Mathematics – Logic
Scientific paper
Jan 2002
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2002iaf..confe.791p&link_type=abstract
IAF abstracts, 34th COSPAR Scientific Assembly, The Second World Space Congress, held 10-19 October, 2002 in Houston, TX, USA.,
Mathematics
Logic
Scientific paper
The need to increase the payload capacity of the current launchers drives rocket engine manufacturers to seek higher thrust level, specific impulse and thrust to weight ratio. A particularly efficient way to do this is the use of increased expansion ratio nozzle extensions for upper stage engines, and using thermostructural composite materials in order to allow higher temperature material limitations and to decrease mass. The latter is applicable to both upper and lower stage engines. Up to the mid 90s, the use of composite nozzles has been limited to solid rocket nozzles, but recent developments led to flight qualification on liquid rocket engines, on the RL10-B2 engine of the DELTA III launcher. This engine is equipped with a large extendible Carbon/Carbon Novoltex Sepcarb nozzle developed by Snecma Propulsion Solide under a contract from Pratt &Whitney San Jose. This paper describes the technological background of Snecma Propulsion Solide concerning the design and manufacturing of large size composite nozzles for liquid rocket engines. It provides an up-to-date status of the demonstrations already performed on different engines (HM7, RL10-B2 in particular) and details all the recent progress on technical and manufacturing performance. The manufacturing process has also been improved and simplified in order to allow the manufacturing of larger scale nozzles, at lower cost. Finally, this paper evidences that this technology is today mature and is ready to be implemented on existing or future liquid rocket engines being developed.
/Lacombe A.
Ferrey A.
Mercier André
Pichon T.
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