FUTURE PARTIALLY REUSABLE SPACE LAUNCH SYSTEM: MAIN PROPULSION SYSTEM DESIGN PHILOSOPHY

摘要

The report presents basic requirements to the layout, configuration and main specifications of the future-orientedspace transportation launch system featuring fly-back 1st stage boosters returned to the launch point. The reportprovides basic results of engineering work for the early stage of the system development.It also shows the role of the fly-back booster propulsion system to achieve required performance factors of thesystem. The report covers basic principles on how to develop and use a propulsion system featuring re-usable liquidpropellantrocket engines (multi-engine configuration of a propulsion system, presence of the on-board malfunctionmonitoring and shutdown system, utilization of new efficient liquid propellants, possibility to accomplish the task incase of a one-engine failure, maintainability and serviceability in-between flights with minimal resources etc.).The report provides experimental data obtained during fire tests of a liquid-propellant rocket engine (a prototype ofthe fly-back booster engine using the compressed natural gas/liquid oxygen propellant components. It formulatesthe direction of subsequent efforts to develop a re-usable transportation system.