Determination of orbital elements for formation assembly problem
Determination of orbital elements for formation assembly problem
In this paper, we derive general relationships between the coordinates of the spacecraft in the Hill frame and their actual orbital elements for a closely placed formation with the help of Euler transformation matrices. Then, with the help of the results, we represent the orbital elements as a function of relative coordinates with respect to a reference spacecraft for an Earth-based scenario. The knowledge of orbital elements of the satellites in a formation help to plan ahead the necessary maneuvers to establish a desired configuration pattern
2641-2646
Balaji, S.K.
3e3f4d8a-c9b3-4cc0-afd5-c630bcda4f63
Tatnall, A.R.L.
2c9224b6-4faa-4bfd-9026-84e37fa6bdf3
2004
Balaji, S.K.
3e3f4d8a-c9b3-4cc0-afd5-c630bcda4f63
Tatnall, A.R.L.
2c9224b6-4faa-4bfd-9026-84e37fa6bdf3
Balaji, S.K. and Tatnall, A.R.L.
(2004)
Determination of orbital elements for formation assembly problem.
In Proceedings of the IEEE Aerospace Conference 2004.
IEEE.
.
(doi:10.1109/AERO.2004.1368059).
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Conference or Workshop Item
(Paper)
Abstract
In this paper, we derive general relationships between the coordinates of the spacecraft in the Hill frame and their actual orbital elements for a closely placed formation with the help of Euler transformation matrices. Then, with the help of the results, we represent the orbital elements as a function of relative coordinates with respect to a reference spacecraft for an Earth-based scenario. The knowledge of orbital elements of the satellites in a formation help to plan ahead the necessary maneuvers to establish a desired configuration pattern
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Published date: 2004
Venue - Dates:
IEEE Aerospace Conference 2004, Big Sky, USA, 2004-03-06 - 2004-03-13
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Local EPrints ID: 22685
URI: http://eprints.soton.ac.uk/id/eprint/22685
PURE UUID: 91430be5-1d15-40c9-b73a-596940733c2d
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Date deposited: 09 Mar 2007
Last modified: 15 Mar 2024 06:39
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Author:
S.K. Balaji
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