| 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 |
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| 引用本文： | 刘红军.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[J].推进技术,1999,20(2):9-12. |
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| 作者姓名： | 刘红军 |
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| 作者单位： | 陕西动力机械设计研究所,西安,710100 |
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| 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。
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| 关 键 词： | 液体火箭发动机 稳态参数 高压补燃 推进剂 温升 |
ADVANCED MODEL OF STATIC CHARACTERISTIC FOR LIQUID OXYGEN/KEROSENE PROPELLANT STAGED COMBUSTION ROCKET ENGINE |
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| Liu Hongjun.ADVANCED MODEL OF STATIC CHARACTERISTIC FOR LIQUID OXYGEN/KEROSENE PROPELLANT STAGED COMBUSTION ROCKET ENGINE[J].Journal of Propulsion Technology,1999,20(2):9-12. |
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| Authors: | Liu Hongjun |
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| 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 |
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| Keywords: | Liquid propellant rocket engine Steady state parameter Mathematical model |
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