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Precise modelling of relative trajectory for formation flying spacecraft

Precise modelling of relative trajectory for formation flying spacecraft
Precise modelling of relative trajectory for formation flying spacecraft
Relative spacecraft motion has long been a problem for mission analysts who plan rendezvous maneuvers. These planners look to the solution devised by Clohessy and Wiltshire as their primary analysis tool. The Clohessy-Wiltshire (CW) equations are usually sufficient for the rendezvous problem that is of short duration and has frequent thruster firings. Consequently, the long-term accuracy of the equations of motion is not as important in the rendezvous problem as in the formation-flying problem. The errors resulting from the assumptions made in the CW equations such as circular reference orbit, very close target orbit are unacceptable for the long-term prediction of relative motion needed for formation flying satellites. A precise analytic solution for the relative motion of and formation flying satellites is needed to minimize fuel consumption and maximize lifetime. In this paper, we derive the relative coordinates of a deputy satellite with respect to a master satellite by a series of transformations and translations from the Earth-centered inertial frame to the spacecraftcentered rotating frame. The equations of relative coordinates derived in this paper are very precise and can be used to analyze orbits of any eccentricity and of any initial separation with or without the inclusion of orbit perturbations.
American Institute of Aeronautics and Astronautics
Balaji, S.K.
3e3f4d8a-c9b3-4cc0-afd5-c630bcda4f63
Tatnall, A.R.L.
2c9224b6-4faa-4bfd-9026-84e37fa6bdf3
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. (2003) Precise modelling of relative trajectory for formation flying spacecraft. In Proceedings of the 54th International Astronautical Federation (IAF) Congress. American Institute of Aeronautics and Astronautics..

Record type: Conference or Workshop Item (Paper)

Abstract

Relative spacecraft motion has long been a problem for mission analysts who plan rendezvous maneuvers. These planners look to the solution devised by Clohessy and Wiltshire as their primary analysis tool. The Clohessy-Wiltshire (CW) equations are usually sufficient for the rendezvous problem that is of short duration and has frequent thruster firings. Consequently, the long-term accuracy of the equations of motion is not as important in the rendezvous problem as in the formation-flying problem. The errors resulting from the assumptions made in the CW equations such as circular reference orbit, very close target orbit are unacceptable for the long-term prediction of relative motion needed for formation flying satellites. A precise analytic solution for the relative motion of and formation flying satellites is needed to minimize fuel consumption and maximize lifetime. In this paper, we derive the relative coordinates of a deputy satellite with respect to a master satellite by a series of transformations and translations from the Earth-centered inertial frame to the spacecraftcentered rotating frame. The equations of relative coordinates derived in this paper are very precise and can be used to analyze orbits of any eccentricity and of any initial separation with or without the inclusion of orbit perturbations.

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More information

Published date: 2003
Additional Information: IAC-03-A.P.15
Venue - Dates: 54th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law, 2003-09-29 - 2003-10-03

Identifiers

Local EPrints ID: 22683
URI: https://eprints.soton.ac.uk/id/eprint/22683
PURE UUID: 059f1edb-398a-4c09-af0d-ae2a4d358a49

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Date deposited: 09 Mar 2007
Last modified: 05 Dec 2018 17:34

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