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First Wind Tunnel Data of CALLISTO - Reusable VTVL Launcher First Stage Demonstrator

Marwege, Ansgar and Riehmer, Johannes and Klevanski, Josef and Gülhan, Ali and Ecker, Tobias and Reimann, Bodo and Dumont, Etienne (2019) First Wind Tunnel Data of CALLISTO - Reusable VTVL Launcher First Stage Demonstrator. EUCASS 2019, 1. - 4. Juli, Madrid, Spanien.

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Abstract

In order to make access to space more affordable for both scientific and commercial activities the German Aerospace Center (DLR), the Japanese Aerospace Exploration Agency (JAXA), and the French National Centre for Space Studies (CNES) joined in a trilateral agreement to develop and demonstrate the technologies that will be needed for future reusable launch vehicles. In the joined project CALLISTO (Cooperative Action Leading to Launcher Innovation in Stage Toss back Operations) a demonstrator for a reusable vertical take-off, vertical landing rocket, acting as first stage, is developed and built. As long-term objective this project aims at paving the way to develop a rocket that can be reused, and the joint efforts of the three agencies will culminate in a demonstrator that will perform its first flights from the Kourou Space Center in French Guyana. The aerodynamic and aerothermal behaviour of the CALLISTO vehicle are investigated at DLR, including its challenging configurations with high angles of attack and subsonic up to supersonic flight regimes. To cross-check the aerodynamic data from CFD and for the enhancement of the understanding of the aerodynamic characteristics of the vehicle, experiments were performed in the Trisonic Wind Tunnel (TMK) at the DLR Department of Supersonic- and Hypersonic Flow Technologies in Cologne for Mach numbers between 0.5 and 2.5. The experiments considered the ascent and the backwards orientated decent configurations of the vehicle with folded and deployed control surfaces at several deflection angles. The angle of attack was continuously varied for all configurations. A comparison between the Aerodynamic Data Base (AEDB), generated previously using Euler and Navier-Stokes based CFD, and the experimental results showed good agreement and no significant deviations in the global coefficients were found. This paper describes the tested configurations and the experimental methods of the test campaign. An uncertainty analysis was performed for the experimental setup and the validity of the data was checked by comparison with other data from preliminary design analysis and CFD simulations. Follow-up investigations in CALLISTO project will evaluate the influence of the exhaust plume on the aerodynamics of the vehicle which is not covered by the present study.

Item URL in elib:https://elib.dlr.de/128629/
Document Type:Conference or Workshop Item (Speech)
Title:First Wind Tunnel Data of CALLISTO - Reusable VTVL Launcher First Stage Demonstrator
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Marwege, AnsgarAnsgar.Marwege (at) dlr.dehttps://orcid.org/0000-0002-3912-9114
Riehmer, JohannesJohannes.Riehmer (at) dlr.deUNSPECIFIED
Klevanski, JosefJosef.Klevanski (at) dlr.deUNSPECIFIED
Gülhan, AliAli.Guelhan (at) dlr.deUNSPECIFIED
Ecker, TobiasTobias.Ecker (at) dlr.dehttps://orcid.org/0000-0001-7134-1185
Reimann, BodoBodo.Reimann (at) dlr.deUNSPECIFIED
Dumont, EtienneEtienne.Dumont (at) dlr.dehttps://orcid.org/0000-0003-4618-0572
Date:July 2019
Refereed publication:No
Open Access:Yes
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Aerodynamics, Forces, Moments, Wind Tunnel Experiments, Reusable Launch Vehicle, Vertical Take-off Vertical Landing
Event Title:EUCASS 2019
Event Location:Madrid, Spanien
Event Type:international Conference
Event Dates:1. - 4. Juli
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: Köln-Porz
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Supersonoc and Hypersonic Technology
Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Institute for Aerodynamics and Flow Technology > Spacecraft, BS
Institute of Space Systems > Systems Engineering and Project Office
Deposited By: Marwege, Ansgar
Deposited On:07 Aug 2019 14:46
Last Modified:23 Sep 2019 08:56

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