Multi-objective optimisation for spacecraft design for demise and survivability
Multi-objective optimisation for spacecraft design for demise and survivability
The paper presents the development of a multi-objective optimisation framework to study the effects that preliminary design choices have on the demisability and the survivability of a spacecraft. Building a spacecraft such that most of it will demise during the re-entry through design-for-demise strategies may lead to design that are more vulnerable to space debris impacts, thus compromising the reliability of the mission. The two models developed to analyse the demisability and the survivability are presented and used as the objective functions of the multi-objective optimisation of the external structure of a simplified spacecraft configuration. The results are presented in the form of Pareto fronts and selected solutions are used to test a spacecraft configuration with internal components in order to better assess the quality of the solutions.
design-for-demise, survivability, multi-objective optimisation, re-entry, space debris, debris impacts, Shielding
Trisolini, Mirko
5637d517-3e44-47d1-8575-9df804914449
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Lewis, Hugh
e9048cd8-c188-49cb-8e2a-45f6b316336a
November 2017
Trisolini, Mirko
5637d517-3e44-47d1-8575-9df804914449
Colombo, Camilla
595ced96-9494-40f2-9763-ad4a0f96bc86
Lewis, Hugh
e9048cd8-c188-49cb-8e2a-45f6b316336a
Trisolini, Mirko, Colombo, Camilla and Lewis, Hugh
(2017)
Multi-objective optimisation for spacecraft design for demise and survivability.
Stardust Conference on Asteroids and Space Debris, Netherlands.
31 Oct - 03 Nov 2016.
Record type:
Conference or Workshop Item
(Paper)
Abstract
The paper presents the development of a multi-objective optimisation framework to study the effects that preliminary design choices have on the demisability and the survivability of a spacecraft. Building a spacecraft such that most of it will demise during the re-entry through design-for-demise strategies may lead to design that are more vulnerable to space debris impacts, thus compromising the reliability of the mission. The two models developed to analyse the demisability and the survivability are presented and used as the objective functions of the multi-objective optimisation of the external structure of a simplified spacecraft configuration. The results are presented in the form of Pareto fronts and selected solutions are used to test a spacecraft configuration with internal components in order to better assess the quality of the solutions.
Text
Stardust - Mirko Trisolini - Extended Abstract
- Version of Record
More information
Accepted/In Press date: 23 September 2016
e-pub ahead of print date: 4 November 2016
Published date: November 2017
Venue - Dates:
Stardust Conference on Asteroids and Space Debris, Netherlands, 2016-10-31 - 2016-11-03
Keywords:
design-for-demise, survivability, multi-objective optimisation, re-entry, space debris, debris impacts, Shielding
Identifiers
Local EPrints ID: 406877
URI: http://eprints.soton.ac.uk/id/eprint/406877
PURE UUID: 6df38122-2032-46b7-9b26-55e6ee88c274
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Date deposited: 25 Mar 2017 02:03
Last modified: 16 Mar 2024 02:55
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Contributors
Author:
Mirko Trisolini
Author:
Camilla Colombo
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