Fault-tolerant spacecraft attitude control system

Murugesan, S.; Goel, P. S.

doi:10.1007/bf02811321

Cited by 61 publications

(24 citation statements)

References 15 publications

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“…ω × is the skew-symmetric matrix acting on the vector ω = [ω 1 , ω 2 , ω 3 ] T and has the similar form of σ × . The matrix = diag {ρ 1 , ρ 2 , ρ 3 } ∈ R 3×3 is the reaction wheel effectiveness matrix, andū ∈ R 3 denotes the additive fault induced by [47,Failure 2]. 0 < ρ i ≤ 1 is the actuator health indicator for the ith actuator.…”

Section: A Attitude Kinematics and Dynamicsmentioning

confidence: 99%

“…Theorem 1: Considering a rigid spacecraft system described by (3) and (5) with actuator fault, for any given attitude reference trajectory σ d , if Assumptions 1 and 2 are satisfied, the control scheme (46) and (47) can guarantee that all the signals in the closed-loop system remain bounded, and the tracking and observer errors converge to a small neighborhood of the origin by choosing the design parameters appropriately.…”

Section: B Tracking Controller Designmentioning

confidence: 99%

“…2) Specify a positive definite matrix Q and by solving the Lyapunov equation (14), a positive definite matrix P is obtained. 3) Choose the design parameters c 1 , c 2 , and γ i , (i = 1, 2, 3) in (37), (46), and (47) to satisfy that c 1 > 0, c 2 > 0, and γ i > 0, respectively. 4) Choose the design parameters r i > 2 in (47) are positive constants, which are used for the σ -modification.…”

Section: B Tracking Controller Designmentioning

confidence: 99%

“…3) Choose the design parameters c 1 , c 2 , and γ i , (i = 1, 2, 3) in (37), (46), and (47) to satisfy that c 1 > 0, c 2 > 0, and γ i > 0, respectively. 4) Choose the design parameters r i > 2 in (47) are positive constants, which are used for the σ -modification. According to [52], the appropriate choices of r i can prevent the parameters θ i to drift.…”

Section: B Tracking Controller Designmentioning

confidence: 99%

“…In this section, to verify the effectiveness of the proposed control scheme (37), (46), and (47), numerical simulations are analyzed for a rigid spacecraft, and the control parameters are shown in Table I. We choose the fuzzy membership functions as 2, 3, l = 1, .…”

Section: Simulation Studiesmentioning

confidence: 99%

See 4 more Smart Citations

Fuzzy Adaptive Fault-Tolerant Output Feedback Attitude-Tracking Control of Rigid Spacecraft

Huo

Xia

Yin

et al. 2017

IEEE Trans. Syst. Man Cybern, Syst.

102

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This paper proposes a stable adaptive fuzzy faulttolerant attitude-tracking controller for a rigid spacecraft in the presence of unavailable velocities, external disturbance, actuator faults, and actuator saturation. Fuzzy logic systems are applied to approximate the unknown nonlinear function vector, and a fuzzy adaptive observer is designed to estimate the unmeasured velocity of the rigid body. By using the backstepping technique, a novel adaptive fuzzy attitude-tracking fault-tolerant control scheme is developed. It has been testified that this control approach guarantees that all signals of the rigid spacecraft are bounded and the tracking error between the system output and the reference signal converges to a small neighborhood of zero. Simulation examples with constant faults and time-variant faults are provided to show the fault-tolerant effectiveness of the control method.Index Terms-Actuator faults, actuator saturation, adaptive fuzzy control, attitude tracking, fault-tolerant control (FTC).

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Section: A Attitude Kinematics and Dynamicsmentioning

confidence: 99%

Section: B Tracking Controller Designmentioning

confidence: 99%

Section: B Tracking Controller Designmentioning

confidence: 99%

Section: B Tracking Controller Designmentioning

confidence: 99%

Section: Simulation Studiesmentioning

confidence: 99%

See 3 more Smart Citations

Fuzzy Adaptive Fault-Tolerant Output Feedback Attitude-Tracking Control of Rigid Spacecraft

Huo

Xia

Yin

et al. 2017

IEEE Trans. Syst. Man Cybern, Syst.

102

View full text Add to dashboard Cite

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Adaptive Fault‐Tolerant Multiplicative Attitude Filtering for Small Satellites

Kinatas,

Hajiyev

2024

Adaptive Control & Signal

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This study tackles the problem of fault‐tolerant attitude estimation for small satellites. A probabilistic adaptive technique is presented for the multiplicative extended Kalman filter (MEKF) algorithm that is used in attitude estimation. The presented method is based on tracking the normalized measurement innovations in the filter and calculating the probability of the normal operation of the estimation system. Using this probability, the filter gain is corrected to maintain the tracking performance of the filter despite faulty measurements. In order to evaluate the performance of this method, several simulations are performed where different types of faults are introduced to the synthetic attitude sensor measurements (magnetometer and sun sensor) at different times. Simulation results are compared not only with a conventional EKF but also with another popular adaptive Kalman filter, an adaptive Kalman filter with multiple scaling factors (MSFs).

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Distributed fault‐tolerant control design for spacecraft finite‐time attitude synchronization

Zhou

Xia

2015

Intl J Robust & Nonlinear

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SUMMARYThis paper develops two distributed finite-time fault-tolerant control algorithms for attitude synchronization of multiple spacecraft with a dynamic virtual leader in the presence of modeling uncertainties, external disturbances, and actuator faults. The leader gives commands only to a subset of the followers, and the communication flow between followers is directed. By employing a novel distributed nonsingular fast terminal sliding mode and adaptive mechanism, a distributed finite-time fault-tolerant control law is proposed to guarantee all the follower spacecraft that finite-time track a dynamic virtual leader. Then utilizing three distributed finite-time sliding mode estimators, an estimator-based distributed finite-time fault-tolerant control law is proposed using only the followers' estimates of the virtual leader. Both of them do not require online identification of the actuator faults and provide robustness, finite-time convergence, fault-tolerant, disturbance rejection, and high control precision. Finally, numerical simulations are presented to evaluate the theoretical results.

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Fault-tolerant spacecraft attitude control system

Cited by 61 publications

References 15 publications

Fuzzy Adaptive Fault-Tolerant Output Feedback Attitude-Tracking Control of Rigid Spacecraft

Fuzzy Adaptive Fault-Tolerant Output Feedback Attitude-Tracking Control of Rigid Spacecraft

Adaptive Fault‐Tolerant Multiplicative Attitude Filtering for Small Satellites

Distributed fault‐tolerant control design for spacecraft finite‐time attitude synchronization

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