Turbo-pump fed miniature rocket engine

Simple item page
dc.contributor.authorScharlemann, C.
dc.contributor.authorMarhold, K.
dc.contributor.authorTajmar, M.
dc.contributor.authorMiotti, P.
dc.contributor.authorGuraya, C.
dc.contributor.authorSeco, F.
dc.contributor.authorSoldati, A.
dc.contributor.authorCampolo, M.
dc.contributor.authorPerennes, F.
dc.contributor.authorMarmiroli, B.
dc.contributor.authorBrahmi, R.
dc.contributor.authorKappenstein, C.
dc.contributor.authorLang, M.
dc.contributor.institutionEXTREMAT
dc.contributor.institutionTecnalia Research & Innovation
dc.date.accessioned2024-07-24T12:17:02Z
dc.date.available2024-07-24T12:17:02Z
dc.date.issued2005
dc.description.abstractThe increasing application of micro-satellites (from 10kg up to 100kg) for a rising number of various missions, demands the development of new propulsion systems. Microsatellites have special requirements for a propulsion system such as small mass, reduced volume, and very stringent electrical power constraints. Existing propulsion systems often can not satisfy these requirements. Recently the development of a bipropellant thruster complying with these requirements was initiated. 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 bipropellant thruster consists of four subcomponents: the propellant pumps, a decomposition chamber (catalyst), a turbine, and the thrusters itself. The turbine is driven by the decomposed hydrogen peroxide and coupled with a power generator. The produced power 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. All the components were individually tested and the results are presented here. The micro-gear pump successfully delivered the required mass flow rate with the necessary pressure. The turbine was tested with a cold air flow and has not yet reached the designed power output. A redesign of the turbine is ongoing. The decomposition chamber was tested and it was verified that the H 2O2 decomposes nearly to 100%. The thruster was successfully ignited and operated for more than 45 minutes. The measured thruster wall temperatures indicate a highly efficient combustion when only ethanol and oxygen are present in the combustion chamber. The injection of water however, tends to produce flame outs. A redesign of the propellant feed system is ongoing and expected to improve the thruster operation.en
dc.description.statusPeer reviewed
dc.identifier.citationScharlemann , C , Marhold , K , Tajmar , M , Miotti , P , Guraya , C , Seco , F , Soldati , A , Campolo , M , Perennes , F , Marmiroli , B , Brahmi , R , Kappenstein , C & Lang , M 2005 , ' Turbo-pump fed miniature rocket engine ' , Paper presented at 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit , Tucson, AZ , United States , 10/07/05 - 13/07/05 .
dc.identifier.citationconference
dc.identifier.urihttps://hdl.handle.net/11556/4721
dc.identifier.urlhttp://www.scopus.com/inward/record.url?scp=84888501452&partnerID=8YFLogxK
dc.language.isoeng
dc.rightsinfo:eu-repo/semantics/restrictedAccess
dc.subject.keywordsAerospace Engineering
dc.subject.keywordsControl and Systems Engineering
dc.subject.keywordsElectrical and Electronic Engineering
dc.subject.keywordsSDG 7 - Affordable and Clean Energy
dc.titleTurbo-pump fed miniature rocket engineen
dc.typeconference output
Files