Attitude Control Method of Spin-Stabilized Satellite Base on Equiangular Precession

DOI

10.2991/aiea-16.2016.55How to use a DOI?

Keywords

Spin-stabilized Satellite; Attitude Control; Equiangular Precession; Theory Executing Angular; Executing Times.

Abstract

Attitude control is a basic task of a spin-stabilized satellite control. There are many kinds of attitude control methods, this paper does research for equiangular precession method. The paper first introduced the basic principle of equiangular precession method, and then gave out a detailed calculation method of attitude control quantity, which included theory executing angular, executing times and time delay, finally attitude maneuver process were simulated. The simulation result shows that the computed result of attitude control quantity is correct, the forecasts for control process are essentially the same as practice. The method has been applied to satellite launch mission.

Copyright

© 2016, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

Download article (PDF)

TY  - CONF
AU  - Yonggang Li
AU  - Jiping Ren
AU  - Libing Guo
AU  - Wen Mao
AU  - Yi Wang
PY  - 2016/11
DA  - 2016/11
TI  - Attitude Control Method of Spin-Stabilized Satellite Base on Equiangular Precession
BT  - Proceedings of the 2016 International Conference on Artificial Intelligence and Engineering Applications
PB  - Atlantis Press
SP  - 308
EP  - 313
SN  - 2352-538X
UR  - https://doi.org/10.2991/aiea-16.2016.55
DO  - 10.2991/aiea-16.2016.55
ID  - Li2016/11
ER  -