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Improved Representation of Destructive Spacecraft Re-entry from Analysis of High Enthalpy Wind Tunnel Tests of Spacecraft and Equipment

Beck, James und Holbrough, Ian und Schleutker, Thorn und Gülhan, Ali (2018) Improved Representation of Destructive Spacecraft Re-entry from Analysis of High Enthalpy Wind Tunnel Tests of Spacecraft and Equipment. 69th International Astronautical Congress, 2018-10-01 - 2018-10-05, Bremen, Deutschland.

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Kurzfassung

The assessment of casualty risk in destructive re-entry has historically been performed purely by simulation using heating correlations, which only have verification on basic shapes, and estimated phenomenology for fragmentation. As the application of space debris mitigation requirements is expected to result in a higher number of re-entries, this has brought a stricter enforcement of the casualty risk guidelines to proposed missions. In turn, this has increased the interest in designing spacecraft to demise in re-entry in order to allow uncontrolled re-entries to be performed. Initial testing of spacecraft materials and basic structures has demonstrated that the destructive re-entry tools do not capture the correct physics to be able to assist design in a meaningful way, and therefore, some means to improve the representativeness of the tools is required. The current understanding of the phenomenology of the fragmentation and demise processes is limited. As a consequence, it is vital to perform appropriate tests in order to improve the capability of the tools to assist the design process. To this end, a set of destructive tests on spacecraft materials, structures and components has been performed in an arc-heated supersonic wind tunnel. These tests include the first destructive wind tunnel tests ever performed on a complete nano-satellite and on a reaction wheel. From these tests, it has been determined that the failure of aluminium structures is highly dependent upon the behaviour of the protective metal oxide layer, and that this can be catastrophic in nature. The tests on the nano-satellite have shown that the structure can be supported by stainless steel spacers between the electronics cards, and that glass fibre reinforced plastic PCBs are more resistant to melting than had been anticipated. The reaction wheel test has shown that the connections between parts are critical to the fragmentation and demise processes, as the glued housing separates quickly, well before melt temperature is reached at the joint. It has also demonstrated the importance of radiative cooling, as the flywheel and ball-bearing unit have survived a test at over 800kW/m² with little damage.

elib-URL des Eintrags:https://elib.dlr.de/125250/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Improved Representation of Destructive Spacecraft Re-entry from Analysis of High Enthalpy Wind Tunnel Tests of Spacecraft and Equipment
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Beck, Jamesjames.beck (at) belstead.comNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Holbrough, Ianian.holbrough (at) belstead.comNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Schleutker, ThornThorn.Schleutker (at) dlr.dehttps://orcid.org/0000-0002-1833-2850NICHT SPEZIFIZIERT
Gülhan, AliAli.Guelhan (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:Oktober 2018
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:veröffentlicht
Stichwörter:ReDSHIFT, aerothermodynamics, aerothermal testing, design for demise
Veranstaltungstitel:69th International Astronautical Congress
Veranstaltungsort:Bremen, Deutschland
Veranstaltungsart:internationale Konferenz
Veranstaltungsbeginn:1 Oktober 2018
Veranstaltungsende:5 Oktober 2018
Veranstalter :International Astronautical Federation
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Technik für Raumfahrtsysteme
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R SY - Technik für Raumfahrtsysteme
DLR - Teilgebiet (Projekt, Vorhaben):R - Projekt Space Debris (alt)
Standort: Köln-Porz
Institute & Einrichtungen:Institut für Aerodynamik und Strömungstechnik > Über- und Hyperschalltechnologien, KP
Hinterlegt von: Schleutker, Thorn
Hinterlegt am:17 Dez 2018 13:39
Letzte Änderung:24 Apr 2024 20:29

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