Test of a turbo-pump fed miniature rocket engine

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dc.contributor.authorScharlemann, C.
dc.contributor.authorSchiebl, M.
dc.contributor.authorMarhold, K.
dc.contributor.authorTajmar, M.
dc.contributor.authorMiotti, P.
dc.contributor.authorGuraya, C.
dc.contributor.authorSeco, F.
dc.contributor.authorKappenstein, C.
dc.contributor.authorBatonneau, Y.
dc.contributor.authorBrahmi, R.
dc.contributor.authorLang, M.
dc.contributor.institutionEXTREMAT
dc.contributor.institutionTecnalia Research & Innovation
dc.date.accessioned2024-07-24T11:53:57Z
dc.date.available2024-07-24T11:53:57Z
dc.date.issued2006
dc.description.abstractThe increasing application of microsatellites (from 10 kg up to 100 kg) for a rising number of various missions requires the development of suitable propulsion systems. Microsatellites have special requirements for a propulsion system such as small mass, reduced volume, und very stringent electrical power constraints. Existing propulsion systems often can not satisfy these requirements. The present paper discusses the development and test of a bipropellant thruster complying with these requirements. The main development goal of this effort was the utilization of ethanol in combination with hydrogen peroxide (H2O2) as a non-toxic propellant combination. The Turbo-Pump Fed Miniature Rocket Engine (TPF-MRE) is a bipropellant thruster consisting of four subsystems: the propellant pumps, a decomposition chamber with a monolithic catalyst, a turbine, and the thruster itself. The turbine is driven by the decomposed hydrogen peroxide and magnetically coupled with a power generator. The power produced is then used to generate a pressure head in order to deliver the propellant into the combustion chamber. This system therefore constitutes a self-sustaining system and does not rely on the limited power supply of a micro-satellite. Previous test have shown that although the thruster can be operated with ethanol and oxygen, it was not possible to ignite the thruster when utilizing hydrogen peroxide in a 70% concentration by weight. A minor redesign of the thruster and the test facility was therefore initiated. This redesign together with the use of hydrogen peroxide in higher concentration was speculated to improve this behavior. However, even though the monolithic catalysts were able to decompose hydrogen peroxide in a concentration of 87.5% with nearly 100% efficiency, it was not possible to ignite or operate the thruster. Subsequently, a thorough investigation of the baseline design and operational conditions of the thruster was conduced. It was found that the failure of the thruster to ignite is due to a combination of reasons. The combustion chamber length is too short to facilitate sufficient mixing of the propellants, making an ignition impossible or very difficult at least. Additionally, the combustion chamber pressure which was chosen such that it accommodates the performance of commercially available mircopumps is considered too low. This further deteriorates the conditions for which an ignition is feasible.en
dc.description.statusPeer reviewed
dc.format.extent10
dc.identifier.citationScharlemann , C , Schiebl , M , Marhold , K , Tajmar , M , Miotti , P , Guraya , C , Seco , F , Kappenstein , C , Batonneau , Y , Brahmi , R & Lang , M 2006 , Test of a turbo-pump fed miniature rocket engine . in Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference . Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference , vol. 3 , American Institute of Aeronautics and Astronautics Inc. , pp. 2446-2455 , AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference , Sacramento, CA , United States , 9/07/06 . https://doi.org/10.2514/6.2006-4551
dc.identifier.citationconference
dc.identifier.doi10.2514/6.2006-4551
dc.identifier.isbn1563478188
dc.identifier.isbn9781563478185
dc.identifier.urihttps://hdl.handle.net/11556/2352
dc.identifier.urlhttp://www.scopus.com/inward/record.url?scp=34249281652&partnerID=8YFLogxK
dc.language.isoeng
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc.
dc.relation.ispartofCollection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
dc.relation.ispartofseriesCollection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference
dc.rightsinfo:eu-repo/semantics/restrictedAccess
dc.subject.keywordsSpace and Planetary Science
dc.subject.keywordsGeneral Energy
dc.subject.keywordsAerospace Engineering
dc.subject.keywordsControl and Systems Engineering
dc.subject.keywordsElectrical and Electronic Engineering
dc.subject.keywordsMechanical Engineering
dc.titleTest of a turbo-pump fed miniature rocket engineen
dc.typeconference output
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