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.
Attitude control of a bias momentum satellite using moment of inertia
IEEE Transactions on Aerospace and Electronic Systems ; 38 , 1 ; 243-250
2002-01-01
267753 byte
Article (Journal)
Electronic Resource
English
Attitude control of a bias momentum satellite using moment of inertia
Tema Archive | 2002
|PAPERS - Attitude Control of a Bias Momentum Satellite Using Moment of Inertia
Online Contents | 2002
|Attitude Control of Bias-Momentum Small Satellite with Two Wheels
British Library Conference Proceedings | 2002
|Efficient and high precision momentum bias attitude control for small satellite
TIBKAT | 2021
|