液氧/煤油高压补燃火箭发动机非线性稳态模型——考虑推进剂温升与密度变化  

ADVANCED MODEL OF STATIC CHARACTERISTIC FOR LIQUID OXYGEN/KEROSENE PROPELLANT STAGED COMBUSTION ROCKET ENGINE

作　　者：刘红军[1] 

机构地区：[1]陕西动力机械设计研究所

出　　处：《推进技术》1999年第2期9-12,共4页Journal of Propulsion Technology

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。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

关 键 词：液体火箭发动机 稳态参数 高压补燃 推进剂 温升 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]