IHI Corporation and IHI Aerospace have been continuing the research and development of LOX/Methane regenerative-cooled rocket engine since 2008. LOX/Methane regeneratively-cooled rocket engine is expected to bring many advantages to reality for future propulsion system, such as high performance, reusability, long storage and so on. The engine adopted Gas Generator Cycle with regeneratively-cooled chamber. In 2011 and 2012, the first hot firing tests of the engine were successfully conducted. In 2013, the engine components have been modified almost close to prototype model, and the engine system hot firing has been conducted. This paper describes the status of the 100kN thrust class LOX/Methane regeneratively-cooled rocket engine and the results of sea level hot firing tests held in 2013.
NomenclatureC* = Characteristic Exhaust Velocity ηC* = C* Efficiency FTP = Fuel Turbo Pump LNG = Liquefied Natural Gas MR = Mixture Ratio OTP = Oxidizer Turbo Pump OTV = Orbital Transfer Vehicle Pc = Combustion Pressure TDM = Total Design Method
:For the regenerative cooling cycle LNG rocket engines, improvement Nickel Electroforming technology and analysis are the major problem because of high reliability and low cost at the design and fabrication. This paper describes analysis methods, results and the successful Improved Nickel Electroforming of the stress and strain level at the Electron beam heat zone.
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