Abstract
Propulsion systems for an SSTO (single-stage-to-orbit) type of space vehicle to be used for space tourism have been studied. Bell nozzle engines and liquid hydrogen and liquid oxygen propellants were chosen for this study to meet the targets of life time, reliability and maintenance frequencies assumed to be required analogous to present-day airline operations. Conceptual design and system analysis were made in terms of engine arrangement in the vehicle and intact abort capability, and a system was conceptualized.
