Robust fault-tolerant control for flexible spacecraft against partial actuator failures

Zhang, Ran; Qiao, Jianzhong; Li, Tao; Guo, Lei

doi:10.1007/s11071-014-1243-2

Cited by 66 publications

(34 citation statements)

References 26 publications

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“…In this paper, we consider the situation in which the actuator experiences failure during the entire attitude maneuvers, and then, the faulty dynamics of the spacecraft with one rigid body and one flexible appendage can be described by [23]:…”

Section: Problem Formulation and Preliminariesmentioning

confidence: 99%

“…More precisely, the proposed control scheme is applied to a flexible spacecraft with one flexible appendage which is proposed in [23]. Since low-frequency modes are generally dominant in a flexible system, only the lowest two bending modes have been considered for the implemented spacecraft model.…”

Section: Numerical Simulationmentioning

confidence: 99%

“…During the past decades, considerable efforts have been made to design robust control for flexible spacecraft systems for simultaneous attitude control and vibration suppression [10,15]. In recent decades, fault-tolerant control is becoming an increasingly important area of research activities, and many investigations on faulttolerant control have been carried out for linear or nonlinear system [23]. Moreover, in order to enhance the system reliability and to discuss the robustness issue in a spacecraft attitude system against inertia uncertainties and bounded disturbances, an accurate faulttolerant control is needed.…”

Section: Introductionmentioning

confidence: 99%

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Fault-tolerant sampled-data control of flexible spacecraft with probabilistic time delays

2014

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In this paper, fault-tolerant sampled-data control for flexible spacecraft in the presence of external disturbances, partial actuator failures and probabilistic time delays is investigated. In particular, unlike the common assumptions on continuous-time information on control input, a more realistic sampled-data communication strategy is proposed with probabilistic occurrence of time-varying delays which is modeled by introducing Bernoulli distributed sequences. The main purpose of this paper is to derive fault-tolerant sampled-data control law which makes the closed-loop system robustly asymptotically stable with a prescribed upper bound of the cost function about its equilibrium point for all possible actuator failures. More precisely, by constructing an appropriate Lyapunov-Krasovskii functional involving the lower and upper bound of the probabilistic time delay, a new set of sufficient conditions are derived in terms of linear matrix inequalities for achieving the required result. Numerical simulations are presented by taking the real parameters to the considered aircraft model, which is not only highlighting the ensured closed-loop performance by the proposed control law, but also illustrates its superior fault tolerance, fast convergence and robustness in the presence of external disturbances and actuator faults when compared with the conventional controller. The simulation result reveals the effectiveness and potential of the proposed new design techniques.

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Section: Problem Formulation and Preliminariesmentioning

confidence: 99%

Section: Numerical Simulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Fault-tolerant sampled-data control of flexible spacecraft with probabilistic time delays

2014

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“…Mitigation of the periodic disturbances by compensating torques has been proposed by researchers over the course of the past years. Zhang et al [8] presented a fault tolerant control for external disturbances and actuator Another way to improve the attitude accuracy of meteorological satellites is to actively suppress the residual vibrations of flexible appendages. This kind of strategy has been widely used in the attitude maneuver of spacecraft.…”

Section: Introductionmentioning

confidence: 99%

A Study on Optimal Compensation Design for Meteorological Satellites in the Presence of Periodic Disturbance

Cui

Fan

et al. 2018

Applied Sciences

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Featured Application: This work may be used to improve the accuracy of attitude stability of flexible meteorological satellites.Abstract: Periodic disturbance may cause serious effects on the attitude of meteorological satellites, and the attenuation of periodic disturbance is required. In this paper, a fundamental study on the optimal design of constant compensations against known-law periodic disturbance for meteorological satellites is investigated. An analytical solution for the relationship between the frequency and amplitude ratios and the response of a typical second-order vibration system is firstly derived. The compensation and disturbance torques are determined according to practical engineering. The criteria for designing the optimal compensations are based on the analytical and simulation results. Then, the criteria are applied to a flexible spacecraft actuated by constant control torque in the presence of sustained periodic disturbance. The optimal compensation torque parameters for spacecraft are acquired based on former criteria. The compensate effectiveness of the optimal compensation torque is provided and compared with results of other selections in the frequency and amplitude ratio domain. Numerical simulation results and experimental results clearly demonstrate the good performance of proposed criteria. This work provides a significant reference for the vibration attenuation of meteorological satellites in the present of periodic disturbance.

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“…Xiao et al [33] proposed a fault-tolerant controller for a flexible spacecraft in the presence of possible additive fault and partial loss of actuator effectiveness fault. Zhang et al [34] presented a robust fault-tolerant control scheme to achieve attitude control of flexible spacecraft with disturbances and actuator failures. These control algorithms can tolerate partial loss of actuator effectiveness.…”

Section: Introductionmentioning

confidence: 99%

Anti-Unwinding Attitude Control with Fixed-Time Convergence for a Flexible Spacecraft

Pukdeboon

Jitpattanakul

2017

International Journal of Aerospace Engineering

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This paper investigates the fixed-time attitude tracking control problem for flexible spacecraft with unknown bounded disturbances. First, with the knowledge of norm upper bounds of external disturbances and the coupling effect of flexible modes, a novel robust fixed-time controller is designed to deal with this problem. Second, the controller is further enhanced by an adaptive law to avoid the knowledge of norm upper bounds of external disturbances and coupling effect of flexible modes. This control law guarantees the convergence of attitude tracking errors in fixed time where the settling time is bounded by a constant independent of initial conditions. Moreover, the proposed controllers can prevent the unwinding phenomenon. Simulation results are presented to demonstrate the performance of the proposed control scheme.

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Robust fault-tolerant control for flexible spacecraft against partial actuator failures

Cited by 66 publications

References 26 publications

Fault-tolerant sampled-data control of flexible spacecraft with probabilistic time delays

Fault-tolerant sampled-data control of flexible spacecraft with probabilistic time delays

A Study on Optimal Compensation Design for Meteorological Satellites in the Presence of Periodic Disturbance

Anti-Unwinding Attitude Control with Fixed-Time Convergence for a Flexible Spacecraft

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