Finite-Time Control for Attitude Tracking Maneuver of Rigid Satellite release_q5gnjbvkrraizkvih5x6z7erbi

by Mingyi Huo, Xing Huo, Hamid Reza Karimi, Jianfei Ni

Published in Abstract and Applied Analysis by Hindawi Limited.

2014   Volume 2014, p1-15

Abstract

The problem of finite-time control for attitude tracking maneuver of a rigid spacecraft is investigated. External disturbance, unknown inertia parameters are addressed. As stepping stone, a sliding mode controller is designed. It requires the upper bound of the lumped uncertainty including disturbance and inertia matrix. However, this upper bound may not be easily obtained. Therefore, an adaptive sliding mode control law is then proposed to release that drawback. Adaptive technique is applied to estimate that bound. It is proved that the closed-loop attitude tracking system is finite-time stable. The tracking errors of the attitude and the angular velocity are asymptotically stabilized. Moreover, the upper bound on the lumped uncertainty can be exactly estimated in finite time. The attitude tracking performance with application of the control scheme is evaluated through a numerical example.
In application/xml+jats format

Archived Files and Locations

application/pdf  3.4 MB
file_2kyhwxlczjdc7paqwyjqwaoqxm
downloads.hindawi.com (publisher)
web.archive.org (webarchive)
application/pdf  3.4 MB
file_g5z45qimtjcn7hb6kmbtsrygce
uia.brage.unit.no (web)
web.archive.org (webarchive)
application/pdf  2.0 MB
file_jzpuj6bt4ndpzpto66t6fkm3ke
projecteuclid.org (web)
web.archive.org (webarchive)
Read Archived PDF
Preserved and Accessible
Type  article-journal
Stage   published
Year   2014
Language   en ?
Container Metadata
Open Access Publication
In DOAJ
In ISSN ROAD
In Keepers Registry
ISSN-L:  1085-3375
Work Entity
access all versions, variants, and formats of this works (eg, pre-prints)
Catalog Record
Revision: b568068b-0634-4fcf-a3dd-b20c4c8c25b0
API URL: JSON