Paper Info
Title
Observer-Based Continuous Finite-Time Attitude Control For Rigid-Flexible Coupling Satellites
Abstract
In this paper, a novel finite-time attitude control law is proposed for rigid-flexible coupling satellites in large angle manoeuver. First, the rigid-flexible coupling dynamic model is set up to reflect the coupling effect between the deformation of flexible appendages and the spatial movement of the rigid hub. Then an extended state observer (ESO) is designed to estimate and compensate the total perturbation including high-order flexible coupling terms, external disturbances and uncertain inertia. Following this, a continuous finite-time attitude controller is designed based on non-singular fast terminal sliding mode (NFTSM) and fast power reaching law, which is introduced to smooth the control input and eliminate the chattering. Numerical simulation is designed to verify the finite-time stability, high accuracy, disturbance rejectionand vibration damping of the proposed control scheme and then a ground experimental system is set to further test the controller's practicability.
Year
DOI
Venue
2019
10.1080/00207179.2018.1458155
INTERNATIONAL JOURNAL OF CONTROL
Keywords
DocType
Volume
Rigid-flexible coupling spacecraft, finite-time control, extended state observer, non-singular terminal sliding mode, fast power reaching law, rapid manoeuver
Journal
92
Issue
ISSN
Citations 
11
0020-7179
1
PageRank 
References 
Authors
0.41
18
3
Name
Order
Citations
PageRank
Yan Xiao1226.08
Dong Ye2212.18
Sun Zhaowei3426.39