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

页码：582 / 587

页数：6

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