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ABOUT THE DEMISABILITY OF PROPELLANT TANKS DURING ATMOSPHERIC RE-ENTRY FROM LEO

Lips, Tobias and Fritsche, Bent and Kanzler, Ronny and Schleutker, Thorn and Gülhan, Ali and Bonvoisin, Benoit and Soares, Tiago and Sinnema, Gerben (2016) ABOUT THE DEMISABILITY OF PROPELLANT TANKS DURING ATMOSPHERIC RE-ENTRY FROM LEO. In: IASS Eighth Conference Proceedings. Eighth IAASS Conference, 18.-20. Mai 2016, Melbourne, Florida, USA.

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Official URL: http://iaass.space-safety.org/proceedings/

Abstract

The concern about the on-ground risk caused by spacecraft fragments surviving atmospheric re-entry has significantly grown during the past decade, resulting in numerous activities of the space community like re-entry simulation tool development, improvement, and validation, as well as research for design-for-demise (D4D). The purpose of the first group is to increase the confidence in numerical re-entry risk predictions, while the second activity aims to develop new spacecraft design techniques which are likely to improve the demise behavior significantly. Standard (Titanium) propellant tanks for LEO (Low Earth Orbit) missions appear regularly within the group of spacecraft (satellite) components causing the highest on-ground risk, i.e. in the order of 20% for a 1-ton class Earth observation satellite. Thus, tanks are one of the primary targets for any D4D activity. Various ideas for demisable propellant tank concepts have been published recently, including aluminum tanks (e.g. based on aluminum-lithium alloys) or composite tanks (e.g. Carbon-fiber overwrapped metallic liners). The demonstration of the actual demisability of such new tank concepts has turned out to be difficult, sometimes even questionable. Intensive laboratory tests in arc-jet heated or plasma wind-tunnels and laser facilities have provided extensive results. Numerical simulations have been conducted to reproduce these experimental findings. This paper will contain a critical review of the latest experimental and numerical results about the demisability of satellite propellant tanks during atmospheric re-entry from LEO.

Item URL in elib:https://elib.dlr.de/121514/
Document Type:Conference or Workshop Item (Speech)
Title:ABOUT THE DEMISABILITY OF PROPELLANT TANKS DURING ATMOSPHERIC RE-ENTRY FROM LEO
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Lips, Tobiast.lips (at) htg-gmbh.comUNSPECIFIED
Fritsche, Bentb.fritsche (at) htg-hst.deUNSPECIFIED
Kanzler, Ronnyr.kanzler (at) htg-hst.deUNSPECIFIED
Schleutker, Thornthorn.schleutker (at) dlr.dehttps://orcid.org/0000-0002-1833-2850
Gülhan, AliAli.Guelhan (at) dlr.deUNSPECIFIED
Bonvoisin, BenoitBenoit.Bonvoisin (at) esa.intUNSPECIFIED
Soares, TiagoTiago.Soares (at) esa.intUNSPECIFIED
Sinnema, GerbenGerben.Sinnema (at) esa.intUNSPECIFIED
Date:17 May 2016
Journal or Publication Title:IASS Eighth Conference Proceedings
Refereed publication:No
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Demisability, propellant tanks, atmospheric re-entry
Event Title:Eighth IAASS Conference
Event Location:Melbourne, Florida, USA
Event Type:international Conference
Event Dates:18.-20. Mai 2016
Organizer:IAASS
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Technology
DLR - Research area:Raumfahrt
DLR - Program:R SY - Technik für Raumfahrtsysteme
DLR - Research theme (Project):R - Project Space Debris
Location: Köln-Porz
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Supersonoc and Hypersonic Technology
Deposited By: Schleutker, Thorn
Deposited On:18 Sep 2018 10:18
Last Modified:18 Sep 2018 10:18

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