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Unsteady Aerodynamics of the Retropropulsion Reentry Burn of Vertically Landing Launchers

Marwege, Ansgar and Gülhan, Ali (2023) Unsteady Aerodynamics of the Retropropulsion Reentry Burn of Vertically Landing Launchers. Journal of Spacecraft and Rockets. American Institute of Aeronautics and Astronautics (AIAA). doi: 10.2514/1.A35647. ISSN 0022-4650.

Full text not available from this repository.

Abstract

During the vertical descent and landing of a launcher first stage with the aid of retropropulsion, commonly two main propulsive deceleration maneuvers are performed: the reentry burn in high altitudes at hypersonic to supersonic speeds and the landing burn shortly before touchdown at transonic to subsonic speeds. In the frame of the EU-funded H2020 project Retro Propulsion Assisted Landing Technologies (RETALT), the unsteady aerodynamics of those retropropulsion phases were studied. This paper presents results of experiments performed in the Hypersonic Wind Tunnel Cologne on the hypersonic reentry burn. The exhaust plume was simulated with pressurized air. Proper orthogonal decomposition was performed on high-speed schlieren videos, and spectral analyses of the time histories of the resulting modes were compared to the frequency content found in high-frequency pressure measurements. Dominant frequencies were found in the proper orthogonal decomposition modes for one and for three active engines. In the pressure measurements, dominant frequencies could only be observed for three active engines. The normalized pressure fluctuations are in the range of 0.002–0.012. Additionally, a good scaling of the pressures on the base area and in the wake of the configuration with the total pressure downstream of the bow shock could be confirmed, in the sense that the ratio of the local surface pressure to the total pressure downstream of the bow shock match for varying freestream Mach numbers.

Item URL in elib:https://elib.dlr.de/200755/
Document Type:Article
Title:Unsteady Aerodynamics of the Retropropulsion Reentry Burn of Vertically Landing Launchers
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Marwege, AnsgarUNSPECIFIEDhttps://orcid.org/0000-0002-3912-9114UNSPECIFIED
Gülhan, AliUNSPECIFIEDhttps://orcid.org/0000-0001-7460-0576UNSPECIFIED
Date:24 August 2023
Journal or Publication Title:Journal of Spacecraft and Rockets
Refereed publication:Yes
Open Access:Yes
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:Yes
DOI:10.2514/1.A35647
Publisher:American Institute of Aeronautics and Astronautics (AIAA)
ISSN:0022-4650
Status:Published
Keywords:Aerodynamics, Aeronautics, Aerospace Sciences, Fluid Dynamics, Propulsion and Power, Shock Waves, Unsteady Aerodynamics, Vortex Dynamics, Wind Tunnels
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Space
HGF - Program Themes:Space Transportation
DLR - Research area:Raumfahrt
DLR - Program:R RP - Space Transportation
DLR - Research theme (Project):R - Reusable Space Systems and Propulsion Technology
Location: Köln-Porz
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Supersonic and Hypersonic Technology
Deposited By: Marwege, Ansgar
Deposited On:14 Dec 2023 09:20
Last Modified:14 Dec 2023 09:20

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