Reaction Wheel Fault Compensation and Disturbance Rejection for Spacecraft Attitude Tracking

Xiao, Bing; Hu, Qinglei; Singhose, William; Huo, Xing

doi:10.2514/1.59839

Cited by 74 publications

(71 citation statements)

References 35 publications

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“…, || || || || sat( )ˆ , || || [6,9], the fault scenario is chosen as: x-axis experiences actuator fault, 1 ( ) Fig.1 shows the comparison results. The steady accuracy of the unit quaternion, denoting the spacecraft attitude, for NDO-AISMC is better than AISMC.…”

Section: Remarkmentioning

confidence: 99%

“…To reduce the chattering, many studies have been carried out, such as boundary layer technique, higher order SMC, and observer based SMC. Among them, observer based SMC can largely reduce the switching gain, since most of disturbances are compensated by observer and only the uncompensated disturbances are required to be attenuated by the switching item [6]. Note that both system states and disturbances are required to estimate at the same time in [6].…”

Section: Introductionmentioning

confidence: 99%

“…Among them, observer based SMC can largely reduce the switching gain, since most of disturbances are compensated by observer and only the uncompensated disturbances are required to be attenuated by the switching item [6]. Note that both system states and disturbances are required to estimate at the same time in [6]. In practice, spacecraft attitude variables are obtained directly from the attitude determination system and do not need to be re-estimated.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Nonlinear disturbance observer based spacecraft attitude control subject to disturbances and actuator faults

Yan¹,

Wu²

2017

AIP Conference Proceedings

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Abstract. To achieve high-accuracy spacecraft attitude stabiliztion subject to complex disturbances and actuator faults, a composite controller is proposed by combining a nonlinear disturbance observer (NDO) with an adaptive integral sliding mode controller. The effects of complex disturbances and actuator faults on the spacecraft are treated as a lumped disturbance. The lumped disturbance is estimated by NDO and the estimated result is used as a feedforward compensator. The switching gain is only required to be no less than the upper bound of disturbance estimation error rather than the disturbance, and the over estimation of switching gain, caused by the initial error, is eliminated due to the global feature of the integral sliding mode item. Finally, simulations are conducted to verify the effectiveness of the proposed method.

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Section: Remarkmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Nonlinear disturbance observer based spacecraft attitude control subject to disturbances and actuator faults

Yan¹,

Wu²

2017

AIP Conference Proceedings

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“…In so doing, the reaction torque due to the spinning rotors can be cancelled out each other. The lifting force generated (7) where l represents the displacement of the rotors with respect to the center of mass of the hexacopter and d denotes the drag factor. Finally, based on the above equations, the full model of the hexacopter can be rewritten as Eq.…”

Section: Hexacopter Configurationmentioning

confidence: 99%

“…Since the active FTC shows promising advantages to overcome preceding drawbacks of the passive FTC, it has drawn interests from many researchers to design aerial vehicle attitude control [7]. A dynamic neural network scheme was presented8 to detect and isolate the fault of aircraft.…”

Section: Introductionmentioning

confidence: 99%

Fault Tolerant Control of Hexacopter for Actuator Faults using Time Delay Control Method

Jang-Ho¹,

Choi²,

Shim³

2016

International Journal of Aeronautical and Space Sciences

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A novel attitude tacking control method using Time Delay Control (TDC) scheme is developed to provide robust controllability of a rigid hexacopter in case of single or multiple rotor faults. When the TDC scheme is developed, the rotor faults such as the abrupt and/or incipient rotor faults are considered as model uncertainties. The kinematics, modeling of rigid dynamics of hexacopter, and design of stability and controllability augmentation system (SCAS) are addressed rigorously in this paper. In order to compare the developed control scheme to a conventional control method, a nonlinear numerical simulation has been performed and the attitude tracking performance has been compared between the two methods considering the single and multiple rotor faults cases. The developed control scheme shows superior stability and robust controllability of a hexacopter that is subjected to one or multiple rotor faults and external disturbance, i.e., wind shear, gust, and turbulence.

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Refined sliding mode disturbance observer‐based finite‐time composite control for Euler–Lagrange systems with multiple disturbances

Zhu,

Liu,

Qiao

2024

Asian Journal of Control

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A wide range of practical control systems such as robot manipulators and spacecrafts can be modeled by Euler–Lagrange systems. On one hand, the requirements for system control accuracy, response speed, and robustness are ever increasing. On the other hand, the control performances are inevitably degraded by multiple disturbances. In this paper, a novel finite‐time composite control law is proposed for a class of Euler–Lagrange systems subject to multiple heterogeneous disturbances including a neutrally stable disturbance and a norm‐bounded disturbance. More specifically, a refined sliding mode disturbance observer (RSMDO) is proposed to estimate and reject the neutrally stable disturbance in the feedforward channel, while an adaptive nonsingular backstepping control (ANBC) is designed in the feedback channel to stabilize the system and attenuate the observer error as well as the norm‐bounded disturbance. The proposed RSMDO can not only fully utilize the disturbance information, but also quantify the convergence time and steady‐state accuracy of the estimation error. The finite‐time stability analysis is carried out for the closed‐loop system. Finally, an example of spacecraft attitude control system is given to demonstrate the effectiveness of the proposed methods.

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Reaction Wheel Fault Compensation and Disturbance Rejection for Spacecraft Attitude Tracking

Cited by 74 publications

References 35 publications

Nonlinear disturbance observer based spacecraft attitude control subject to disturbances and actuator faults

Nonlinear disturbance observer based spacecraft attitude control subject to disturbances and actuator faults

Fault Tolerant Control of Hexacopter for Actuator Faults using Time Delay Control Method

Refined sliding mode disturbance observer‐based finite‐time composite control for Euler–Lagrange systems with multiple disturbances

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