Adaptive fast sliding mode fault tolerant control integrated with disturbance observer for spacecraft attitude stabilization system

Guo, Bin; Chen, Yong

doi:10.1016/j.isatra.2019.04.014

Cited by 36 publications

(16 citation statements)

References 18 publications

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“…ii) A fixed-time disturbance observer is designed based on the Gudermannian equation. It is noteworthy that the disturbance observers in [17]- [19] were asymptotically stable. Compared with [17]- [19], the convergence time of the proposed observer could be regulated according to system demands.…”

Section: Introductionmentioning

confidence: 96%

“…Due to imaging for the ground target dynamically and continuously, the satellite attitude should be well controlled. To this end, tremendous control methods were applied in the last decades, involving the backstepping control [5], [6], the neural-network control [7]- [11], the adaptive control [12], [13], the event-triggered control [14], [15] and the sliding mode control [16]- [19].…”

Section: Introductionmentioning

confidence: 99%

“…According to Eqs. (13)-(15), we can deduce thaṫ r b st = −[ω b eo ] × r b et − [ω b ob ] × r b st + ) − [ω b eo ] × r b et − [ω b ob ] × r b st Usually, for ensuring the boresight points to the ground target and the drift angle being kept to be zero, thus, define the orthonormal vectors e x , e y , e z with satisfying e z = r e st l , e y = r e st × V e T r e st × V e T, e x = e y × e z e y × e z(19)…”

mentioning

confidence: 99%

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The Attitude Control Algorithm of Agile Optical Satellite Oriented to Nonparallel-Ground-Track-Imaging

Zhao

Hao

et al. 2019

IEEE Access

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This paper concerns the control algorithm oriented to nonparallel-ground-track-imaging for agile optical satellite. Firstly, for obtaining the desired trajectory, the mapping relationship between the satellite attitude and the ground stripe is established by using space vector method. According to the mapping function, an attitude adjustment strategy via constant scanning velocity is proposed. Then, considering the exact information of the external disturbance cannot be obtained and the input saturation problem, a robust anti-saturation tracking controller is designed via fixed-time disturbance observer and integral sliding mode. Finally, the effectiveness of the proposed control algorithm is illustrated by numerical simulation. INDEX TERMS Agile optical satellite, nonparallel-ground-track-imaging, integral sliding mode, disturbance observer, input saturation.

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Section: Introductionmentioning

confidence: 96%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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The Attitude Control Algorithm of Agile Optical Satellite Oriented to Nonparallel-Ground-Track-Imaging

Zhao

Hao

et al. 2019

IEEE Access

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“…The attitude can be determined by processing the recorded data. Many studies considering a rigid spacecraft with three attached control torques perpendicular to the three principal axes have been published, including studies on time-optimal attitude control, (1,2) energy-optimal control, (3) feedback control with input saturation, (4) finite-time output feedback control, (5) adaptive sliding mode control, (6)(7)(8)(9)(10) and path-planning control. (11,12) Because of their smooth operating modes, reaction wheel systems are usually utilized by momentum exchange to achieve and maintain the precise attitudes of a spacecraft.…”

Section: Introductionmentioning

confidence: 99%

“…The control input signals of a reaction wheel system are the wheel torques. Many schemes of actuator fault detection (10) have been introduced to determine whether the control input signals are working precisely. Normally, three reaction wheels are used to control a spacecraft with the wheel axes aligned with the body principal axes.…”

Section: Introductionmentioning

confidence: 99%

Sensor-based Optimal Attitude Reorientation Control Scheme Based on Computational Programming Approach

Gao¹,

Wu²,

Yang³

et al. 2020

Sensors and Materials

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Sensor-based optimal spacecraft attitude reorientation control by momentum exchange based on a computational programming approach is addressed in this study. The control problem of a rigid spacecraft actuated by more than three reaction wheels with an open time of maneuver is considered. The modified Rodrigues parameters for large principal rotations are applied to derive our kinematical model. The introduced algorithm can be realized by attitude sensors, such as rate gyros, with an appropriate arrangement. The cost function to be minimized is defined as a weighted performance index of the time of the maneuver and the integral of the squared sum of wheel-torque magnitudes. Instead of utilizing Pontryagin's minimum principle, an iterative procedure is used to reformulate and solve the optimal reorientation control problem as a constrained nonlinear programming problem. To show the feasibility of the proposed method, numerical simulated results are included for illustration.

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Estimation of attraction domain of nonlinear systems with saturated impulses and input disturbances

et al. 2021

Intl J Robust & Nonlinear

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In this article, the estimation of attraction domain of nonlinear systems with saturated impulses and input disturbances is investigated. The sufficient conditions which can ensure the robust convergence of a class of nonlinear dynamical systems for every initial condition in the attraction domain are established.Moreover, some optimization problems are proposed to design the control gain so as to enlarge the size of the estimation of attraction domain as much as possible with a prespecified decay rate. In addition, the exponential stabilization and the estimation of attraction domain for nonlinear dynamical systems under this saturated impulsive control without disturbances are also studied. Finally, simulation results for a chaotic oscillator are displayed to show the effectiveness and feasibility of our results.

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Adaptive fast sliding mode fault tolerant control integrated with disturbance observer for spacecraft attitude stabilization system

Cited by 36 publications

References 18 publications

The Attitude Control Algorithm of Agile Optical Satellite Oriented to Nonparallel-Ground-Track-Imaging

The Attitude Control Algorithm of Agile Optical Satellite Oriented to Nonparallel-Ground-Track-Imaging

Sensor-based Optimal Attitude Reorientation Control Scheme Based on Computational Programming Approach

Estimation of attraction domain of nonlinear systems with saturated impulses and input disturbances

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