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Parametric Aero-Thermo-Mechanical Investigation of a Hypersonic Transport Glider

Kopp, Alexander (2018) Parametric Aero-Thermo-Mechanical Investigation of a Hypersonic Transport Glider. Dissertation, DLR, Institut für Raumfahrtsysteme.

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Abstract

Hypersonic airliner concepts with flight Mach numbers close to orbital velocities resemble space transportation systems in terms of configuration and technology. The serial production and routine operation of such systems for intercontinental high-speed transport could be an effective approach for significantly reducing the costs of space transportation systems. Based on these considerations, the rocket-propelled SpaceLiner concept was formulated at DLR, consisting of a booster- and a passenger-stage. Such concepts are characterized by high levels of complexity and strong interactions between the technical disciplines. The potential design space is large, the identification of suitable configurations therefore laborious, and the strong discipline interactions always require a consideration on complete system level. Based on this background, the objective of this thesis is to set-up an automated parametric design tool-chain for two-stage rocket-propelled hypersonic airliners. This tool-chain shall enable the definition, analysis, and comparative evaluation of such vehicle concepts on complete system level. The focus is on supporting trade-off studies in preliminary design phases that shall enable comparatively rapid identifications of suitable and efficient configurations. To accomplish this task, different software tools of various disciplines including geometry design, aerodynamics, aerothermodynamics, trajectory simulation, thermal protection design, and structural design are connected. Some of the applied tools including tools for parametric geometry generation, trajectory simulation, or structural design are developed within this thesis. The coupling of the programs is realized in a way that a fully automated preliminary system analysis can be executed by provision of a limited number of input parameters. By variations of the input parameters numerous different configurations can be designed and compared with each other in a relatively short time frame. After implementation of the tool-chain and integration of the programs the individual programs are validated. Subsequently, initial parameter studies are conducted on discipline level in order to reduce the design space. Based on the findings, eventually the tool-chain is applied for parametric complete vehicle preliminary system analyses. Here, a special focus is placed on vehicle geometry and structural design. The results of these parameter studies enable the identification of sensitivities and trends for the investigated vehicle category. Finally, an outlook on future works is formulated, especially concerning integration of improved analysis programs and the extension of the tool-chain for other vehicle categories.

Item URL in elib:https://elib.dlr.de/118774/
Document Type:Thesis (Dissertation)
Title:Parametric Aero-Thermo-Mechanical Investigation of a Hypersonic Transport Glider
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Kopp, AlexanderAlexander.Kopp (at) dlr.deUNSPECIFIED
Date:January 2018
Journal or Publication Title:DLR Forschungsbericht 2017-63
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Number of Pages:241
Status:Published
Keywords:Space Transportation, Hypersonic, reusability. passenger transport
Institution:DLR, Institut für Raumfahrtsysteme
Department:Systemanalyse Raumtransport
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transport
DLR - Research area:Raumfahrt
DLR - Program:R RP - Raumtransport
DLR - Research theme (Project):R - Raumfahrzeugsysteme - Systemanalyse Raumtransport
Location: Bremen
Institutes and Institutions:Institute of Space Systems > Space Launcher Systems Analysis
Deposited By: Vormschlag, Nele Marei
Deposited On:05 Mar 2018 15:35
Last Modified:05 Mar 2018 15:35

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