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

Shinji Hokamoto; Kazuo Setoyama

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

Shinji Hokamoto, Kazuo Setoyama

Flight Dynamics Lab

Research output: Chapter in Book/Report/Conference proceeding › Conference 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 language	English
Title of host publication	International Astronautical Federation - 56th International Astronautical Congress 2005
Pages	3105-3111
Number of pages	7
Volume	5
Publication status	Published - 2005
Event	International Astronautical Federation - 56th International Astronautical Congress 2005 - Fukuoka, Japan Duration: Oct 17 2005 → Oct 21 2005

Other

Other	International Astronautical Federation - 56th International Astronautical Congress 2005
Country/Territory	Japan
City	Fukuoka
Period	10/17/05 → 10/21/05

All Science Journal Classification (ASJC) codes

Space and Planetary Science
Aerospace Engineering

Cite this

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title = "Orbital control of a tethered satellite system using tether-length variations",

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.",

author = "Shinji Hokamoto and Kazuo Setoyama",

year = "2005",

language = "English",

volume = "5",

pages = "3105--3111",

booktitle = "International Astronautical Federation - 56th International Astronautical Congress 2005",

note = "International Astronautical Federation - 56th International Astronautical Congress 2005 ; Conference date: 17-10-2005 Through 21-10-2005",

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T1 - Orbital control of a tethered satellite system using tether-length variations

AU - Hokamoto, Shinji

AU - Setoyama, Kazuo

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N2 - 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.

AB - 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.

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M3 - Conference contribution

AN - SCOPUS:34250866366

VL - 5

SP - 3105

EP - 3111

BT - International Astronautical Federation - 56th International Astronautical Congress 2005

T2 - International Astronautical Federation - 56th International Astronautical Congress 2005

Y2 - 17 October 2005 through 21 October 2005

ER -

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

Abstract

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All Science Journal Classification (ASJC) codes

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