液氧/煤油火箭发动机推力和混合比的非线性调整研究

NON LINEAR THROTTLING ANALYSIS OF THRUST AND MIXTURE RATIO FOR A LIQUID OXYGEN/KEROSENE ROCKET ENGINE

关键词:  液体推进剂火箭发动机  推力控制  发动机性能参数  计算方法

Key words:  Liquid propellant rocket engine  Thrust control  Motor performance parameter  Calculation method

摘要:

对液体火箭发动机推力和混合比的大范围非线性调整，提出了分级迭代直接求解高维非线性方程组的计算方法，并对液氧／煤油补燃循环火箭发动机的典型调整方案进行了计算分析，得到了考虑作为冷却剂的燃料温升、主涡轮入口燃气温度、主涡轮泵转速、发动机真空比冲以及燃气发生器喷注器压降和主燃烧室喷注器压降约束下发动机推力和混合比的最大可调域。

Abstract:

This paper focuses on the calculation of thrust and mixture ratio throttling for a liquid oxygen/kerosene propellant staged combustion cycle rocket engine.An effective method for the non linear throttling calculation was presented,and a useful code was developed.The maximum static throttleable region of thrust and mixture ratio under the restraint of static performance requirements,such as fuel temperature increment restriction,main turbine inlet gas temperature restriction and main trubopump rotational speed restriction,etc.,was determined.