Home News About Us Contact Contributors Disclaimer Privacy Policy Help FAQ

Home
Search
Quick Search
Advanced
Fulltext
Browse
Collections
Persons
My eDoc
Session History
Login
Name:
Password:
Documentation
Help
Support Wiki
Direct access to
document ID:


          Display Documents



  history
ID: 398735.0, MPI für Gravitationsphysik / Laser Interferometry & Gravitational Wave Astronomy
Methods for orbit optimization for the LISA gravitational wave observatory
Authors:Li, Guangyu; Yi, Zhaohua; Heinzel, Gerhard; Rüdiger, Albrecht; Jennrich, Oliver; Wang, Li; Xia, Yan; Zeng, Fei; Zhao, Haibin
Date of Publication (YYYY-MM-DD):2008-05
Title of Journal:International Journal of Software Engineering and Knowledge Engineering
Volume (in Journal):18
Issue / Number:3
Start Page:1021
End Page:1042
Name of Conference/Meeting:3rd International ASTROD Symposium
Place of Conference/Meeting:Beijing, CHINA
(Start) Date of Conference/Meeting
 (YYYY-MM-DD):
2006-07-13
End Date of Conference/Meeting 
 (YYYY-MM-DD):
2006-07-16
Review Status:Peer-review
Audience:Not Specified
Abstract / Description:The Laser Interferometer Space Antenna (LISA) mission is a joint ESA-NASA mission for detecting low-frequency gravitational waves in the frequency range from 0.1mHz to 1Hz, by using accurate distance measurements with laser interferometry between three spacecraft, which will be launched around 2015 and one year later reach their orbits around the Sun. In order to operate successfully, it is crucial for the constellation of the three spacecraft to have extremely high stability. In this paper, several problems of the orbit optimization of the LISA constellation are discussed by using numerical and analytical methods for satisfying the requirements of accuracy. On the basis of the coorbital restricted problem, analytical expressions of the heliocentric distance and the trailing angle to the Earth of the constellation's barycenter are deduced, with the result that the approximate analytical solution of first order will meet the accuracy requirement of the spacecraft orbit design. It is proved that there is a value of the inclination of the constellation plane that will make the variation of the arm-length a minimum. The principle for selecting the optimum starting elements of orbits at any epoch is proposed. The method and programming principles of finding the optimized orbits are also presented together with examples of the optimization design.
External Publication Status:published
Document Type:Conference-Paper
Communicated by:Karsten Danzmann
Affiliations:MPI für Gravitationsphysik/Laser Interferometry & Gravitational Wave Astronomy
MPI für Gravitationsphysik/Teilinstitut Hannover
Identifiers:ISSN:0218-1940
The scope and number of records on eDoc is subject to the collection policies defined by each institute - see "info" button in the collection browse view.