Browsing by Author "Miotti, P."

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    Bi-propellant micro-rocket engine
    (2004) Miotti, P.; Tajmar, M.; Guraya, C.; Perennes, F.; Marmiroli, B.; Soldati, A.; Campolo, M.; Kappenstein, C.; Eloirdi, R.; Lang, M.; EXTREMAT
    Micro-satellites (from 10kg up to 100kg) have mass, volume, and electrical power constraints due to their low dimensions. These limitations lead to the lack in currently available active orbit control systems in micro-satellites. Therefore, a micro-propulsion system with a high thrust to mass ratio is required to increase the potential functionality of small satellites. Mechatronic is presently working on a liquid bipropellant micro-rocket engine under contract with ESA (Contract No.16914/NL/Sfe - Microturbomachinery Based Bipropellant System Using MNT). The advances in Mechatronic's project are to realise a micro-rocket engine with propellents pressurised by micro-pumps. The energy for driving the pumps would be extracted from a micro-turbine. Cooling channels around the nozzle would be also used in order to maintain the wall material below its maximum operating temperature. A mass budget comparison with more traditional pressure-fed micro-rockets shows a real benefit from this system in terms of mass reduction. In the paper, an overview of the project status in Mechatronic is presented.
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    Bi-propellant micro-rocket engine
    (2004) Miotti, P.; Tajmar, M.; Guraya, C.; Perennes, F.; Marmiroli, B.; Soldati, A.; Campolo, M.; Kappenstein, C.; Brahmi, R.; Lang, M.; EXTREMAT
    Micro-satellites (from 10 kg up to 100 kg) have mass, volume, and electrical power constraints due to their low dimensions. These limitations lead to the lack in currently available active orbit control systems in micro-satellites. Therefore, a micro-propulsion system with a high thrust to mass ratio is required to increase the potential functionality of small satellites. Mechatronic is presently working on a liquid bipropellant micro-rocket engine under contract with ESA (Contract No.l6914/NL/Sfe - Microturbomachinery Based Bipropellant System Using MNT). The advances in Mechatronic's project are to realise a micro-rocket engine with propellants pressurised by micro-pumps. The energy for driving the pumps would be extracted from a micro-turbine. Cooling channels around the nozzle would be also used in order to maintain the wall material below its maximum operating temperature. A mass budget comparison with more traditional pressure-fed micro-rockets shows a real benefit from this system in terms of mass reduction. In the paper, an overview of the project status in Mechatronic is presented.
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    Test of a turbo-pump fed miniature rocket engine
    (American Institute of Aeronautics and Astronautics Inc., 2006) Scharlemann, C.; Schiebl, M.; Marhold, K.; Tajmar, M.; Miotti, P.; Guraya, C.; Seco, F.; Kappenstein, C.; Batonneau, Y.; Brahmi, R.; Lang, M.; EXTREMAT; Tecnalia Research & Innovation
    The 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.
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    Turbo pump FED micro-rocket engine
    (2004) Miotti, P.; Tajmar, M.; Seco, F.; Guraya, C.; Perennes, F.; Soldati, A.; Lang, M.; Tecnalia Research & Innovation; EXTREMAT
    Micro-satellites (from 10kg up to 100kg) have mass, volume, and electrical power constraints due to their low dimensions. These limitations lead to the lack in currently available active orbit control systems in micro-satellites. Therefore, a micro-propulsion system with a high thrust to mass ratio is required to increase the potential functionality of small satellites. Mechatronic is presently working on a liquid bipropellant micro-rocket engine under contract with ESA (Contract No.16914/NL/Sfe - Micro-turbo-machinery Based Bipropellant System Using MNT). The advances in Mechatronic's project are to realise a micro-rocket engine with propellants pressurised by micro-pumps. The energy for driving the pumps would be extracted from a micro-turbine. Cooling channels around the nozzle would be also used in order to maintain the wall material below its maximum operating temperature. A mass budget comparison with more traditional pressure-fed micro-rockets shows a real benefit from this system in terms of mass reduction. In the paper, an overview of the project status in Mechatronic is presented.
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    Turbo-pump fed miniature rocket engine
    (2005) 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.; EXTREMAT; Tecnalia Research & Innovation
    The 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.