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Researches on optimization of micro‐core attitude parameters

Researches on optimization of micro‐core attitude parameters Purpose – To provide a new method to determine parameters of the attitude determination system facing micro‐core. Design/methodology/approach – Take example for attitude determination systems based on star‐sensor and fiber‐optic gyroscope combination and only based on star‐sensor. The optimum parameters of sensors are obtained by setting up of optimization design model of the attitude determination system adopting genetic algorithm. Findings – Put forward a new concept of micro‐core aiming at a micro satellite. Further aiming at micro‐core, a new method which differs from traditional satellite design methods is adopted in this paper. The method proposed in this paper is instructive to the design of future micro satellites. Research limitations/implications – The method proposed in this paper only applied to attitude determination system. With the development of this method, it is hoped that the method can apply to other systems of a micro satellite. Practical implications – The method proposed in this paper is instructive to the engineering design of a micro satellite. Originality/value – Put forward a new concept of micro‐core, and aiming at its design a new method is proposed to design the attitude determination system by adopting genetic algorithm. The method is different from traditional satellite design methods. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Researches on optimization of micro‐core attitude parameters

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References (18)

Publisher
Emerald Publishing
Copyright
Copyright © 2006 Emerald Group Publishing Limited. All rights reserved.
ISSN
0002-2667
DOI
10.1108/00022660610685521
Publisher site
See Article on Publisher Site

Abstract

Purpose – To provide a new method to determine parameters of the attitude determination system facing micro‐core. Design/methodology/approach – Take example for attitude determination systems based on star‐sensor and fiber‐optic gyroscope combination and only based on star‐sensor. The optimum parameters of sensors are obtained by setting up of optimization design model of the attitude determination system adopting genetic algorithm. Findings – Put forward a new concept of micro‐core aiming at a micro satellite. Further aiming at micro‐core, a new method which differs from traditional satellite design methods is adopted in this paper. The method proposed in this paper is instructive to the design of future micro satellites. Research limitations/implications – The method proposed in this paper only applied to attitude determination system. With the development of this method, it is hoped that the method can apply to other systems of a micro satellite. Practical implications – The method proposed in this paper is instructive to the engineering design of a micro satellite. Originality/value – Put forward a new concept of micro‐core, and aiming at its design a new method is proposed to design the attitude determination system by adopting genetic algorithm. The method is different from traditional satellite design methods.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Sep 1, 2006

Keywords: Optimization techniques; Artificial satellites; Space technology

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