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ENHANCED DEVELOPMENT OF A CATALYST CHAMBER FOR THE DECOMPOSITION OF UP TO 1.0 KG/S HYDROGEN PEROXIDE

Bozic, Ognjan and Porrmann, Dennis and Lancelle, Daniel and May, Stefan (2016) ENHANCED DEVELOPMENT OF A CATALYST CHAMBER FOR THE DECOMPOSITION OF UP TO 1.0 KG/S HYDROGEN PEROXIDE. CEAS Space Journal, 8 (2), pp. 77-88. Springer. DOI: 10.1007/s12567-015-0109-x ISBN x ISSN 1868-2502

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Official URL: http://link.springer.com/article/10.1007/s12567-015-0109-x/fulltext.html#copyrightInformation

Abstract

A new innovative hybrid rocket engine concept is developed within the AHRES program of the German Aerospace Center (DLR). This rocket engine based on hydroxyl-terminated polybutadiene (HTPB) with metallic additives as solid fuel and high test peroxide (HTP) as liquid oxidizer. Instead of a conventional ignition system, a catalyst chamber with a silver mesh catalyst is designed to decompose the HTP. The newly modified catalyst chamber is able to decompose up to 1.0 kg/s of 87.5 wt.% HTP. Used as a monopropellant thruster, this equals an average thrust of 1600 N. The catalyst chamber is designed using the self-developed software tool SHAKIRA. The applied kinetic law, which determines catalytic decomposition of HTP within the catalyst chamber, is given and commented. Several calculations are carried out to determine the appropriate geometry for complete decomposition with a minimum of catalyst material. A number of tests under steady-state conditions are carried out, using 87.5 wt.% HTP with different flow rates and a constant amount of catalyst material. To verify the decomposition, the temperature is measured and compared with the theoretical prediction. The experimental results show good agreement with the results generated by the design tool. The developed catalyst chamber provides a simple, reliable ignition system for hybrid rocket propulsion systems based on hydrogen peroxide as oxidizer. This system is capable for multiple re-ignition. The developed hardware and software can be used to design full scale monopropellant thrusters based on HTP and catalyst chambers for hybrid rocket engines.

Item URL in elib:https://elib.dlr.de/100294/
Document Type:Article
Additional Information:This paper is based on a presentation at the 4th (International) Space Propulsion Conference, May 19–22, 2014, Cologne, Germany.
Title:ENHANCED DEVELOPMENT OF A CATALYST CHAMBER FOR THE DECOMPOSITION OF UP TO 1.0 KG/S HYDROGEN PEROXIDE
Authors:
AuthorsInstitution or Email of AuthorsAuthors ORCID iD
Bozic, Ognjanbozic.ognjan (at) dlr.deUNSPECIFIED
Porrmann, Dennisdennis.porrmann (at) dlr.deUNSPECIFIED
Lancelle, Danieldaniel.lancelle (at) dlr.deUNSPECIFIED
May, Stefanstefan.may (at) dlr.deUNSPECIFIED
Date:2016
Journal or Publication Title:CEAS Space Journal
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Volume:8
DOI :10.1007/s12567-015-0109-x
Page Range:pp. 77-88
Editors:
EditorsEmail
Kordulla, Wilhelmwilhelm.kordulla@esa.int
Publisher:Springer
Series Name:CEAS Space Journal
ISSN:1868-2502
ISBN:x
Status:Published
Keywords:Hydrogen Peroxide, Catalyst Chamber, Hybrid Rocket Engine, Monopropellant Thruster
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 - Vorhaben AHRES (old)
Location: Braunschweig
Institutes and Institutions:Institute of Aerodynamics and Flow Technology > Spacecraft
Deposited By: Bozic, Dr.-Ing. Ognjan
Deposited On:06 Jul 2016 16:33
Last Modified:08 Mar 2018 19:01

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