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Liquid Rocket Engine Concept for SMILE Launcher

Müller, Ilja and Kuhn, Markus and Petkov, Ivaylo (2017) Liquid Rocket Engine Concept for SMILE Launcher. 21st AIAA International Space Planes and Hypersonics Technologies Conference, 6.-9. März 2017, Xiamen, China. DOI: 10.2514/6.2017-2349

Full text not available from this repository.

Official URL: https://doi.org/10.2514/6.2017-2349

Abstract

The development of the liquid propellant engine within the frame of the SMILE Project is described in the current paper. The analysis of a generic liquid propelled rocket launcher was performed and resulted in a description of the engines of each stage. The focus of this work is on the performance analysis of the first stage engine. As the liquid engine concept for the first stage aims for a cost efficient solution, three separate concepts are discussed. Thus, a conventional bell nozzle main combustion chamber and two aerospike concepts with multiple combustor chamber configurations geometries are compared and evaluated with respect to each other. The basis for the analytical comparison is a weight driven performance calculation. It is shown that 30 unitary combustion chambers in linear aerospike configuration can compete, regardless of their higher weight, against the other two concepts. An analytical calculation for the maximum change of velocity for each configuration is performed over a variable initial acceleration of the first stage. The analysis indicated only a minor impact on the change of velocity, the difference between best and worst performing configurations is less than 30 m/s, assuming an initial acceleration of 1.4 for the first stage. It can be further stated that a structure, which is fully dependent on the initial acceleration, results in minor differences of the change of velocity for the first stage.

Item URL in elib:https://elib.dlr.de/119471/
Document Type:Conference or Workshop Item (Speech)
Additional Information:AIAA 2017-2349
Title:Liquid Rocket Engine Concept for SMILE Launcher
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Müller, IljaIlja.Mueller (at) dlr.deUNSPECIFIED
Kuhn, MarkusMarkus.Kuhn (at) dlr.dehttps://orcid.org/0000-0002-0633-2327
Petkov, IvayloIvaylo.Petkov (at) dlr.deUNSPECIFIED
Date:9 May 2017
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
DOI :10.2514/6.2017-2349
Page Range:pp. 1-10
Status:Published
Keywords:ADDITIVE MANUFACTURING, ALM, INJECTOR, KEROLOX, LOX/KEROSENE, LIQUID PROPULSION, LIQUID ROCKET ENGINE, SMILE PROJECT, UNITARY ENGINE CONCEPT
Event Title:21st AIAA International Space Planes and Hypersonics Technologies Conference
Event Location:Xiamen, China
Event Type:international Conference
Event Dates:6.-9. März 2017
Organizer:AIAA
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 - Antriebsystemtechnik - Schubkammertechnologie, R - Wiederverwendbare Raumfahrtsysteme und Antriebstechnologie
Location: Stuttgart
Institutes and Institutions:Institute of Structures and Design > Space System Integration
Deposited By: Kuhn, Markus
Deposited On:14 Jun 2018 15:41
Last Modified:14 Jun 2018 15:41

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