Orbit design for the Laser Interferometer Space Antenna (LISA)

verfasst von: Yan Xia, Guangyu Li, Gerhard Heinzel, Albrecht Rüdiger, Yongjie Luo
Abstract: The Laser Interferometer Space Antenna (LISA) is a joint ESA-NASA mission for detecting low-frequency gravitational waves in the frequency range from 0.1 mHz to 1 Hz, by using accurate laser interferometry between three spacecrafts, which will be launched around 2018 and one year later reach their operational orbits around the Sun. In order to operate successfully, it is crucial for the constellation of the three spacecrafts to have extremely high stability. Based on the study of operational orbits for a 2015 launch, we design the operational orbits of beginning epoch on 2019-03-01, and introduce the method of orbit design and optimization. We design the orbits of the transfer from Earth to the operational orbits, including launch phase and separation phase; furthermore, the relationship between energy requirement and flight time of these two orbit phases is investigated. Finally, an example of the whole orbit design is presented.
Organisationseinheit(en): Institut für Gravitationsphysik
Externe Organisation(en): CAS - Purple Mountain Observatory
Graduate University of Chinese Academy of Sciences
Max-Planck-Institut für Gravitationsphysik (Albert-Einstein-Institut)
Typ: Artikel
Journal: Science China: Physics, Mechanics and Astronomy
Band: 53
Seiten: 179-186
Anzahl der Seiten: 8
ISSN: 1674-7348
Publikationsdatum: 30.01.2010
Publikationsstatus: Veröffentlicht
Peer-reviewed: Ja
ASJC Scopus Sachgebiete: Allgemeine Physik und Astronomie
Elektronische Version(en): https://doi.org/10.1007/s11433-010-0100-7 (Zugang: Geschlossen)

BibTeX

@article{aaf52ad32b984e7b82cfcd707c2c2294,
title = "Orbit design for the Laser Interferometer Space Antenna (LISA)",
abstract = "The Laser Interferometer Space Antenna (LISA) is a joint ESA-NASA mission for detecting low-frequency gravitational waves in the frequency range from 0.1 mHz to 1 Hz, by using accurate laser interferometry between three spacecrafts, which will be launched around 2018 and one year later reach their operational orbits around the Sun. In order to operate successfully, it is crucial for the constellation of the three spacecrafts to have extremely high stability. Based on the study of operational orbits for a 2015 launch, we design the operational orbits of beginning epoch on 2019-03-01, and introduce the method of orbit design and optimization. We design the orbits of the transfer from Earth to the operational orbits, including launch phase and separation phase; furthermore, the relationship between energy requirement and flight time of these two orbit phases is investigated. Finally, an example of the whole orbit design is presented.",
keywords = "Co-orbital restricted problem, Launch energy, Orbit design, Orbit optimization",
author = "Yan Xia and Guangyu Li and Gerhard Heinzel and Albrecht R{\"u}diger and Yongjie Luo",
year = "2010",
month = jan,
day = "30",
doi = "10.1007/s11433-010-0100-7",
language = "English",
volume = "53",
pages = "179--186",
journal = "Science China: Physics, Mechanics and Astronomy",
issn = "1674-7348",
publisher = "Science in China Press",
number = "1",
}