Constrained dual-loop attitude control design for spacecraft

Li, Ming-Xiang; Hou, Ming; Yin, Chunwu

doi:10.1016/j.ast.2016.05.024

Cited by 12 publications

(2 citation statements)

References 28 publications

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“…Under angular velocity constraints, a virtual angular velocity command used to stabilise the attitude was designed by a hyperbolic tangent function [30]. Based on a two‐loop structure, Li et al [31] stabilised the attitude under angular velocity constraints by designing an outer‐loop control law. A constrained input‐to‐stable controller was presented by a non‐linear disturbance observer considering assigned angular velocity and control constraints [32].…”

Section: Introductionmentioning

confidence: 99%

Dynamic infinity‐norm constrained control allocation for attitude tracking control of overactuated combined spacecraft

Huang

Duan

2019

IET Control Theory & Applications

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Section: Introductionmentioning

confidence: 99%

Dynamic infinity‐norm constrained control allocation for attitude tracking control of overactuated combined spacecraft

Huang

Duan

2019

IET Control Theory & Applications

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“…Since the observer output is fed back to the controller unit, a large initial estimation error may cause a large controller output, leading to, important problems in real conditions. A back stepping controller and a nonlinear observer, 29,30 a Kalman filter, 31,32 a high-order sliding mode controller, and integral SM observer 33 are used to estimate the spacecraft angular velocity.…”

Section: Introductionmentioning

confidence: 99%

Hardware-in-the-loop attitude control via a high-order sliding mode controller/observer

Malekzadeh

Rezayati

Saboohi

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this study, a hardware-in-the-loop implementation of attitude control algorithms based on high-order sliding mode theory is performed and then both compared in terms of performance and functionality. The spacecraft simulator consists of a free-floating platform hinged on a spherical air-bearing support. In order to compensate for the unreliable performance of the rate gyros, a super-twisting sliding mode observer is incorporated to estimate the angular velocities fed back to the controller unit. The proposed scheme makes full use of novel sliding mode methods to alleviate the chattering effects without increasing the control effort; both controllers and observer are tuned to deal with the saturation of reaction wheels with respect to momentum and its rate. The ab initio simulations compared well with the simulator responses, implying that involved instruments including actuators and sensors have been properly emulated. This also proved that the external disturbances were modeled in a reliable manner. The robustness and effectiveness of the proposed scheme have been validated experimentally under extreme circumstances of disturbances and levels of uncertainties.

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Gao,

2023

Spacecraft Maneuver With Performance Guaranteed

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Constrained dual-loop attitude control design for spacecraft

Cited by 12 publications

References 28 publications

Dynamic infinity‐norm constrained control allocation for attitude tracking control of overactuated combined spacecraft

Dynamic infinity‐norm constrained control allocation for attitude tracking control of overactuated combined spacecraft

Hardware-in-the-loop attitude control via a high-order sliding mode controller/observer

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