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Title: Robust fault-tolerant tracking control for spacecraft proximity operations using time-varying sliding mode
Authors: Hu, Qinglei
Shao, Xiaodong
Chen, Wen-Hua
Keywords: Finite-time convergence
Time-varying sliding mode
Fault-tolerant control
Spacecraft proximity operations
Issue Date: 2017
Publisher: © IEEE
Citation: HU, Q., SHAO, X. and CHEN, W.-H., 2017. Robust fault-tolerant tracking control for spacecraft proximity operations using time-varying sliding mode. IEEE Transactions on Aerospace and Electronic Systems, doi:10.1109/TAES.2017.2729978.
Abstract: The capture of a free-floating tumbling object using an autonomous vehicle is a key technology for many future orbital missions. Spacecraft proximity operations will play an important role in guaranteeing the success of such missions. In this paper, we technically propose a tracking control scheme for proximity operations between a target and a pursuer spacecraft that ensures accurate relative position tracking as well as attitude synchronization. Specifically, an integrated six degrees of freedom dynamics model is first established to describe the relative motion of the pursuer with respect to the target. Then, a robust fault-tolerant controller is derived by combining the sliding mode control and the adaptive technique. The designed controller is proved to be not only robust against unexpected disturbances and adaptive to unknown and uncertain mass/inertia properties of the pursuer, but also able to accommodate a large class of actuator faults. In particular, by incorporating a novel time-varying forcing function into the sliding dynamics, the proposed control algorithm is able to guarantee the finite-time convergence of the translational and rotational tracking errors, and the convergence time as an explicit parameter can be assigned a priori by the designers. Furthermore, a theoretical analysis is also presented to assess the fault tolerance ability of the designed controller. Finally, numerous examples are carried out to evaluate the effectiveness and demonstrate the benefits of the overall control approach.
Description: © 2017 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other uses, in any current or future media, including reprinting/republishing this material for advertising or promotional purposes, creating new collective works, for resale or redistribution to servers or lists, or reuse of any copyrighted component of this work in other works.
Sponsor: This work was supported in part by National Natural Science Foundation of China (61522301, 61633003).
Version: Accepted for publication
DOI: 10.1109/TAES.2017.2729978
URI: https://dspace.lboro.ac.uk/2134/26958
Publisher Link: https://doi.org/10.1109/TAES.2017.2729978
ISSN: 0018-9251
Appears in Collections:Published Articles (Aeronautical and Automotive Engineering)

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