Abstract
Dual-expander rocket engines offer a trajectory adapted dual-mode operation during the ascent of a launcher, which may be of significant advantage for single-stage earth-to-orbit vehicles, when compared to conventional rocket engines with bell-type nozzles. This paper investigates a reusable single-stage earth-to-orbit vehicle with a constant payload capability of 16.5 Mg into low earth orbit, for the comparison of the dual-expander rocket engines with conventional rocket engines, using only hydrogen and oxygen as propellant combination in all engines.
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