液体火箭发动机系统瞬变过程模块化建模与仿真  

Modularization modeling and simulation for the transients of liquid propellant rocket engines

作　　者：刘昆[1] 张育林[1] 程谋森[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2003年第5期401-405,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金资助项目 (50 2 0 60 2 6)

摘　　要：为对发动机研制过程中多种试验方案进行仿真预示和对发动机进行结构优化,研究了液体火箭发动机系统瞬变过程模块化建模与仿真方法。提出了流体管道系统的管道 体积模块化分解方法,将组成发动机系统的典型元部件划分为21个模块,并建立了仿真数学模型。提出了一种描述模块元件及其连接关系的系统组态矩阵,以及模块的组合连接方法和组合系统的仿真计算方法。在此基础上,研制了分级燃烧循环液氧 液氢发动机系统瞬变过程的模块化建模与仿真软件(LRETMMSS),建立了某型号液氧 液氢补燃发动机的半系统试验的仿真计算模型,进行了仿真计算,计算结果与实验数据吻合。To prefigure the test processes of different test schemes of liquid rocket engines, and optimize their configuration, a new methodology of modularization modeling and simulation for the transients of liquid propellant rocket engines (LPRE) was studied. A pipe-volume module disassembly method for fluid line systems was presented. By using it, LPRE was disassembled into 21 typical components and their simulation mathematical models were developed. A configuration matrix for combination systems, which described their module components and relationships among them, was presented. The methods for assembling and connecting module components as well as for solving the modules combination systems were developed, respectively. Based on the research results, a modularization modeling and simulation software for the transients of LOX/LH, staged combustion cycle liquid rocket engines (LRETMMSS) were developed. The transient analysis of the start-up process of a model LH2/LOX rocket engine was modeled and solved by using LRETMMSS. The computed results agree well with test data.

关 键 词：液体推进剂火箭发动机 模块化设计 数学模型 仿真 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]