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
出处
《推进技术》
EI
CAS
CSCD
北大核心
1999年第2期9-12,共4页
Journal of Propulsion Technology
关键词
液体火箭发动机
稳态参数
高压补燃
推进剂
温升
Liquid propellant rocket engine,Steady state parameter,Mathematical model
