FULL PROPELLANT MULTI-STAGE COMBUSTION CYCLE LIQUID ROCKET ENGINE SYSTEM USING LIQUID METHANE AND LIQUID OXYGEN AS PROPELLANT

摘要

The present invention relates to a full propellant multi-stage combustion cycle liquid rocket engine system using liquid methane and liquid oxygen as propellant and, more specifically, relates to a full propellant multi-stage combustion cycle liquid rocket engine system using liquid methane and liquid oxygen as propellant, wherein after generating gaseous oxidizing agent excess gas and fuel excess gas through combustion reaction of a liquefied liquid oxidizing agent and liquid fuel which is methane, thrust is generated by reaction of the oxidizing agent excess gas and the fuel excess gas. Thus, combustion stability is excellent, and an expensive injector needs not to be provided as liquid within a main combustion chamber needs not to be atomized. Moreover, an oxidizing agent pump and a fuel pump to pressurize a liquefied liquid oxidizing agent and liquid fuel are individually formed to be operated to improve efficiency of an engine system.;COPYRIGHT KIPO 2016