本文介绍了全尺寸液体火箭发动机预燃起动过程的程序和模拟结果。实现这种发动机起动过程的主要条件是根据在模拟条件下所作出的结果分析和各种起动方案的数学模型而定的。当前高应力的液体火箭发动机,特别是分级燃烧循环发动机的起动和其他瞬态过程反映了燃烧室、燃气发生器、和燃料供应系统中互相关联的非稳态过程的复杂性。这种过程非常接近发动机功能的容限。为了使这些互相关联的非稳态过程正常地进行,需要定出多种参数 This paper introduces the procedure and simulation results of the pre-ignition start-up process of a full-size liquid propellant rocket engine. The main conditions for achieving this engine starting process are based on the analysis of the results under simulated conditions and the mathematical models of the various starting schemes. The current start-up and other transient processes of highly stressed liquid rocket engines, particularly staged combustion cycle engines, reflect the complexity of the interdependent non-steady-state processes in combustion chambers, gas generators, and fuel supply systems. This process is very close to the tolerance of engine function. In order for these inter-related non-steady-state processes to proceed normally, many parameters need to be set