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Attitude control system for the nano‐astrometry satellite “Nano‐JASMINE”

Attitude control system for the nano‐astrometry satellite “Nano‐JASMINE” Purpose – This paper aims to present an attitude determination and control system for a nano‐astrometry satellite which requires precise angular rate control. Focus of the research is methods to achieve the requirement. Design/methodology/approach – In order to obtain astrometry data, the satellite attitude should be controlled to an accuracy of 0.05°. Furthermore, attitude spin rate must be controlled to an accuracy of 4×10 −7 rad/s during observation. In this paper the following unique ideas to achieve these requirements are introduced: magnetic disturbance compensation and rate estimation using star blurred images. Findings – This paper presents the feasibility of a high accurate attitude control system in nano‐ and micro‐satellite missions. Practical implications – This paper presents a possibility of the application of nano‐satellites to remote‐sensing and astronomy mission, which requires accurate attitude control. Originality/value – Originalities of the paper are the methods to achieve the high accurate attitude control: magnetic disturbance compensation and angular rate estimation using star images. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Attitude control system for the nano‐astrometry satellite “Nano‐JASMINE”

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References (9)

Publisher
Emerald Publishing
Copyright
Copyright © 2011 Emerald Group Publishing Limited. All rights reserved.
ISSN
0002-2667
DOI
10.1108/00022661111138639
Publisher site
See Article on Publisher Site

Abstract

Purpose – This paper aims to present an attitude determination and control system for a nano‐astrometry satellite which requires precise angular rate control. Focus of the research is methods to achieve the requirement. Design/methodology/approach – In order to obtain astrometry data, the satellite attitude should be controlled to an accuracy of 0.05°. Furthermore, attitude spin rate must be controlled to an accuracy of 4×10 −7 rad/s during observation. In this paper the following unique ideas to achieve these requirements are introduced: magnetic disturbance compensation and rate estimation using star blurred images. Findings – This paper presents the feasibility of a high accurate attitude control system in nano‐ and micro‐satellite missions. Practical implications – This paper presents a possibility of the application of nano‐satellites to remote‐sensing and astronomy mission, which requires accurate attitude control. Originality/value – Originalities of the paper are the methods to achieve the high accurate attitude control: magnetic disturbance compensation and angular rate estimation using star images.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jul 5, 2011

Keywords: Nano‐ and micro‐satellite; Attitude control; Attitude determination; Astronomy; Satellite; Aerospace

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