Haidn, O. and Habiballah, M. (2003) Research on High Pressure Cryogenic Combustion. Aerospace Science Technology, 7 (6), pp. 473-491.
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Due to their high specific impulse, Oxygen/Hydrogen systems are often used to increase launcher performance and will probably continue to be preferred option for the next decades. In order to get insight into complex processes involved in the combustion of such propellants, research efforts have been conducted in both France and Germany including theoretical and experimental activities. This article deals with recent progress achived by research teams from both countries in high pressure Oxygen/Hydrogen (O2/H2) combustion systems. In France, the research program was conducted in the framework of the GDR goup including Snecma Moteurs-Rocket Engine Division, Centre National d'Etudes Spatiales (CNES), Centre National de la Recherche Scientifique (CNRS) and ONERA. In Germany, research was conducted in the framework of the national technology program TEKAN involving universities, DLR and Astrium. A close cooperation between teams was made possible through a Memorandum of Understanding (MoU) on research on high pressure cryogaenic combustion.
|Title:||Research on High Pressure Cryogenic Combustion|
|Journal or Publication Title:||Aerospace Science Technology|
|In ISI Web of Science:||Yes|
|Page Range:||pp. 473-491|
|Keywords:||Oxygen/Hydrogen; Combustion device; High pressure; Mascotte; M3; P8; Diagnostics; Modeling|
|HGF - Research field:||Aeronautics, Space and Transport (old)|
|HGF - Program:||Space (old)|
|HGF - Program Themes:||W RP - Raumtransport|
|DLR - Research area:||Space|
|DLR - Program:||W RP - Raumtransport|
|DLR - Research theme (Project):||E -- no assignement|
|Institutes and Institutions:||Institute of Space Propulsion|
|Deposited By:||Monika Lohmiller|
|Deposited On:||16 Sep 2005|
|Last Modified:||06 Jan 2010 14:04|
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