Suppression of Effects on Model Error in Attitude Control of Spacecraft Using Two Reaction Wheels Considering Initial Angular Momentum

被引：0
|
作者：
Watabe, Kento [1 ]
Fukaishi, Tomohiro [1 ]
Sekiguchi, Kazuma [1 ]
Nonaka, Kenichiro [1 ]
机构：
[1] Tokyo City Univ, Mech Syst Engn, Tokyo, Japan
来源：
2015 54TH ANNUAL CONFERENCE OF THE SOCIETY OF INSTRUMENT AND CONTROL ENGINEERS OF JAPAN (SICE) | 2015年
关键词：
Attitude control of spacecraft; Adaptive control; Non-linear systems; Input output linearization;
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
The attitude control of a spacecraft utilizing only two reaction wheels is proposed in [5]. However, the model error and initial angular momentum are not considered in the model base controller, and that may become a problem when it has been applied to actual spacecraft. In this study, considering the case of unknown initial angular momentum and a model error existing in inertia matrix, we propose an adaptive modification of model parameters. The validity of the proposed method is verified by numerical simulations.
引用
收藏
页码：582 / 587
页数：6
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