A computerized preliminary design system is used to evaluate potential main liquid-rocket propulsion systems for advanced technology winged single-stage-to-orbit launch vehicles. Evaluated are trade-offs 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.
Optimization and evaluation of main liquid rocket propulsion systems for advanced earth-to-orbit shuttles
Joint Propulsion Conference ; 1978 ; Las Vegas, NV, US
1978-07-01
Conference paper
No indication
English