一、前言液体火箭发动机的特点是不靠外部能源而利用飞行器上推进剂诸组元的化学能建立推力。推进剂诸组元之间经过反应的物质(即燃烧产物)构成高速喷射物质。这样,火箭发动机的主要参数:喷射速度(比冲)就取决于单位质量推进剂所含的化学能。实际上,单位质量推进剂所含化学能的上限等于12.10~6焦耳/千克。具体说,双组元推进剂F_2/H_2在其燃烧产 I. Introduction Liquid rocket engines are characterized by the use of chemical energy of the propellant components of the aircraft to establish thrust without reliance on external energy sources. Reactants between the components of the propellant (ie, the products of combustion) constitute a high velocity spray. In this way, the main parameters of the rocket engine: jet speed (specific impulse) depends on the chemical energy per unit mass of propellant. In fact, the upper limit of the chemical energy per unit mass of propellant is equal to 12.10 to 6 Joules / kg. Specifically, the bipropellant F_2 / H_2 in its combustion