Abstract: An advanced mathematical model of system static characteristics for liquid oxygen/kerosene propellant staged combustion cycle rocket engine was considered,in which the variety of the temperature and densyit of the propellants was developed.The feasibility was demonstrated through mathematical simulations for the improved model

Key words: Liquid propellant rocket engine;Steady state parameter;Mathematical model

摘要： 针对液氧／煤油高压补燃循环液体火箭发动机，考虑了推进剂供应系统中的温度与密度变化，推导建立了改进的简化非线性稳态特性数学模型。并通过数值模拟分析验证了该改进的非线性稳态模型可行性。

关键词: 液体推进剂火箭发动机;稳态参数;数学模型