分级燃烧循环（staged combustion cycle）也叫高压补燃循环，是双元液体推进剂火箭发动机的动力循环的一种。一部分燃料在预燃室燃烧产生高温燃气推动发动机的涡轮和泵。随后废气和推进剂一起注入燃烧室。
提出了一种新的液体火箭发动机分级燃烧循环最高室压计算方法。
A new modular method for calculating the maximum combustion chamber pressure with stage combustion cycles is proposed in this paper.
针对分级燃烧循环液体火箭发动机启动过程的特点，提出了一种变结构控制系统。
A variable structure control system for the start up process of staged combustion cycle liquid rocket engine is presented in this paper.
本文给出了用该程序对采用液氧、丙烷作为推进剂的分级燃烧循环进行计算的结果。
The stage combustion cycle using the liquid oxygen and methane as propellant is calculated with the program, and the calculation results are also given.
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