Integrated Fault-Tolerant Stabilization Control for Satellite Attitude Systems with Actuator and Sensor Faults

Bai, Lang; Gao, Zhifeng

doi:10.1007/s40313-019-00498-3

Cited by 9 publications

(5 citation statements)

References 27 publications

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“…Using the unit quaternion in practical implementations, (10) describes the alignment of the object direction and the reference coordinate. In the case of the alignment, the unit quaternion is 𝑞 =…”

Section: B Attitude Kinematicsmentioning

confidence: 99%

“…𝑅 𝐸𝑅𝑊 𝑦 . 𝑅 𝐸𝑅𝑊 𝑧 (19) Given that the failure rate of the reaction wheels was 𝐹𝑅 = 0.0001, then the reliability of the system for 3 years lifetime, based on the exponential probability distribution [10] estimated 𝑅 = 0.99.…”

Section: E Actuators' Reliability Block Diagrammentioning

confidence: 99%

“…Using the redundant members, while an actuator is defective, is one of the possibilities to increase the reliability of ACS. In this regard, in some works, three-wheel standard orthogonal, pyramidal, tetrahedron configurations, or groups of redundant members were used to control a satellite in faulty situations [9][10][11]. Wang et al carried out a number of investigations into the fault detection of actuators, angular rate sensors, attitude sensor systems, and attitude tracking problems, and designed robust controllers such as Event-triggered back-stepping control [12,13].…”

Section: Introductionmentioning

confidence: 99%

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Controller Reliability Assessment Model: A New Method for Reliability Assessment of Attitude Control Subsystem in Space Missions

Damircheli,

Fakoor

2024

Preprint

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The objective of this research is to assess the reliability of the controller and attitude control subsystem (ACS) of a LEO satellite using the presented Controller Reliability Assessment Model (CRAM). CRAM is based on the Software in the Loop (SIL) simulation which leads to the construction of a database from ACS performance. Using data analysis techniques leads to a comprehensive understanding of the ACS’s controller functionality and determines the failure rate of the controller’s component. In addition, Reliability Block Diagram (RBD) is implemented to visualize the contribution of the controller and estimate the reliability of the controllers according to the evaluated failure rates and reliability mathematical model for three years of operating. CRAM defines the relatively most robust, and accurate controller with the fastest response and highest reliability. In the designed control system, solar radiation, gravity gradient, and aerodynamic effects are considered as external disturbances. The actuator's loss of effectiveness is considered as an internal disturbance. The Tetrahedron configuration of reaction wheels is modeled in which three reaction wheels serve as three-axis control, and one reaction wheel as a redundant actuator. In this research, controllers such as PD, H∞, and two different types of sliding mode controllers are considered.

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Section: B Attitude Kinematicsmentioning

confidence: 99%

Section: E Actuators' Reliability Block Diagrammentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Controller Reliability Assessment Model: A New Method for Reliability Assessment of Attitude Control Subsystem in Space Missions

Damircheli,

Fakoor

2024

Preprint

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“…On the one hand, active FTC approaches depend on the fault information given by the FDD unit 23 which for an active FTC not only has an execution level but also has a supervision level. For example, Bai and Gao 181 have studied an integrated fault-tolerant stabilization control system for a rigid body satellite. The satellite attitude control system is faced with both sensor and actuator faults.…”

Section: Fault-tolerant Controlmentioning

confidence: 99%

Advanced fault detection and diagnosis in spacecraft attitude control systems: Current state and challenges

Pourtakdoust

Mehrjardi

Hajkarim

et al. 2023

Proceedings of the Institution of Mechanical Engineers, Part G:

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A review of advanced fault detection and diagnosis (FDD) techniques in attitude control systems (ACSs) of spacecraft is presented. In the first part of the paper, several types of ACS failure scenarios with their practical solutions are presented. Next, the existing approaches to FDD are considered and classified based on different criteria, including applications and design techniques. The literature of this part showed that to enhance ACS operational safety, predictability of failure of an ACS and/or of its components as well as reducing the possibility of failure occurrence is imperative. In addition, fast FDD of various kinds of failures is necessary to guarantee the required reliability of an ACS. The second part of this study highlights challenges involved with different FDD approaches, emphasizing their practical applicability. Current research gaps in FDD techniques such as insensitive residual signal, process monitoring methods, accurate plant model design, easy-to-use software development, FDD tuning process, dealing with noisy sensor measurements, time taken for fault management, the sensitivity of FDD system to faults, and FDD robustness are further elaborated on. Subsequently, the state-of-the-art FDD and its future needs are reflected on. The results of this study could direct spacecraft manufacturers and ACS providers to focus on future needs and improve ground testing for enhanced operational reliability and redundancy.

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“…In longitudinal flight control system, the aircraft may suffer atmospheric disturbance (defined as S-UI) during flight, while the inertial sensors output the attitude information subject to fault signal (defined as M-UI) in Chen and Patton [18]. The attitude systems of a rigid satellite may be subjected to actuator faults (defined as S-UI) and sensor faults (defined as M-UI) in Bai and Gao [19]. In conclusion, the introduction of dual-UIs is expected to describe the system behavior more accurately and further improves the state estimate accuracy.…”

Section: Introductionmentioning

confidence: 99%

Secure state estimation for unmanned aircraft cyber‐physical systems under multiple attacks

Feng

Shu-hui

et al. 2022

Asian Journal of Control

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By exploiting the communication infrastructure among the sensor, actuator, and control system, attackers may compromise the security of unmanned aircraft cyber‐physical systems, with techniques such as denial‐of‐service (DoS) attack, random attack, and data‐injection attack. In this paper, the data‐injection attacks for controller and sensor are modeled as the dual unknown disturbance inputs (dual‐UIs) appearing in dynamic and measurement model. The problem of secure state estimation under multiple attacks together with the DoS attack‐induced packet dropout is transformed into the problem of stochastic system state estimation under dual‐UIs together with the missing measurement. Therefore, a recursive dual‐UIs decoupling filter is proposed through minimizing the minimum upper bound of the estimation covariance. First, a Kalman‐like recursive filter scheme independent of the dual‐UIs is established to realize the unbiased estimation. Meanwhile, a lower bounded adaptive factor is introduced to depict the state related unknown dual‐UI that cannot be eliminated completely due to the randomly missing measurements. Then, the minimum upper bound of the estimation covariance is deduced via online scalar convex optimization, based on which the measurement coefficient matrix is derived under the dual‐UIs decoupling conditions. Finally, the sufficient condition for the convergence of the proposed filter is shown and the stability of the state estimate is investigated. Simulation cases of unmanned aircraft longitudinal flight control system verifies the effectiveness and superiority of the proposed method.

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Integrated Fault-Tolerant Stabilization Control for Satellite Attitude Systems with Actuator and Sensor Faults

Cited by 9 publications

References 27 publications

Controller Reliability Assessment Model: A New Method for Reliability Assessment of Attitude Control Subsystem in Space Missions

Controller Reliability Assessment Model: A New Method for Reliability Assessment of Attitude Control Subsystem in Space Missions

Advanced fault detection and diagnosis in spacecraft attitude control systems: Current state and challenges

Secure state estimation for unmanned aircraft cyber‐physical systems under multiple attacks

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