Adaptive attitude tracking control for rigid spacecraft with finite-time convergence

Yuanqing Xia; Jinhui Zhang; Kunfeng Lu; Ning Zhou

doi:10.1007/978-981-13-1373-8_4

Adaptive attitude tracking control for rigid spacecraft with finite-time convergence

Yuanqing Xia^*, Jinhui Zhang, Kunfeng Lu, Ning Zhou

^*Corresponding author for this work

School of Automation

Research output: Chapter in Book/Report/Conference proceeding › Chapter › peer-review

4 Citations (Scopus)

Abstract

In this chapter, the finite-time attitude tracking control problem for rigid spacecraft with external disturbances and inertia uncertainties is addressed. First, a novel fast nonsingular terminal sliding mode surface (FNTSMS) without any constraint is designed, which not only avoids the singularity problem, but also contains the advantages of the nonsingular terminal sliding mode (NTSM) and the conventional sliding-mode together. Second, the proposed FNTSM control laws (FNTSMCLs) by employing FNTSMS associated with adaptation provide finite-time convergence, robustness, faster, higher control precision. The proposed FNTSMCLs in light of novel adaptive control architecture are continuous. Thus, they are chattering-free. Finally, simulation results are presented to illustrate effectiveness of the control strategies. In addition, digital simulations of satellite Hubble Space Telescope (HST) are presented to verify the practical feasibility of the reorientation/ slew maneuvers mission.

Original language	English
Title of host publication	Advances in Industrial Control
Publisher	Springer International Publishing
Pages	51-69
Number of pages	19
DOIs	https://doi.org/10.1007/978-981-13-1373-8_4
Publication status	Published - 2019

Publication series

Name	Advances in Industrial Control
ISSN (Print)	1430-9491
ISSN (Electronic)	2193-1577

Keywords

Adaptive control
Attitude tracking
Fast terminal sliding mode control
Finite-time control
Spacecraft control

Access to Document

10.1007/978-981-13-1373-8_4

Cite this

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title = "Adaptive attitude tracking control for rigid spacecraft with finite-time convergence",

abstract = "In this chapter, the finite-time attitude tracking control problem for rigid spacecraft with external disturbances and inertia uncertainties is addressed. First, a novel fast nonsingular terminal sliding mode surface (FNTSMS) without any constraint is designed, which not only avoids the singularity problem, but also contains the advantages of the nonsingular terminal sliding mode (NTSM) and the conventional sliding-mode together. Second, the proposed FNTSM control laws (FNTSMCLs) by employing FNTSMS associated with adaptation provide finite-time convergence, robustness, faster, higher control precision. The proposed FNTSMCLs in light of novel adaptive control architecture are continuous. Thus, they are chattering-free. Finally, simulation results are presented to illustrate effectiveness of the control strategies. In addition, digital simulations of satellite Hubble Space Telescope (HST) are presented to verify the practical feasibility of the reorientation/ slew maneuvers mission.",

keywords = "Adaptive control, Attitude tracking, Fast terminal sliding mode control, Finite-time control, Spacecraft control",

author = "Yuanqing Xia and Jinhui Zhang and Kunfeng Lu and Ning Zhou",

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AU - Xia, Yuanqing

AU - Zhang, Jinhui

AU - Lu, Kunfeng

AU - Zhou, Ning

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PY - 2019

Y1 - 2019

N2 - In this chapter, the finite-time attitude tracking control problem for rigid spacecraft with external disturbances and inertia uncertainties is addressed. First, a novel fast nonsingular terminal sliding mode surface (FNTSMS) without any constraint is designed, which not only avoids the singularity problem, but also contains the advantages of the nonsingular terminal sliding mode (NTSM) and the conventional sliding-mode together. Second, the proposed FNTSM control laws (FNTSMCLs) by employing FNTSMS associated with adaptation provide finite-time convergence, robustness, faster, higher control precision. The proposed FNTSMCLs in light of novel adaptive control architecture are continuous. Thus, they are chattering-free. Finally, simulation results are presented to illustrate effectiveness of the control strategies. In addition, digital simulations of satellite Hubble Space Telescope (HST) are presented to verify the practical feasibility of the reorientation/ slew maneuvers mission.

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