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Beschreibung
Currently used propellants for mono- and bipropellant systems such as hydrazine, NTO, and MMH are highly toxic and therefore expensive to be implemented. So-called green propellants have drawn increasing interest in times with decreasing budgets for space missions and development tasks. They are promising a significant reduction of the overall development and operational costs at similar or better performance. FOTEC GmbH has developed a one Newton bipropellant thruster system operating exclusively with green propellants under contract of the European Space Agency. One of the main properties to be investigated was the ignition capability and ignition conditions of such new propellants. For the investigated system hydrogen peroxide (87 wt%) was used as oxidizer. Kerosene was selected as fuel and their suitability was investigated for such a propulsion system. Their auto ignition capability (quasi-hypergolicity) in the presence of decomposed hydrogen peroxide (i.e. steam and oxygen) has been investigated experimentally. An analytical non adiabatic auto ignition model of the ignition conditions for a choked and non-choked flow in a micro rocket combustion chamber has been developed assuming a one-step single forward chemical reaction and with consideration of a residence time distribution of the propellants. Special focus is laid on the pressure-temperature auto ignition behavior.
Currently used propellants for mono- and bipropellant systems such as hydrazine, NTO, and MMH are highly toxic and therefore expensive to be implemented. So-called green propellants have drawn increasing interest in times with decreasing budgets for space missions and development tasks. They are promising a significant reduction of the overall development and operational costs at similar or better performance. FOTEC GmbH has developed a one Newton bipropellant thruster system operating exclusively with green propellants under contract of the European Space Agency. One of the main properties to be investigated was the ignition capability and ignition conditions of such new propellants. For the investigated system hydrogen peroxide (87 wt%) was used as oxidizer. Kerosene was selected as fuel and their suitability was investigated for such a propulsion system. Their auto ignition capability (quasi-hypergolicity) in the presence of decomposed hydrogen peroxide (i.e. steam and oxygen) has been investigated experimentally. An analytical non adiabatic auto ignition model of the ignition conditions for a choked and non-choked flow in a micro rocket combustion chamber has been developed assuming a one-step single forward chemical reaction and with consideration of a residence time distribution of the propellants. Special focus is laid on the pressure-temperature auto ignition behavior.
Über den Autor
Markus Schiebl holds a [...]. and [...]. in Physics from the Vienna University of Technology. He participated in several research projects funded by the European Space Agency or the European Commision. His major line of work focused on the development of a unique chemical propulsion system which operates with low toxicity propellants.
Details
Erscheinungsjahr: 2012
Fachbereich: Physikalische Chemie
Genre: Chemie, Mathematik, Medizin, Naturwissenschaften, Technik
Rubrik: Naturwissenschaften & Technik
Medium: Taschenbuch
Inhalt: 244 S.
ISBN-13: 9783639397147
ISBN-10: 3639397142
Sprache: Englisch
Einband: Kartoniert / Broschiert
Autor: Schiebl, Markus
Hersteller: AV Akademikerverlag
Verantwortliche Person für die EU: BoD - Books on Demand, In de Tarpen 42, D-22848 Norderstedt, info@bod.de
Maße: 220 x 150 x 16 mm
Von/Mit: Markus Schiebl
Erscheinungsdatum: 02.04.2012
Gewicht: 0,381 kg
Artikel-ID: 106531077

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