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Dealing with uncertainties in angles-only initial orbit determination

Dealing with uncertainties in angles-only initial orbit determination
Dealing with uncertainties in angles-only initial orbit determination
A method to deal with uncertainties in initial orbit determination (IOD) is presented. This is based on the use of Taylor differential algebra (DA) to nonlinearly map uncertainties from the observation space to the state space. When a minimum set of observations is available, DA is used to expand the solution of the IOD problem in Taylor series with respect to measurement errors. When more observations are available, high order inversion tools are exploited to obtain full state pseudo-observations at a common epoch. The mean and covariance of these pseudo-observations are nonlinearly computed by evaluating the expectation of high order Taylor polynomials. Finally, a linear scheme is employed to update the current knowledge of the orbit. Angles-only observations are considered and simplified Keplerian dynamics adopted to ease the explanation. Three test cases of orbit determination of artificial satellites in different orbital regimes are presented to discuss the feature and performances of the proposed methodology.
0923-2958
1-16
Armellin, Roberto
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
Di Lizia, Pierluigi
f86916ba-a73b-42a9-8247-558335c21f22
Zanetti, Renato
245aa251-d6d5-431a-8f8a-a21b992ccbe6
Armellin, Roberto
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
Di Lizia, Pierluigi
f86916ba-a73b-42a9-8247-558335c21f22
Zanetti, Renato
245aa251-d6d5-431a-8f8a-a21b992ccbe6

Armellin, Roberto, Di Lizia, Pierluigi and Zanetti, Renato (2016) Dealing with uncertainties in angles-only initial orbit determination. Journal of Celestial Mechanics and Dynamical Astronomy, 1-16. (doi:10.1007/s10569-016-9694-z).

Record type: Article

Abstract

A method to deal with uncertainties in initial orbit determination (IOD) is presented. This is based on the use of Taylor differential algebra (DA) to nonlinearly map uncertainties from the observation space to the state space. When a minimum set of observations is available, DA is used to expand the solution of the IOD problem in Taylor series with respect to measurement errors. When more observations are available, high order inversion tools are exploited to obtain full state pseudo-observations at a common epoch. The mean and covariance of these pseudo-observations are nonlinearly computed by evaluating the expectation of high order Taylor polynomials. Finally, a linear scheme is employed to update the current knowledge of the orbit. Angles-only observations are considered and simplified Keplerian dynamics adopted to ease the explanation. Three test cases of orbit determination of artificial satellites in different orbital regimes are presented to discuss the feature and performances of the proposed methodology.

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Accepted/In Press date: 5 April 2016
e-pub ahead of print date: 3 May 2016
Organisations: Astronautics Group

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Local EPrints ID: 392035
URI: https://eprints.soton.ac.uk/id/eprint/392035
ISSN: 0923-2958
PURE UUID: 96fd727c-4c2f-4d20-8291-8cfd77c3e7d1

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Date deposited: 14 Apr 2016 08:59
Last modified: 19 Jul 2019 05:29

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