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Enhancement of Free Flight Force Measurement Technique for Scramjet Engine Shock Tunnel Testing

Hannemann, Klaus and Martinez Schramm, Jan and Karl, Sebastian and Laurence, Stuart Jon (2017) Enhancement of Free Flight Force Measurement Technique for Scramjet Engine Shock Tunnel Testing. In: 21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017. 21st AIAA International Space Planes and Hypersonic Systems and Technologie Conference, 2017-03-06 - 2017-03-09, Xiamen, China. doi: 10.2514/6.2017-2235.

Full text not available from this repository.

Official URL: https://www.aiaa.org/EventDetail.aspx?id=33740

Abstract

The free flight force measurement technique is a very attractive tool to determine forces and moments in particular in short duration ground based test facilities. With test times in the order of a few milliseconds, conventional force balances cannot be applied. The free flight technique has been applied in a number of shock tunnels utilizing models up to approximately 300 mm in length and looking at external aerodynamics. Test campaigns in the High Enthalpy Shock Tunnel Göttingen (HEG) of the German Aerospace Center (DLR) conducted in the framework of the EU co-funded LAPCAT II project demonstrated that this technique, in combination with optical tracking, can successfully be applied for thrust measurements of a complex fully integrated scramjet engine. In addition to the engine components intake, combustor and thrust nozzle, the hydrogen fueling system and gauge measurement infrastructure were integrated in the 1.5 m long model with a mass of 85 kg. The test campaigns in HEG together with vehicle aerodynamics predictions based on computational fluid dynamics demonstrated experimentally that the considered small scale flight experiment configuration is able to generate net thrust, i.e., has a positive aero propulsive balance. In the present article, the results of a new HEG test campaign utilizing an optimized optical set-up are presented. Motivated by uncertainty analyses results, the optical resolution and the camera frame rate were increased. It could be shown that by these modifications the uncertainty of the thrust increment measurements could be reduced by a factor of approximately 2. Further, the new results demonstrated the repeatability of the scramjet thrust measurement technique in HEG.

Item URL in elib:https://elib.dlr.de/118184/
Document Type:Conference or Workshop Item (Speech)
Additional Information:AIAA 2017-2235
Title:Enhancement of Free Flight Force Measurement Technique for Scramjet Engine Shock Tunnel Testing
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Hannemann, KlausUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Martinez Schramm, JanUNSPECIFIEDhttps://orcid.org/0000-0002-8891-6253UNSPECIFIED
Karl, SebastianUNSPECIFIEDhttps://orcid.org/0000-0002-5558-6673UNSPECIFIED
Laurence, Stuart JonDept. of Aerospace Engineering, University of MarylandUNSPECIFIEDUNSPECIFIED
Date:2017
Journal or Publication Title:21st AIAA International Space Planes and Hypersonics Technologies Conference, Hypersonics 2017
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
DOI:10.2514/6.2017-2235
Status:Published
Keywords:free flight force measurement technique, thrust measurement, shock tunnel, optical tracking, scramjet engine
Event Title:21st AIAA International Space Planes and Hypersonic Systems and Technologie Conference
Event Location:Xiamen, China
Event Type:international Conference
Event Start Date:6 March 2017
Event End Date:9 March 2017
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 - Raumfahrzeugsysteme - Anlagen u. Messtechnik (old)
Location: Göttingen
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Spacecraft, GO
Deposited By: Bachmann, Barbara
Deposited On:12 Jan 2018 14:03
Last Modified:24 Apr 2024 20:22

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