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Titel:

Design and Test of Nitrous Oxide Injectors for a Hybrid Rocket Engine

Autor(en): E. Gamper, R. Hink
Zusammenfassung: An injection system for the Helios hybrid rocket engine is designed by ExperimentalRaumfahrt-InteressenGemeinschaft e.V. (ERIG). Within three years German students design and launch their own hypersonic rockets with self-made rocket engines within Studentische Experimental-Raketen (STERN) program of German Aerospace Center (DLR). The quality and homogeneity of an atomized fluid and therefore the stability and efficiency of hybrid rocket engines are basically determined by the oxidizer injection system. The Helios hybrid rocket engine uses nitrous oxide as oxidizer. Evaporation and combustion of the atomized nitrous oxygen droplets need to be completed inside the combustion chamber, which is less than one meter long. The pressure drop over the injector protects the feed and tank system against backflow of the hot combustion gas. To respect this amount of requirements the most important equations and design rules of several injector designs are summarized shortly. Furthermore the design of the special test bench, which was built to validate the design of different injectors, is presented. An acrylic glass chamber was used for the experiments. Moreover the acrylic glass chamber provided a field of view into the injection of nitrous oxide, which was recorded by high-speed camera pictures. The quality and homogeneity of the injectors are rated directly by these pictures.
Veranstaltung: Deutscher Luft- und Raumfahrtkongress 2013, Stuttgart
Verlag, Ort: Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2013
Medientyp: Conference Paper
Sprache: englisch
Format: 21,0 x 29,7 cm, 6 Seiten
URN: urn:nbn:de:101:1-2013112216177
Stichworte zum Inhalt: Einspritzkopf/Injektor, Hybridraketentriebwerke
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Veröffentlicht am: 22.11.2013