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Influence of the Combustion Chamber Geometry on the Performance of a Gel Propulsion System

Kröger, P. and Kirchberger, Christoph and Ciezki, H. (2016) Influence of the Combustion Chamber Geometry on the Performance of a Gel Propulsion System. Space Propulsion 2016, 02.-06. Mai 2016, Rom, Italien.

Full text not available from this repository.

Abstract

Gelled fluids are homogeneous mixtures of a liquid and a gelling agent and behave like a solid at rest but can be liquefied if a sufficiently high shear stress is applied. Over the past years a growing interest in gelled propellants for rocket and ramjet propulsion applications is observable worldwide because of safety and performance benefits. Due to the non-Newtonian flow behavior of their propel-lant, gel rocket motors combine the advantages of liquid engines e.g. throttling and restart capabilities with and simple handling and storage characteris-tics typical for solid motors. In Germany, within the German Gel Propulsion Technology Program (GGTP), which was started in 2001, necessary technologies to build a green gel propellant rocket engine are developed. Using the latest develop-ment of a gelled monopropellant, investigations on the performance, combustion pressure and the required combustor size thus residence time have been carried out. Capacitively cooled stainless steel combustion chambers with an inner diameter of 20.6 mm and a variable length of 80 mm up to 400 mm have been used. In combination with different nozzles featur-ing a throat diameter of either 5 mm or 6 mm a characteristic length L* (chamber volume to throat area ratio, Vc/At) between 1 m and 7 m could be realized. During tests, the mass flow rate has been varied between 0.058 kg/s and 0.124 kg/s resulting in a combustion pressure of up to 9 MPa. The re-sults obtained comprise the combustion perfor-mance (characteristic velocity, c*) as well as the operational envelope for a self-sustaining combus-tion for the current gel propellant and injector type. The experimental data serves as reference for future test and flight combustion chambers and as base for the development of design and scaling rules for gel rocket motors.

Item URL in elib:https://elib.dlr.de/107919/
Document Type:Conference or Workshop Item (Speech)
Title:Influence of the Combustion Chamber Geometry on the Performance of a Gel Propulsion System
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Kröger, P.peter.kroeger (at) dlr.deUNSPECIFIED
Kirchberger, ChristophChristoph.Kirchberger (at) dlr.dehttps://orcid.org/0000-0002-7574-2581
Ciezki, H.helmut.ciezki (at) dlr.deUNSPECIFIED
Date:6 May 2016
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:No
In ISI Web of Science:No
Status:Published
Keywords:Gel Propulsion, Performance, characteristic length
Event Title:Space Propulsion 2016
Event Location:Rom, Italien
Event Type:international Conference
Event Dates:02.-06. Mai 2016
Organizer:3AF
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:fixed-wing aircraft
DLR - Research area:Aeronautics
DLR - Program:L AR - Aircraft Research
DLR - Research theme (Project):L - Military Technologies
Location: Lampoldshausen
Institutes and Institutions:Institute of Space Propulsion > Propellants
Deposited By: Schmidt, Melanie
Deposited On:17 Nov 2016 08:02
Last Modified:01 Dec 2018 19:52

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