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Solar radiation pressure end-of-life disposal for Libration-point orbits in the elliptic restricted three-body problem

Solar radiation pressure end-of-life disposal for Libration-point orbits in the elliptic restricted three-body problem
Solar radiation pressure end-of-life disposal for Libration-point orbits in the elliptic restricted three-body problem
This paper proposes an end-of-life propellant-free disposal strategy for Libration-point orbits in the elliptic restricted three-body problem as an extension of a preliminary study performed in the circular problem. The spacecraft is initially disposed into the unstable manifold leaving the Libration-point orbit, before a reflective sun-pointing surface is deployed to enhance the effect of solar radiation pressure. This allows closing the pulsating zero-velocity curves at the pseudo Libration-point, SL2 such that, the consequent increase in energy prevents the spacecraft returning to Earth. An energy approach is used to compute the required area for the Hill’s curves closure at the pseudo Libration-point SL2, via numerical optimisation. The Gaia mission is selected as an example scenario since a low deployable area is required in the circular case. Guidelines for the end-of-life disposal of future Libration-point orbit missions are proposed.
Soldini, Stefania
6f392822-9b01-4adb-aa37-cff2049bac18
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Walker, Scott J.I.
f28a342f-9755-48fd-94ea-09e44ac4dbf5
Soldini, Stefania
6f392822-9b01-4adb-aa37-cff2049bac18
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Walker, Scott J.I.
f28a342f-9755-48fd-94ea-09e44ac4dbf5

Soldini, Stefania, Colombo, Camilla and Walker, Scott J.I. (2015) Solar radiation pressure end-of-life disposal for Libration-point orbits in the elliptic restricted three-body problem. AAS-AIAA Space Flight Mechanics Meeting, Williamsburg, United States. 11 - 15 Jan 2015.

Record type: Conference or Workshop Item (Paper)

Abstract

This paper proposes an end-of-life propellant-free disposal strategy for Libration-point orbits in the elliptic restricted three-body problem as an extension of a preliminary study performed in the circular problem. The spacecraft is initially disposed into the unstable manifold leaving the Libration-point orbit, before a reflective sun-pointing surface is deployed to enhance the effect of solar radiation pressure. This allows closing the pulsating zero-velocity curves at the pseudo Libration-point, SL2 such that, the consequent increase in energy prevents the spacecraft returning to Earth. An energy approach is used to compute the required area for the Hill’s curves closure at the pseudo Libration-point SL2, via numerical optimisation. The Gaia mission is selected as an example scenario since a low deployable area is required in the circular case. Guidelines for the end-of-life disposal of future Libration-point orbit missions are proposed.

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More information

Published date: January 2015
Venue - Dates: AAS-AIAA Space Flight Mechanics Meeting, Williamsburg, United States, 2015-01-11 - 2015-01-15
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 374426
URI: http://eprints.soton.ac.uk/id/eprint/374426
PURE UUID: fce1c696-bb55-4d01-bd47-74dabf65e236
ORCID for Camilla Colombo: ORCID iD orcid.org/0000-0001-9636-9360

Catalogue record

Date deposited: 17 Feb 2015 14:15
Last modified: 11 Dec 2021 06:02

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Contributors

Author: Camilla Colombo ORCID iD
Author: Scott J.I. Walker

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