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End-of-life disposal of high elliptical orbit missions: the case of INTEGRAL

End-of-life disposal of high elliptical orbit missions: the case of INTEGRAL
End-of-life disposal of high elliptical orbit missions: the case of INTEGRAL
Nowadays there is international consensus that space activities must be managed to minimize debris generation and risk. The paper presents a method for the end-of-life (EoL) disposal of spacecraft in high elliptical orbits (HEO). The time evolution of HEO is strongly affected by Earth’s oblateness and luni-solar perturbation, and this can cause in the long-term to extended interferences with low Earth orbit (LEO) protected region and uncontrolled Earth re-entry. An EoL disposal concept that exploits the effect of orbital perturbations to reduce the disposal cost is presented. The problem is formulated as a multiobjective optimization problem, which is solved with an evolutionary algorithm. To explore at the best the search space a semi-analytical orbit propagator, which allows the propagation of the orbit motion for 100 years in few seconds, is adopted. The EoL disposal of the INTErnational Gamma-Ray Astrophysics Laboratory (INTEGRAL) mission is used as a practical test-case to show the effectiveness of the proposed methodology
0273-1177
1-15
Armellin, Roberto
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
San-Juan, Juan F.
0b015e57-0ce0-4f06-92e2-444ea16992ec
Lara, Martin
54b62795-ce51-4a8e-8c5f-bd2c92df0c25
Armellin, Roberto
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
San-Juan, Juan F.
0b015e57-0ce0-4f06-92e2-444ea16992ec
Lara, Martin
54b62795-ce51-4a8e-8c5f-bd2c92df0c25

Armellin, Roberto, San-Juan, Juan F. and Lara, Martin (2015) End-of-life disposal of high elliptical orbit missions: the case of INTEGRAL. Advances in Space Research, 1-15. (doi:10.1016/j.asr.2015.03.020).

Record type: Article

Abstract

Nowadays there is international consensus that space activities must be managed to minimize debris generation and risk. The paper presents a method for the end-of-life (EoL) disposal of spacecraft in high elliptical orbits (HEO). The time evolution of HEO is strongly affected by Earth’s oblateness and luni-solar perturbation, and this can cause in the long-term to extended interferences with low Earth orbit (LEO) protected region and uncontrolled Earth re-entry. An EoL disposal concept that exploits the effect of orbital perturbations to reduce the disposal cost is presented. The problem is formulated as a multiobjective optimization problem, which is solved with an evolutionary algorithm. To explore at the best the search space a semi-analytical orbit propagator, which allows the propagation of the orbit motion for 100 years in few seconds, is adopted. The EoL disposal of the INTErnational Gamma-Ray Astrophysics Laboratory (INTEGRAL) mission is used as a practical test-case to show the effectiveness of the proposed methodology

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Accepted/In Press date: 18 March 2015
Published date: 26 March 2015
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 377351
URI: http://eprints.soton.ac.uk/id/eprint/377351
ISSN: 0273-1177
PURE UUID: a6171b44-84cd-47cd-83a9-bf23e781ceaf

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Date deposited: 29 May 2015 11:11
Last modified: 18 Nov 2019 20:24

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