Fault Tolerant Attitude Control for spacecraft with SGCMGs under actuator partial failure and actuator saturation

Zhang, Fuzhen; Jin, Lei; Xu, Shengyuan

doi:10.1016/j.actaastro.2016.12.033

Cited by 27 publications

(5 citation statements)

References 26 publications

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“…Noting that the saturation is not treated as fault since it is a kind of con- Combining these different work conditions, the fault model list of SGCMG is obtained as shown in Table 1. This model is consistent with that in [14], where only the gimbal fault is considered. To the best knowledge of authors, this is the first attempt to establish a systematic fault model of SGCMG.…”

Section: Sgcmg Fault Modelsupporting

confidence: 87%

“…In view of the output relationship (14), and substituting the potential fault model (15) and (16) into (17), we get the output of the overall system as:…”

Section: Fault Model Of Em-vsd Systemmentioning

confidence: 99%

“…However, failures of these momentum exchange devices occur occasionally in practical missions. In existing fault-tolerant researches, most of the work such as [9,10,11,12,13,14] focus on the control problem itself, except for [11] and [12], where the four potential faults (recoverable) and/or failures (irrecoverable) of RWs are briefly introduced. Why the fault are modeled in additive way and multiplicative way is not clear.…”

Section: Introductionmentioning

confidence: 99%

“…In [13], the skew angle of CMG configuration is analyzed and a genetic algorithm is adopted to simultaneously tune the skew angle and controller gains to achieve fault tolerant. In [14], Zhang et al considered the gimbal fault and employed sliding mode control theory to change the CMG gimbal rate directly to void the singularity and achieve fault tolerance. Comparing with these existing works, this paper gives insight into the fault in general momentum exchange devices (MEDs).…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Fault modeling of general momentum exchange devices in spacecraft attitude control systems

Yue

Shen

Cao

et al. 2020

Journal of the Franklin Institute

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Section: Sgcmg Fault Modelsupporting

confidence: 87%

“…In view of the output relationship (14), and substituting the potential fault model (15) and (16) into (17), we get the output of the overall system as:…”

Section: Fault Model Of Em-vsd Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Fault modeling of general momentum exchange devices in spacecraft attitude control systems

Yue

Shen

Cao

et al. 2020

Journal of the Franklin Institute

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“…In this study, a CMG system of four identical single gimbal CMGs (4-SGCMGs) including a redundancy has been considered for a small satellite because of their simple structure, high reliability and high torque amplification properties (Zhang et al , 2017). The flywheel of the SGCMG rotates at a constant speed and its moment of inertia is also constant.…”

Section: Cmg Modelmentioning

confidence: 99%

An active force controlled of small CMG-based satellite

Salleh

Suhadis

Varatharajoo

2021

AEAT

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Purpose This paper aims to investigate the attitude control pointing improvement for a small satellite with control moment gyroscopes (CMGs) using the active force control (AFC) method. Design/methodology/approach The AFC method is developed with its governing equations and integrated into the conventional proportional-derivative (PD) controller of a closed-loop satellite attitude control system. Two numerical simulations of an identical attitude control mission namely the PD controller and the PD+AFC controller were carried out using the MATLAB®-SimulinkTM software and their attitude control performances were demonstrated accordingly. Findings Having the PD+AFC controller, the attitude maneuver can be completed within the desired slew rate, which is about 2.14 degree/s and the attitude pointing accuracies for the roll, pitch and yaw angles have improved significantly by more than 85% in comparison with the PD controller alone. Moreover, the implementation of the AFC into the conventional PD controller does not cause significant difference on the physical structure of the four single gimbal CMGs (4-SGCMGs). Practical implications To achieve a precise attitude pointing mission, the AFC method can be applied directly to the existing conventional PD attitude control system of a CMG-based satellite. In this case, the AFC is indeed the backbone for the satellite attitude performance improvement. Originality/value The present study demonstrates that the attitude pointing of a small satellite with CMGs is improved through the implementation of the AFC scheme into the PD controller.

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Adaptive fault-tolerant attitude control for a CMG-based underwater vehicle

Huang²,

Xie

et al. 2019

J Mar Sci Technol

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Fault Tolerant Attitude Control for spacecraft with SGCMGs under actuator partial failure and actuator saturation

Cited by 27 publications

References 26 publications

Fault modeling of general momentum exchange devices in spacecraft attitude control systems

Fault modeling of general momentum exchange devices in spacecraft attitude control systems

An active force controlled of small CMG-based satellite

Adaptive fault-tolerant attitude control for a CMG-based underwater vehicle

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