A LOX-hydrocarbon engine for the propulsion of a reusable launcher first stage was defined and commonality with the HM60 was analyzed. Engines presented are: LOX-CH4, LOX-C3H8, LOX-UDMH, and LOX-RP1. Engine performances and cooling analysis are summarized. Results suggest that the LOX-methane combination is the most promising.
Studies on Rocket Engines for Future European Launchers
1984
58 pages
Report
Keine Angabe
Englisch
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