Abstract
A computerized preliminary design system is used to evaluate potential main liquid-rocket propulsion systems for advanced technology winged single-state-to-orbit launch vehicles. Evaluated are tradeoffs between ascent flight trajectory performance and flight vehicle sizing driven by engine mass and propellant requirements. Numerous mission, flight, and vehicle-related requirements and constraints are satisfied in the design process. With the design system, five dual-mode propulsion system concepts are compared to a baseline hydrogen and oxygen system in terms of the changes in vehicle dry mass and gross mass.
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