液氧/煤油补燃循环发动机起动过程研究  

Study on start-up of the staged combustion LOX/kerosene rocket engine

作　　者：杨明磊 张黎辉[2] 

机构地区：[1]上海空间推进研究所,上海200233 [2]北京航空航天大学宇航学院,北京100083

出　　处：《火箭推进》2009年第1期21-26,共6页Journal of Rocket Propulsion

摘　　要：液体火箭发动机起动过程是发动机研制过程中的难点和关键技术之一。针对某液氧/煤油补燃循环发动机,进行了起动过程研究。建立了发动机各组件的动态数学模型,并进行了适当简化,计算得到了起动过程发动机性能参数随时间变化的仿真曲线。计算结果与试车数据基本相符,初步验证了所建立的仿真模型及采用的仿真方法的正确性。还分析了部分干扰因素对发动机起动过程的影响。The start-up process is a crucial and tough part in the development of the liquid propellant rocket engine. The dynamic characteristics of the startup process of LOX/kerosene staged combustion cycle engine were studied. According to the main components of the liquid oxygen/ kerosene staged combustion cycle engine, mathematic models depicting propulsion system dynamic process were established and ameliorated. The result curves affecting the performance parameters vs time were presented. Some rules relating to start-up were acquired, on the basis of which the influences of interference factors on the process were analyzed. Furthermore, the correctness and reliability of both established models and adopted methods were preliminarily validated through comparisons of computing results and testing data.

关 键 词：液体火箭发动机 动态特性 起动过程 数学模型 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]