Details
| Original language | English |
|---|---|
| Pages (from-to) | 179-186 |
| Number of pages | 8 |
| Journal | Science China: Physics, Mechanics and Astronomy |
| Volume | 53 |
| Issue number | 1 |
| Publication status | Published - 30 Jan 2010 |
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
ASJC Scopus subject areas
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In: Science China: Physics, Mechanics and Astronomy, Vol. 53, No. 1, 30.01.2010, p. 179-186.
Research output: Contribution to journal › Article › Research › peer review
}
TY - JOUR
T1 - Orbit design for the Laser Interferometer Space Antenna (LISA)
AU - Xia, Yan
AU - Li, Guangyu
AU - Heinzel, Gerhard
AU - Rüdiger, Albrecht
AU - Luo, Yongjie
PY - 2010/1/30
Y1 - 2010/1/30
N2 - 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.
AB - 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.
KW - Co-orbital restricted problem
KW - Launch energy
KW - Orbit design
KW - Orbit optimization
UR - http://www.scopus.com/inward/record.url?scp=77649088950&partnerID=8YFLogxK
U2 - 10.1007/s11433-010-0100-7
DO - 10.1007/s11433-010-0100-7
M3 - Article
AN - SCOPUS:77649088950
VL - 53
SP - 179
EP - 186
JO - Science China: Physics, Mechanics and Astronomy
JF - Science China: Physics, Mechanics and Astronomy
SN - 1674-7348
IS - 1
ER -