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 | Japan |
| City | Fukuoka |
| Period | 10/17/05 → 10/21/05 |
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All Science Journal Classification (ASJC) codes
- Space and Planetary Science
- Aerospace Engineering
Cite this
Orbital control of a tethered satellite system using tether-length variations. / Hokamoto, Shinji; Setoyama, Kazuo.
International Astronautical Federation - 56th International Astronautical Congress 2005. Vol. 5 2005. p. 3105-3111.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Orbital control of a tethered satellite system using tether-length variations
AU - Hokamoto, Shinji
AU - Setoyama, Kazuo
PY - 2005
Y1 - 2005
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
VL - 5
SP - 3105
EP - 3111
BT - International Astronautical Federation - 56th International Astronautical Congress 2005
ER -