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Overall Preliminary Design of the Thermal Protection System for a Long Range Hypersonic Rocket-Powered Passenger Vehicle (SpaceLiner)

Garbers, Nicole (2013) Overall Preliminary Design of the Thermal Protection System for a Long Range Hypersonic Rocket-Powered Passenger Vehicle (SpaceLiner). 7th European Workshop on Thermal Protection Systems and Hot Structures, 2013-04-08 - 2013-04-10, ESA-ESTEC, Noordwijk, The Netherlands. (nicht veröffentlicht)

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Kurzfassung

The long range hypersonic passenger transportation system SpaceLiner has been proposed by the Space Launcher Systems Analysis Group (SART) of the German Aerospace Center (DLR) and investigated in the frame of the European Commission project FAST20XX. The SpaceLiner is a two-stage fully reusable vehicle powered by rocket engines. It should carry about 50 passengers from Australia to Europe within 90 minutes. To accomplish a safe return to earth for all passengers in case of an emergency, the SpaceLiner passenger capsule can be separated from the rest of the vehicle and is then able to fly autonomously back to Earth. The focus of the paper is the sizing of both stages as well as the capsule’s passive thermal protection system. The SpaceLiner’s Thermal Protection System (TPS) has to withstand several different heat loads according to nominal flight and different abort cases. To be able to determine the heat loads for a full vehicle surface along different trajectories, fast engineering methods have to be used. The external heat flux was calculated by a fast code for preliminary flow analyses in hypersonic regime based on modified Newtonian surface inclination techniques and by using the Fay-Ridell equation close to the stagnation point and the Zoby-Moss-Sutton approach further downstream. The thicknesses of the different materials were optimized by using a 1D thermal conduction model. They depend heavily on the allowed temperature of the back-structure. According to the functional task and the chosen material, the structure is allowed to heat up to different maximum temperatures. Depending on the maximum temperature for the subdivided surface regions, different reusable materials were considered: CMC, TABI, AETB, AFRSI and FRSI. The TPS of the capsule, which is not part of the orbiter’s outer shell, is subject to high heat flux and has no need for re-usability. Therefore, an ablative thermal protection is preferred for stagnation and bottom areas with low system complexity, thus guaranteeing high safety. As an example, Avcoat was chosen. The paper shows the overall preliminary design of the TPS for a long range hypersonic rocket-powered passenger vehicle, comparing different materials and different back-structure temperatures.

elib-URL des Eintrags:https://elib.dlr.de/88040/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:Overall Preliminary Design of the Thermal Protection System for a Long Range Hypersonic Rocket-Powered Passenger Vehicle (SpaceLiner)
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Garbers, Nicolenicole.garbers (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:2013
Referierte Publikation:Ja
Open Access:Nein
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:nicht veröffentlicht
Stichwörter:SpaceLiner, Thermal Protection System
Veranstaltungstitel:7th European Workshop on Thermal Protection Systems and Hot Structures
Veranstaltungsort:ESA-ESTEC, Noordwijk, The Netherlands
Veranstaltungsart:Workshop
Veranstaltungsbeginn:8 April 2013
Veranstaltungsende:10 April 2013
Veranstalter :esa
HGF - Forschungsbereich:Luftfahrt, Raumfahrt und Verkehr
HGF - Programm:Raumfahrt
HGF - Programmthema:Raumtransport
DLR - Schwerpunkt:Raumfahrt
DLR - Forschungsgebiet:R RP - Raumtransport
DLR - Teilgebiet (Projekt, Vorhaben):R - Raumfahrzeugsysteme - Systemanalyse Raumtransport (alt)
Standort: Bremen
Institute & Einrichtungen:Institut für Raumfahrtsysteme > Systemanalyse Raumtransport
Hinterlegt von: Garbers, Nicole
Hinterlegt am:04 Feb 2014 12:34
Letzte Änderung:24 Apr 2024 19:54

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