关键词: 液体推进剂火箭发动机;自燃火箭推进剂;推进剂燃烧;燃烧稳定性;数值仿真

Abstract: A comprehensive model was developed for the analysis of MMH/NTO rocket engine combustion instability Fuel vaporization was identified as the combustion rate limiting process The mechanism for combustion instability was studied Axial acoustic resonator model was proposed and numerical treatment was developed Acoustic resonator characteristic frequency affecting the combustion stability was simulated numerically It was obtained on how axial slots affect combustion instability The frequency scope can be determined by the current method for the axial acoustic slots located at the outer edge of the injector Simulation results are agreeable to both the theoretical analysis and engine hot test data This is of great use to analyze and design liquid rocket engine

Key words: Liquid propellant rocket engine;Hypergolic rocket propellant;Propellant combustion;Combustion stability;Numerical simulation