Staged Combustion Cycle Rocket Engine Design Trade-Offs for Future Advanced Passenger Transport
2012
Staged combustion cycle rocket engines with a moderate nominal 16 MPa chamber pressure have been selected as the baseline propulsion system for the visionary intercontinental passenger transport SpaceLiner.
Several technical engine design trade-offs are run by numerical simulations and results are pre-sented including:
• Fuel rich vs. Full-flow cycle
• Useful operational domain in MR
• Regenerative cooling options of thrust chamber
The engine operational domain is evaluated on launcher system level. The applicability of current European experimental staged combustion technology development (e.g. SCORE-D) on the SpaceLiner propulsion development is assessed.
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