Spacecraft spin axis attitude determination

Author

Emara-Shabaik, H.E.

Author_Institution

Dept. of Syst. Eng., King Fahd Univ. of Pet. & Miner., Dhahran, Saudi Arabia

Volume

28

Issue

2

fYear

1992

fDate

4/1/1992 12:00:00 AM

Firstpage

529

Lastpage

534

Abstract

A mathematical formulation of the spacecraft spin axis attitude determination problem in the form of a norm constrained-least-squares minimization problem is provided. The formulation has a mathematically transparent interpretation as a search for the optimal unit vector on the surface of the unit sphere. Two algorithms are developed and compared by simulation. The results show a tradeoff between estimation accuracy and computational requirements. One algorithm is about three times more accurate than the other and is therefore recommended even though it requires about 20% more in computer storage and operations, and about 50% more in central processing unit time

Keywords

aerospace computing; estimation theory; least squares approximations; minimisation; signal processing; attitude sensor; computer storage; computing time; estimation accuracy; norm constrained-least-squares minimization; optimal unit vector; simulation; spacecraft spin axis attitude; Eigenvalues and eigenfunctions; Equations; Filtering theory; Geometry; Kalman filters; Pollution measurement; Position measurement; Quaternions; Sensor systems; Space vehicles;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/7.144578

Filename

144578