Start-up Transient Simulation of 60t Class LOX/Methane Liquid Rocket Engine
- Paper number
IAC-13,C4,P,3.p1,x17697
- Author
Mr. WANG JUN, Beijing Aerospace Propulsion Institute, China
- Year
2013
- Abstract
Toward the object of furthering domestic liquid rocket engine preparing ability, a series of theoretical analysis and experimental investigation were performed, focusing on the start-up technology of 60 ton thrust reusable Oxygen/Methane liquid rocket engine. The mainly schematic and specification for the 60-ton-thrust reusable Oxygen/Methane liquid rocket engine were introduced. The transient behavior simulation system of rocket engine was established and the start-up characteristics were predicted. The test results show that the simulation results were well in line with the ground test data. However, the phenomenon of combustion chamber fuel-rich ignition impulsion and subcritical two-phase pressure oscillation in cooling jacket cannot be predicted perfectly. The proper simulation models should be added for modifying these deficiencies of current computational model.
- Abstract document
- Manuscript document
IAC-13,C4,P,3.p1,x17697.pdf (🔒 authorized access only).
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