Orbital control of a tethered satellite system using tether-length variations

Shinji Hokamoto, Kazuo Setoyama

研究成果: Chapter in Book/Report/Conference proceedingConference contribution

1 被引用数 (Scopus)

抄録

This study deals with orbital transfer of a tethered satellite system into a specified orbit (defined in the equatorial plane as a set of semilatus rectum, eccentricity, and augment of pericenter,) by using tether-length variations. While in the 55th IAC conference the tethered satellite system was assumed as a rigid dumbbell type satellite, the tethered satellite system dealt in this paper is not rigid, and the system has only one control input: tether-length variation. By comparing the nature of the systems to that of rigid satellite systems, this paper points out that the timing of changing the tether length on its orbital motion is a key of orbital transfer. And controllability of the system is discussed numerically by examining the distribution of the control effect.

本文言語英語
ホスト出版物のタイトルInternational Astronautical Federation - 56th International Astronautical Congress 2005
ページ3105-3111
ページ数7
5
出版ステータス出版済み - 2005
イベントInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, 日本
継続期間: 10 17 200510 21 2005

その他

その他International Astronautical Federation - 56th International Astronautical Congress 2005
国/地域日本
CityFukuoka
Period10/17/0510/21/05

All Science Journal Classification (ASJC) codes

  • 宇宙惑星科学
  • 航空宇宙工学

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