DocumentCode
2857417
Title
Attitude control of an underactuated satellite
Author
Godhavn, John-Morten ; Egeland, Olav
Author_Institution
Div. of Eng. Cybern., Norwegian Inst. of Technol., Trondheim, Norway
Volume
4
fYear
1995
fDate
13-15 Dec 1995
Firstpage
3986
Abstract
A continuous feedback controller with a periodic time varying term for the attitude control of an underactuated rigid spacecraft is derived. The attitude is described with the Euler parameter vector. Due to the nondifferentiable nature of exponential stabilizers, sampling of some measurements is used. Global exponential convergence is indicated with analysis and simulations
Keywords
artificial satellites; attitude control; convergence; feedback; periodic control; Euler parameter vector; attitude control; continuous feedback controller; exponential stabilizer nondifferentiability; global exponential convergence; periodic time-varying term; underactuated rigid spacecraft; underactuated satellite; Adaptive control; Aerospace engineering; Analytical models; Control systems; Convergence; Cybernetics; Sampling methods; Satellites; Space vehicles; State feedback;
fLanguage
English
Publisher
ieee
Conference_Titel
Decision and Control, 1995., Proceedings of the 34th IEEE Conference on
Conference_Location
New Orleans, LA
ISSN
0191-2216
Print_ISBN
0-7803-2685-7
Type
conf
DOI
10.1109/CDC.1995.479227
Filename
479227
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