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  • Demonstration of a 600kN class LOX/Methane Rocket Engine

    Paper number



    Prof. Nan Zhang, Beijing Aerospace Propulsion Institute, China


    Mr. Weibin Wang, Beijing Aerospace Propulsion Institute, China


    Mr. Jiguo Sun, Beijing Aerospace Propulsion Institute, China



    Liquid oxygen (LOX)/liquid methane (LCH4) propellants combination is considered as a leading candidate propulsion technology for the future space vehicles. A 600kN class LOX/LCH4 gas generator cycle prototype engine has been developed in China since 2006 to develop rocket engine reusability technology. A LOX/methane thrust chamber, with a shear coaxial injector and a methane regenerative-cooled chamber, was developed for the engine. A number of experiments at subscale level were conducted to study and evaluate methane/LOX gas-liquid and liquid-liquid injection combustion performance, combustion instability and methane cooling characteristics etc. A methane/oxygen turbine pump together with a LOX/methane gas generator was hot tested to validate their thermo-mechanical behavior. Thirty six hot runs were performed totally more than 538 seconds of hot testing time for the LOX/methane components and subsystem. Prototype engine at full power levels have been achieved successfully accumulating 4 tests and 67 seconds of operation. The engine showed excellent reliable steady state and transient behavior and high level performance. LOX/methane engine offers some advantages for future space transprotaion.
    Abstract document


    Manuscript document

    IAC-12,C4,1,3,x13537.pdf (🔒 authorized access only).

    To get the manuscript, please contact IAF Secretariat.