Cycles for Earth-to-orbit propulsion

The reduction of Earth-to-orbit launch costs in conjunction with an increas e in launcher reliability and operational efficiency are the key demands on future space transportation systems. Results of various system analyses in dicate that these demands can be met with future single-stage-to-orbit (SST O) vehicles using advanced technologies for both structure and propulsion s ystems. This paper will provide a classification and description of all tur bopump feed liquid rocket engine cycles, followed by a combined vehicle/pro pulsion analysis of the design parameters for the propulsion systems and th eir associated thermodynamic cycles for the launch of future SSTO vehicles. Existing and projected rocket engine cycles capable of SSTO missions will be presented.