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

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.

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