Abstract
This paper discusses propulsion requirements for rocket-powered single stage to orbit (SSTO) vehicles and defines a dual mixture ratio Hi/Oi staged combustion engine concept with characteristics matched to those requirements. The objective of this study was to configure an engine within the limits of current technology that when combined with a vehicle based on the material advances of the National Aerospace Plane program could provide an effective SSTO system. This engine uses high mixture ratio to provide high bulk density propellant usage and high thrust for the booster mode and transitions to low mixture ratio for high specific impulse during the upper stage mode. The internal operating characteristics of this engine are within the limits of current technology. Preliminary SSTO system studies indicate significant vehicle weight reductions relative to the Space Shuttle main engine (SSME) powered systems. This engine could be available before the end of this century.
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