Zobrazeno 1 - 5
of 5
pro vyhledávání: '"Grenard, Philippe"'
Autor:
Vingert, Lucien, Grenard, Philippe, Lévy, Frédéric, Nicole, Aurélie, Dorey, Luc-Henry, Benito, Miguel Martin
Publikováno v:
32nd ISTS & 9th NSAT Joint Symposium
32nd ISTS & 9th NSAT Joint Symposium, Jun 2019, FUKUI, Japan
32nd ISTS & 9th NSAT Joint Symposium, Jun 2019, FUKUI, Japan
International audience; A test series aimed at investigating wall temperatures and heat fluxes in a subscale rocket engine combustion chamber operated with oxygen and methane was achieved at the Mascotte test facility. A total of nearly one hundred a
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=dedup_wf_001::83c36ce2150bac7a32c4cbd529e45c57
https://hal.archives-ouvertes.fr/hal-02345107/file/DMPE19047.1571402949.pdf
https://hal.archives-ouvertes.fr/hal-02345107/file/DMPE19047.1571402949.pdf
Experimental investigation of heat transfer in a subscale liquid rocket engine at high mixture ratio
Autor:
Grenard, Philippe, Fdida, Nicola, Vingert, Lucien, Dorey, Luc-Henry, Selle, Laurent, Pichillou, Julien
Publikováno v:
Journal of Propulsion and Power
Journal of Propulsion and Power, American Institute of Aeronautics and Astronautics, 2019, 35 (3), pp.544-551. ⟨10.2514/1.B36928⟩
Journal of Propulsion and Power, American Institute of Aeronautics and Astronautics, 2019, 35 (3), pp.544-551. ⟨10.2514/1.B36928⟩
International audience; This work presents the experimental investigation of heat fluxes through the walls of a reduced-scale rocket motor using hydrogen and oxygen as propellants. The engine is water-cooled so that it can be run in steady state for
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=dedup_wf_001::dba64df9f563016bff672745baa1c131
https://oatao.univ-toulouse.fr/28062/
https://oatao.univ-toulouse.fr/28062/
Combustion experimental test at subscale is a key element for the knowledge improvement of the design of liquid rocket engine. Within the frame of a CNES ONERA common research program, the MASCOTTE test bench has been used to gather an important expe
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3356ff2134bb05fe165372b4740eaa0d
An engineering model (EM) is under development that describes the propagation of a rocket exhaust plume after the nozzle exit. The aim of this EM is to allow a fast analysis of the structure of the plume and the exhaust species within the plume. The
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=od______1640::fc087ebe51795a65e6f724e1de74c05a
https://elib.dlr.de/83242/
https://elib.dlr.de/83242/
Even though the technology of cryogenic rocket engines is well mastered today, and has been applied successfully in many launchers all over the world, research activities on the various elementary or coupled processes involved in these complex system
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::7ca002c116f5a57f72dff85404ce860d