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

Shinji Hokamoto, Kazuo Setoyama

Research output: Chapter in Book/Report/Conference proceedingConference contribution

1 Citation (Scopus)

Abstract

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.

Original languageEnglish
Title of host publicationInternational Astronautical Federation - 56th International Astronautical Congress 2005
Pages3105-3111
Number of pages7
Volume5
Publication statusPublished - 2005
EventInternational Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, Japan
Duration: Oct 17 2005Oct 21 2005

Other

OtherInternational Astronautical Federation - 56th International Astronautical Congress 2005
Country/TerritoryJapan
CityFukuoka
Period10/17/0510/21/05

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

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