HYDRA III Hybrid Rocket Engine - Flight Version Test Results
The flight version of the HYDRA III hybrid rocket engine was built by the ExperimentalRaumfahrt-InteressenGemeinschaft e.V. (ERIG) in cooperation with the Institute of Aerospace Systems of TU Braunschweig. The HYDRA III engine was improved to a thrust of about 1300 N for the supersonic rocket named...
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ftdlr:oai:elib.dlr.de:97794 2023-05-15T17:04:15+02:00 HYDRA III Hybrid Rocket Engine - Flight Version Test Results Hink, Rüdiger 2015 application/pdf http://elib.dlr.de/97794/ http://elib.dlr.de/97794/1/ERIG_DLRK_Testrun_Paper.pdf http://www.dlrk2015.dglr.de/ de ger DGLR http://elib.dlr.de/97794/1/ERIG_DLRK_Testrun_Paper.pdf Hink, Rüdiger (2015) HYDRA III Hybrid Rocket Engine - Flight Version Test Results. In: Deutscher Luft- und Raumfahrtkongress 2015. DGLR. Deutscher Luft- und Raumfahrtkongress 2015, 22.-24. Sept. 2015, Rostock, Deutschland. Raumfahrzeuge Konferenzbeitrag PeerReviewed 2015 ftdlr 2016-03-28T21:11:12Z The flight version of the HYDRA III hybrid rocket engine was built by the ExperimentalRaumfahrt-InteressenGemeinschaft e.V. (ERIG) in cooperation with the Institute of Aerospace Systems of TU Braunschweig. The HYDRA III engine was improved to a thrust of about 1300 N for the supersonic rocket named FAUST of the Studentische Experimental-Raketen program (STERN), which is initiated by the German Aerospace center (DLR). The launch of the FAUST rocket is planned to be at the end of this year at the Esrange Space Center in Kiruna (North Sweden). The aim of the STERN program is to motivate and educate students for aerospace sciences by developing a rocket. The ERIG advanced therefore the hybrid rocket engine HYDRA III, which bases on a liquid oxidizer and a solid fuel grain as propellants. Therefore, liquid nitrous oxide is used as oxidizer and hydroxyl-terminated polybutadiene (HTPB) with metal powder as solid fuel grain. For the flight version of this engine a carbon fiber reinforced plastic (CFRP) oxidizer vessel and the CFRP flight pressure vessel with helium were used. Also a new lightweight flight version valve segment was used to control the high amount of oxidizer mass flow into the combustion chamber. The latest test results of this flight engine from the horizontal test bench as well as the set-up of the vertical test bench are presented. Conference Object Kiruna North Sweden German Aerospace Center: elib - DLR electronic library Kiruna Esrange ENVELOPE(21.117,21.117,67.883,67.883) |
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German |
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Raumfahrzeuge |
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Raumfahrzeuge Hink, Rüdiger HYDRA III Hybrid Rocket Engine - Flight Version Test Results |
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Raumfahrzeuge |
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The flight version of the HYDRA III hybrid rocket engine was built by the ExperimentalRaumfahrt-InteressenGemeinschaft e.V. (ERIG) in cooperation with the Institute of Aerospace Systems of TU Braunschweig. The HYDRA III engine was improved to a thrust of about 1300 N for the supersonic rocket named FAUST of the Studentische Experimental-Raketen program (STERN), which is initiated by the German Aerospace center (DLR). The launch of the FAUST rocket is planned to be at the end of this year at the Esrange Space Center in Kiruna (North Sweden). The aim of the STERN program is to motivate and educate students for aerospace sciences by developing a rocket. The ERIG advanced therefore the hybrid rocket engine HYDRA III, which bases on a liquid oxidizer and a solid fuel grain as propellants. Therefore, liquid nitrous oxide is used as oxidizer and hydroxyl-terminated polybutadiene (HTPB) with metal powder as solid fuel grain. For the flight version of this engine a carbon fiber reinforced plastic (CFRP) oxidizer vessel and the CFRP flight pressure vessel with helium were used. Also a new lightweight flight version valve segment was used to control the high amount of oxidizer mass flow into the combustion chamber. The latest test results of this flight engine from the horizontal test bench as well as the set-up of the vertical test bench are presented. |
format |
Conference Object |
author |
Hink, Rüdiger |
author_facet |
Hink, Rüdiger |
author_sort |
Hink, Rüdiger |
title |
HYDRA III Hybrid Rocket Engine - Flight Version Test Results |
title_short |
HYDRA III Hybrid Rocket Engine - Flight Version Test Results |
title_full |
HYDRA III Hybrid Rocket Engine - Flight Version Test Results |
title_fullStr |
HYDRA III Hybrid Rocket Engine - Flight Version Test Results |
title_full_unstemmed |
HYDRA III Hybrid Rocket Engine - Flight Version Test Results |
title_sort |
hydra iii hybrid rocket engine - flight version test results |
publisher |
DGLR |
publishDate |
2015 |
url |
http://elib.dlr.de/97794/ http://elib.dlr.de/97794/1/ERIG_DLRK_Testrun_Paper.pdf http://www.dlrk2015.dglr.de/ |
long_lat |
ENVELOPE(21.117,21.117,67.883,67.883) |
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Kiruna Esrange |
geographic_facet |
Kiruna Esrange |
genre |
Kiruna North Sweden |
genre_facet |
Kiruna North Sweden |
op_relation |
http://elib.dlr.de/97794/1/ERIG_DLRK_Testrun_Paper.pdf Hink, Rüdiger (2015) HYDRA III Hybrid Rocket Engine - Flight Version Test Results. In: Deutscher Luft- und Raumfahrtkongress 2015. DGLR. Deutscher Luft- und Raumfahrtkongress 2015, 22.-24. Sept. 2015, Rostock, Deutschland. |
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1766058321135009792 |