Attitude Control Method of Spin-Stabilized Satellite Base on Equiangular Precession
Yonggang Li, Jiping Ren, Libing Guo, Wen Mao, Yi Wang
Available Online November 2016.
- 10.2991/aiea-16.2016.55How to use a DOI?
- Spin-stabilized Satellite; Attitude Control; Equiangular Precession; Theory Executing Angular; Executing Times.
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.
- © 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/).
Cite this article
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 -