportional–integral adaptive laws is first designed. Without measuring any dynamic information of flexible appendages, estimated values of unknown actuator faults and vibration disturbances of flexible appendages can be obtained simultaneously. This is the most important advantage of the proposed fault estimation scheme over the previous methods. Then, a fuzzy sliding mode fault tolerant control scheme, based on fewer fuzzy rules and less computational burden, is developed under the framework of feedback linearisation and feedforward compensation. The actuator faults and vibration disturbances are counteracted in real time. Regional pole placement and virtual controller with input saturation are adopted to tune the control input and avoid the radical control torque scheduling. Finally, numerical simulations are given to illustrate the validity of the proposed fault estimation and fault tolerant control strategies.

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“…Moreover, the similar assumption can be found in the recent literature. [41][42][43][44]…”

Section: Spacecraft Attitude Kinematics and Dynamicsmentioning

confidence: 99%

Finite‐time fault‐tolerant output feedback attitude control of spacecraft formation with guaranteed performance

Gao

Xia

Zhang

et al. 2021

Intl J Robust & Nonlinear

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This article examines the problem of finite-time fault-tolerant output feedback attitude control for spacecraft formation system with guaranteed performance, in the presence of uncertainties, external disturbances, actuator faults, and input saturation. First, a neural network (NN) based finite-time observer is established for follower spacecraft to observe its angular velocity, where the NN is utilized to approximate the unknown uncertainties. Furthermore, based on the information from the angular velocity observer, backstepping procedure, and barrier Lyapunov function technique, a distributed finite-time controller with only attitude measurement is proposed. Unlike the existing finite-time control scheme, the tracking errors keep inside their predefined feasible regions with guaranteed transient and steady-state performance. A theoretical proof shows that the finite-time stability of the closed-loop system can be achieved. Finally, numerical simulation results are presented to illustrate the effectiveness and fine performance of the proposed finite-time observer and controller for the attitude control system.

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Observer-based fault-tolerant attitude tracking control for rigid spacecraft with actuator saturation and faults

Cited by 37 publications

References 42 publications

Fuzzy adaptive observer‐based fault estimation design with adjustable parameter for satellite under unknown actuator faults and perturbations

Fuzzy adaptive observer‐based fault estimation design with adjustable parameter for satellite under unknown actuator faults and perturbations

Fuzzy model based fault estimation and fault tolerant control for flexible spacecraft with unmeasurable vibration modes

Finite‐time fault‐tolerant output feedback attitude control of spacecraft formation with guaranteed performance

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