Attitude control of a bias momentum satellite using moment of inertia

Author

Bang, Hyochoong ; Don Choi, Hyung

Author_Institution

Korea Adv. Inst. of Sci. & Technol., Seoul, South Korea

Volume

38

Issue

1

fYear

2002

fDate

1/1/2002 12:00:00 AM

Firstpage

243

Lastpage

250

Abstract

Analysis on the attitude controller based upon moment of inertia distribution for a bias momentum satellite is discussed. Spacecraft moment of inertia distribution is represented in the form of product of inertia terms in the system inertia matrix. The product of inertia between orthogonal body axes of the satellite is used to build a controller which controls the nutational motion caused by the angular momentum of the wheel. The attitude controller in the pitch axis controlling the pitch motion as well as nutational dynamics in the roll/yaw planes is analyzed in detail. Analytic expressions using linearized equations are derived providing further insight into the dynamic coupling effect among orthogonal body axes

Keywords

aerospace control; artificial satellites; attitude control; angular momentum; attitude control; bias momentum satellite; dynamic coupling; inertia matrix; moment of inertia distribution; nutational motion; orthogonal body axis; pitch motion; spacecraft; Aerodynamics; Aerospace control; Attitude control; Communication system control; Equations; Motion control; Satellites; Space technology; Space vehicles; Wheels;

fLanguage

English

Journal_Title

Aerospace and Electronic Systems, IEEE Transactions on

Publisher

ieee

ISSN

0018-9251

Type

jour

DOI

10.1109/7.993243

Filename

993243