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Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion

Research output: Contribution to Journal/Magazine › Journal article › peer-review

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Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion. / Sun, Lichao; Huang, Yanpei; Fei, Haolin et al.
In: Frontiers in Robotics and AI, Vol. 10, 1138115, 14.02.2023.

Research output: Contribution to Journal/Magazine › Journal article › peer-review

Harvard

Sun, L, Huang, Y, Fei, H, Xiao, B, Yeatman, E, Montazeri, A & Wang, Z 2023, 'Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion', Frontiers in Robotics and AI, vol. 10, 1138115. https://doi.org/10.3389/frobt.2023.1138115

APA

Sun, L., Huang, Y., Fei, H., Xiao, B., Yeatman, E., Montazeri, A., & Wang, Z. (2023). Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion. Frontiers in Robotics and AI, 10, Article 1138115. https://doi.org/10.3389/frobt.2023.1138115

Vancouver

Sun L, Huang Y, Fei H, Xiao B, Yeatman E, Montazeri A et al. Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion. Frontiers in Robotics and AI. 2023 Feb 14;10:1138115. doi: 10.3389/frobt.2023.1138115

Author

Sun, Lichao ; Huang, Yanpei ; Fei, Haolin et al. / Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion. In: Frontiers in Robotics and AI. 2023 ; Vol. 10.

Bibtex

@article{c3f098410a7a41daabd63b090fdd9679,
title = "Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion",
abstract = "On-orbit service spacecraft with redundant actuators need to overcome orbital and attitude coupling when performing proximity maneuvers. In addition, transient/steady-state performance is required to fulfill the user-defined requirements. To these ends, this paper introduces a fixed-time tracking regulation and actuation allocation scheme for redundantly actuated spacecraft. The coupling effect of translational and rotational motions is described by dual quaternion. Based on this, we propose a non-singular fast terminal sliding mode controller to guarantee fixed-time tracking performance in the presence of external disturbances and system uncertainties, where the settling time is only dependent on user-defined control parameters rather than initial values. The unwinding problem caused by the redundancy of dual quaternion is handled by a novel attitude error function. Moreover, optimal quadratic programming is incorporated into null space pseudo-inverse control allocation that ensures the actuation smoothness and never violates the maximum output capability of each actuator. Numerical simulations on a spacecraft platform with symmetric thruster configuration demonstrate the validity of the proposed approach.",
keywords = "dual quaternion, spacecraft control, fixed-time stability, control torque allocation, optimization",
author = "Lichao Sun and Yanpei Huang and Haolin Fei and Bo Xiao and Eric Yeatman and Allahyar Montazeri and Ziwei Wang",
year = "2023",
month = feb,
day = "14",
doi = "10.3389/frobt.2023.1138115",
language = "English",
volume = "10",
journal = "Frontiers in Robotics and AI",
issn = "2296-9144",
publisher = "Frontiers Media S.A.",

}

RIS

TY - JOUR

T1 - Fixed-time regulation of spacecraft orbit and attitude coordination with optimal actuation allocation using dual quaternion

AU - Sun, Lichao

AU - Huang, Yanpei

AU - Fei, Haolin

AU - Xiao, Bo

AU - Yeatman, Eric

AU - Montazeri, Allahyar

AU - Wang, Ziwei

PY - 2023/2/14

Y1 - 2023/2/14

N2 - On-orbit service spacecraft with redundant actuators need to overcome orbital and attitude coupling when performing proximity maneuvers. In addition, transient/steady-state performance is required to fulfill the user-defined requirements. To these ends, this paper introduces a fixed-time tracking regulation and actuation allocation scheme for redundantly actuated spacecraft. The coupling effect of translational and rotational motions is described by dual quaternion. Based on this, we propose a non-singular fast terminal sliding mode controller to guarantee fixed-time tracking performance in the presence of external disturbances and system uncertainties, where the settling time is only dependent on user-defined control parameters rather than initial values. The unwinding problem caused by the redundancy of dual quaternion is handled by a novel attitude error function. Moreover, optimal quadratic programming is incorporated into null space pseudo-inverse control allocation that ensures the actuation smoothness and never violates the maximum output capability of each actuator. Numerical simulations on a spacecraft platform with symmetric thruster configuration demonstrate the validity of the proposed approach.

AB - On-orbit service spacecraft with redundant actuators need to overcome orbital and attitude coupling when performing proximity maneuvers. In addition, transient/steady-state performance is required to fulfill the user-defined requirements. To these ends, this paper introduces a fixed-time tracking regulation and actuation allocation scheme for redundantly actuated spacecraft. The coupling effect of translational and rotational motions is described by dual quaternion. Based on this, we propose a non-singular fast terminal sliding mode controller to guarantee fixed-time tracking performance in the presence of external disturbances and system uncertainties, where the settling time is only dependent on user-defined control parameters rather than initial values. The unwinding problem caused by the redundancy of dual quaternion is handled by a novel attitude error function. Moreover, optimal quadratic programming is incorporated into null space pseudo-inverse control allocation that ensures the actuation smoothness and never violates the maximum output capability of each actuator. Numerical simulations on a spacecraft platform with symmetric thruster configuration demonstrate the validity of the proposed approach.

KW - dual quaternion

KW - spacecraft control

KW - fixed-time stability

KW - control torque allocation

KW - optimization

U2 - 10.3389/frobt.2023.1138115

DO - 10.3389/frobt.2023.1138115

M3 - Journal article

VL - 10

JO - Frontiers in Robotics and AI

JF - Frontiers in Robotics and AI

SN - 2296-9144

M1 - 1138115

ER -