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THE AURORA SPACE LAUNCHER CONCEPT

Kopp, Alexander (2016) THE AURORA SPACE LAUNCHER CONCEPT. Deutsche Luft- und Raumfahrtkongress (DLRK) 2016, 2016-09-13 - 2016-09-15, Braunschweig, Deutschland.

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Offizielle URL: http://www.dlrk2016.dglr.de/nc/paper_download/index.html

Kurzfassung

Large-scale space transportation cost reductions will require completely new launch vehicle configurations. Various alternative launcher configurations have been investigated in the recent decades including hypersonic single stage or two stage to orbit vehicles. Unfortunately, these alternative concepts were frequently found to be technically infeasible or their economic viability perspectives were considered to be doubtful. However, technological advances can shift the results of earlier trade-offs, and vehicle concepts that so far were found to be uninteresting or even unfeasible can become attractive. Recently, with thin-ply composites a new material technology emerged that offers the potential for major structural weight reductions of launch vehicles. Also in other relevant technology areas improvements have been achieved. Therefore, it is reasonable to re-evaluate alternative launcher concepts and to assess whether with using thin-ply composites and the latest technologies in other areas, novel launcher configurations can be made feasible. Based on this idea, the Aurora space launcher study was initiated in late-2015/early-2016 with contributions from several European partners. Within the Aurora studies, several spaceplane-like vehicle configurations with different geometries, propulsion systems and mission profiles will be designed, investigated and evaluated with respect to their technical and economic feasibility. The first step of this study is a first order investigation of thin-ply composite mass saving potentials for selected configurations. This paper consists of two parts. The first part will discuss the study logic and the current status of the Aurora studies and introduces the first three vehicle configurations. In the second part the focus will be shifted to the thin-ply technology and its application on vehicle level. Corresponding results for the first two configurations will be presented and discussed. Although the analysis procedures are still simplified and the findings of preliminary nature, the results indicate that indeed large weight savings are possible when using thin-ply composites, whereas the actual mass saving strongly depends on the particular vehicle configuration, load environment and structural design. This opens very promising perspectives for the realization of advanced launcher configurations and encourages to further investigate alternative space transportation systems.

elib-URL des Eintrags:https://elib.dlr.de/107566/
Dokumentart:Konferenzbeitrag (Vortrag)
Titel:THE AURORA SPACE LAUNCHER CONCEPT
Autoren:
AutorenInstitution oder E-Mail-AdresseAutoren-ORCID-iDORCID Put Code
Kopp, AlexanderAlexander.Kopp (at) dlr.deNICHT SPEZIFIZIERTNICHT SPEZIFIZIERT
Datum:September 2016
Referierte Publikation:Nein
Open Access:Ja
Gold Open Access:Nein
In SCOPUS:Nein
In ISI Web of Science:Nein
Status:veröffentlicht
Stichwörter:thin-ply Composites, Aurora space launcher study, alternative launcher concepts,
Veranstaltungstitel:Deutsche Luft- und Raumfahrtkongress (DLRK) 2016
Veranstaltungsort:Braunschweig, Deutschland
Veranstaltungsart:nationale Konferenz
Veranstaltungsbeginn:13 September 2016
Veranstaltungsende:15 September 2016
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: Vormschlag, Nele Marei
Hinterlegt am:16 Nov 2016 12:12
Letzte Änderung:24 Apr 2024 20:12

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