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Continuity equation approach for the analysis of the collision risk due to space debris clouds generated by a fragmentation event

Continuity equation approach for the analysis of the collision risk due to space debris clouds generated by a fragmentation event
Continuity equation approach for the analysis of the collision risk due to space debris clouds generated by a fragmentation event
As the debris population increases, the probability of collisions in space grows. Even a collision involving small objects may produce thousands of fragments due to high orbital velocity and the high energy released in the collision. The propagation of the trajectories of all the objects would be prohibitive in terms of computational time, so simplified models have been proposed to describe the consequences of a collision with a reasonable computational effort. In this work, the consequences of a collision are simulated focusing on the description of the behaviour of the fragments cloud as a whole and applying the continuity equation. A debris cloud in Low Earth Orbit (LEO) is modelled as a fluid, whose spatial density varies with time, under the effect of the Earth's gravity and atmospheric drag. Introducing some simplifying assumptions, such as an exponential model of the atmosphere and the hypothesis of limited eccentricity for the fragments' orbits, an analytical expression for the cloud density evolution in time is derived. This novel approach enables the analysis of a large number of potential fragmentation scenarios that would be time-limited with current numerical methods that rely on the integration of the all the fragment trajectories through semi-analytical expression of the dynamics. Moreover, compared to the approaches where only some representative objects are propagated, this method operates directly on the objects spatial density, which is then used to compute the collision probability.Results will be shown considering different collisions scenarios, considering the fragmentation of satellites at different altitudes and inclinations. In this way, it is possible to identify orbiting objects that, in case of fragmentation, are more likely to generate a debris cloud that can create a hazard to reference operative satellites in LEO
Letizia, Francesca
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Colombo, Camilla
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Lewis, Hugh
e9048cd8-c188-49cb-8e2a-45f6b316336a
Letizia, Francesca
5f9f7e3f-0bf0-4731-9660-2d025def8392
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Lewis, Hugh
e9048cd8-c188-49cb-8e2a-45f6b316336a

Letizia, Francesca, Colombo, Camilla and Lewis, Hugh (2014) Continuity equation approach for the analysis of the collision risk due to space debris clouds generated by a fragmentation event. 65th International Astronautical Congress (IAC2014), Toronto, Canada. 29 Sep - 03 Oct 2014. 12 pp .

Record type: Conference or Workshop Item (Paper)

Abstract

As the debris population increases, the probability of collisions in space grows. Even a collision involving small objects may produce thousands of fragments due to high orbital velocity and the high energy released in the collision. The propagation of the trajectories of all the objects would be prohibitive in terms of computational time, so simplified models have been proposed to describe the consequences of a collision with a reasonable computational effort. In this work, the consequences of a collision are simulated focusing on the description of the behaviour of the fragments cloud as a whole and applying the continuity equation. A debris cloud in Low Earth Orbit (LEO) is modelled as a fluid, whose spatial density varies with time, under the effect of the Earth's gravity and atmospheric drag. Introducing some simplifying assumptions, such as an exponential model of the atmosphere and the hypothesis of limited eccentricity for the fragments' orbits, an analytical expression for the cloud density evolution in time is derived. This novel approach enables the analysis of a large number of potential fragmentation scenarios that would be time-limited with current numerical methods that rely on the integration of the all the fragment trajectories through semi-analytical expression of the dynamics. Moreover, compared to the approaches where only some representative objects are propagated, this method operates directly on the objects spatial density, which is then used to compute the collision probability.Results will be shown considering different collisions scenarios, considering the fragmentation of satellites at different altitudes and inclinations. In this way, it is possible to identify orbiting objects that, in case of fragmentation, are more likely to generate a debris cloud that can create a hazard to reference operative satellites in LEO

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IAC-14-A6-P31_Letizia.pdf - Author's Original
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More information

Published date: 1 October 2014
Venue - Dates: 65th International Astronautical Congress (IAC2014), Toronto, Canada, 2014-09-29 - 2014-10-03
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 368770
URI: http://eprints.soton.ac.uk/id/eprint/368770
PURE UUID: d1c4aaa2-1618-4fcf-ab1a-7176c0ad3393
ORCID for Camilla Colombo: ORCID iD orcid.org/0000-0001-9636-9360
ORCID for Hugh Lewis: ORCID iD orcid.org/0000-0002-3946-8757

Catalogue record

Date deposited: 29 Sep 2014 10:42
Last modified: 15 Mar 2024 02:54

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Contributors

Author: Francesca Letizia
Author: Camilla Colombo ORCID iD
Author: Hugh Lewis ORCID iD

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