Scharlemann, 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.2024-07-242024-07-242005Scharlemann , 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 .conferencehttps://hdl.handle.net/11556/4721The 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.enginfo:eu-repo/semantics/restrictedAccessconference outputAerospace EngineeringControl and Systems EngineeringElectrical and Electronic EngineeringSDG 7 - Affordable and Clean Energyhttp://www.scopus.com/inward/record.url?scp=84888501452&partnerID=8YFLogxK