Modeling and Attitude Control of a Spinning Spacecraft with Internal Moving Mass

Authors
Pengfei Guo, Liangyu Zhao
Corresponding Author
Pengfei Guo
Available Online March 2013.
DOI
https://doi.org/10.2991/iccsee.2013.733How to use a DOI?
Keywords
spinning spacecraft, moving mass, LQR, attitude control
Abstract
An attitude control system of a spinning spacecraft with internal moving mass is presented in this paper. This system consists of a rigid body and two internal radial moving masses. The mathematical model, including attitude kinematics and nonlinear dynamics equations, is established based on Newtonian mechanics. The control law is designed based on the linear-quadratic-regulator (LQR) theory. The performance of the controller is demonstrated in numerical simulation, and the response shows that the attitude control system is stable and effective.
Open Access
This is an open access article distributed under the CC BY-NC license.

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Proceedings
Proceedings of the 2nd International Conference on Computer Science and Electronics Engineering
Part of series
Advances in Intelligent Systems Research
Publication Date
March 2013
ISBN
978-90-78677-61-1
ISSN
1951-6851
DOI
https://doi.org/10.2991/iccsee.2013.733How to use a DOI?
Open Access
This is an open access article distributed under the CC BY-NC license.

Cite this article

TY  - CONF
AU  - Pengfei Guo
AU  - Liangyu Zhao
PY  - 2013/03
DA  - 2013/03
TI  - Modeling and Attitude Control of a Spinning Spacecraft with Internal Moving Mass
BT  - Proceedings of the 2nd International Conference on Computer Science and Electronics Engineering
PB  - Atlantis Press
SP  - 3172
EP  - 3175
SN  - 1951-6851
UR  - https://doi.org/10.2991/iccsee.2013.733
DO  - https://doi.org/10.2991/iccsee.2013.733
ID  - Guo2013/03
ER  -