DocumentCode
700703
Title
Feedback laws for attitude stabilization via optimal control theory on lie groups
Author
Spindler, K.
Author_Institution
Fachhochschule Wiesbaden, Wiesbaden, Germany
fYear
1997
fDate
1-7 July 1997
Firstpage
1610
Lastpage
1615
Abstract
In this paper we will derive feedback laws to stabilize the attitude motion of a rigid spacecraft in finite time. The laws are such that a cost functional measuring the overall angular velocity during the spacecraft motion is minimized. The implementation of these laws in an on-board attitude control system requires only autonomous attitude determination capabilities and no measurements of the angular velocities.
Keywords
Lie groups; angular velocity control; attitude control; feedback; motion control; optimal control; space vehicles; stability; Lie group; angular velocity; attitude control system; attitude motion stabilization; autonomous attitude determination; cost functional; feedback law; finite time; optimal control theory; rigid spacecraft; spacecraft motion; Algebra; Angular velocity; Attitude control; Integral equations; Optimal control; Position measurement; Space vehicles; Feedback Stabilization; Geometric Control Theory; Optimal Control on Lie Groups; Spacecraft Attitude Control;
fLanguage
English
Publisher
ieee
Conference_Titel
Control Conference (ECC), 1997 European
Conference_Location
Brussels
Print_ISBN
978-3-9524269-0-6
Type
conf
Filename
7082333
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