Robust fault-tolerant attitude control of spacecraft using hybrid actuators

Xu, Yiqi

doi:10.1108/aeat-09-2020-0200

Cited by 3 publications

(2 citation statements)

References 32 publications

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“…In [ 22 ], an LMI-based robust control allocation was employed to deal with the problem of distributing the three-axis torques over the reaction wheels. In [ 23 ], an online robust control allocation scheme was proposed to redistribute virtual control signals to the actuators taking into account the actuator saturation, uncertainties and faults. The scheme allows a smooth switch between thrusters and reaction wheels, which handles the inaccuracy problem of thrusters and the saturation problem of reaction wheels.…”

Section: Introductionmentioning

confidence: 99%

Robust Control Allocation for Space Inertial Sensor under Test Mass Release Phase with Overcritical Conditions

Zhang

Tao

et al. 2023

Sensors

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This paper proposes a robust control allocation for the capture control of the space inertial sensor’s test mass under overcritical conditions. Uncertainty factors of the test mass control system under the overcritical condition are analyzed first, and a 6-DOF test mass dynamics model with system uncertainty is established. Subsequently, a time-varying weight function is designed to coordinate the allocation of 6-DOF generalized forces. Moreover, a robust control allocation method is proposed to distribute the commanded forces and torques into individual electrodes in an optimal manner, which takes into account the system uncertainties. This method transforms the robust control allocation problem into a second-order cone optimization problem, and its dual problem is introduced to simplify the computational complexity and improve the solving efficiency. Numerical simulation results are presented to illustrate and highlight the fine performance benefits obtained using the proposed robust control allocation method, which improves capture efficiency, increases the security margin and reduces allocation errors.

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Section: Introductionmentioning

confidence: 99%

Robust Control Allocation for Space Inertial Sensor under Test Mass Release Phase with Overcritical Conditions

Zhang

Tao

et al. 2023

Sensors

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“…Spacecraft maneuver control is essential technologies in space missions, such as deep-space explorations, resource exploration, disaster warning and military reconnaissance (Jia et al, 2019;Sun et al, 2018Sun et al, , 2020Xu, 2021;Zhang et al, 2021Zhang et al, , 2020. Unlike attitude-only or orbit-only control missions, attitude and orbit motion of rigid spacecraft must be fully considered in the controller design and stability analysis.…”

Section: Introductionmentioning

confidence: 99%

Non-singular fixed-time pose tracking control for spacecraft with dead-zone input

Chen

Zhang

et al. 2022

AEAT

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Purpose The purpose of this paper is to investigate the pose control of rigid spacecraft subject to dead-zone input, unknown external disturbance and parametric uncertainty in space maneuvering mission. Design/methodology/approach First, a 6-Degree of Freedom (DOF) dynamic model of rigid spacecraft with dead-zone input, unknown external disturbances and parametric uncertainty is derived. Second, a super-twisting-like fixed-time disturbance observer (FTDO) with strong robustness is developed to estimate the lumped disturbances in fixed time. Based on the proposed observer, a non-singular fixed-time terminal sliding-mode (NFTSM) controller with superior performance is proposed. Findings Different from the existing sliding-mode controllers, the proposed control scheme can directly avoid the singularity in the controller design and speed up the convergence rate with improved control accuracy. Moreover, no prior knowledge of lumped disturbances’ upper bound and its first derivatives is required. The fixed-time stability of the entire closed-loop system is rigorously proved in the Lyapunov framework. Finally, the effectiveness and superiority of the proposed control scheme are proved by comparison with existing approaches. Research limitations/implications The proposed NFTSM controller can merely be applied to a specific type of spacecrafts, as the relevant system states should be measurable. Practical implications A NFTSM controller based on a super-twisting-like FTDO can efficiently deal with dead-zone input, unknown external disturbance and parametric uncertainty for spacecraft pose control. Originality/value This investigation uses NFTSM control and super-twisting-like FTDO to achieve spacecraft pose control subject to dead-zone input, unknown external disturbance and parametric uncertainty.

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Spacecraft attitude control based on generalised dynamic inversion with adaptive neural network

Jafri,

Aslam

2023

Aeronaut. j.

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This paper proposes a robust generalised dynamic inversion (GDI) control system design with adaptive neural network (NN) estimation for spacecraft attitude tracking under the absence of knowledge of the spacecraft inertia parameters. The robust GDI control system works to enforce attitude tracking, and the adaptive NN augmentation compensates for the lack of knowledge of the spacecraft inertia parameters. The baseline GDI control law consists of a particular part and an auxiliary part. The particular part of the GDI control law works to realise a desired attitude dynamics of the spacecraft, and the auxiliary part works for finite-time stabilisation of the spacecraft angular velocity. Robustness against modeling uncertainties and external disturbances is provided by augmenting a siding mode control element within the particular part of the GDI control law. The singularity that accompanies GDI control is avoided by modifying the Moore-Penrose generalised inverse by means of a dynamic scaling factor. The NN weighting matrices are updated adaptively through a control Lyapunov function. A detailed stability analysis shows that the closed loop system is semi-global practically stable. For performance assessment, a spacecraft model is developed, and GDI-NN control is investigated for its attitude control problem through numerical simulations. Simulation results reveal the efficacy, robustness and adaptive attributes of proposed GDI-NN control for its application to spacecraft attitude control.

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Robust fault-tolerant attitude control of spacecraft using hybrid actuators

Cited by 3 publications

References 32 publications

Robust Control Allocation for Space Inertial Sensor under Test Mass Release Phase with Overcritical Conditions

Robust Control Allocation for Space Inertial Sensor under Test Mass Release Phase with Overcritical Conditions

Non-singular fixed-time pose tracking control for spacecraft with dead-zone input

Spacecraft attitude control based on generalised dynamic inversion with adaptive neural network

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