Abstract: Using feeding system of a pump fed Liquid Propellant Staged Combustion Cycle Rocket Engine (LPSCCRE) as research object,adopt two dynamic mathematical models to evaluate the dynamic characteristic of engine, to analyze the adjusting system of engine The original data for studying the system stability and computing the rocket longitudinal stability in flight were obtained This method is fit for developing rocket engine in initial stages

Key words: Liquid propellant rocket engine;High pressure staged combustion rocket engine;Mathematical model;Frequency response

摘要： 以某大型泵压式补燃循环液体火箭发动机的输送系统为研究对象,采用两种动态数学模型:在低频区域为集中参数法,在中频区域为分布参数法,进行了发动机动态特性的评估、发动机调节系统的分析,为发动机系统稳定性研究以及火箭飞行中的纵向稳定性计算提供原始数据。

关键词: 液体推进剂火箭发动机;高压补燃火箭发动机;数学模型;频率响应