脉冲式火箭发动机工作过程的数值分析+文献综述
关键词 脉冲火箭发动机 热流冲击 内流场 数值分析6565
毕业设计说明书（论文）外文摘要
Title Numerical analysis of the pulse rocket engine
Abstract
The solid propellant engine ignition procedure is a very short process,
which is especially important for pulse solid propellant engine steady
work. The problem of ignition impact comes outstanding because of small
structure size, short operating time and poor combustion stability in the
pulse solid propellant engine.
The structure of rocket engine was reasonably simplified for generating
reasonable numerical simulation grids. Suitable numerical models were
adopted to simulate the spreading process of the engine's ignition hotflow.
The combustion of propellant wasn't considered in this paper for the limit
of the time and author's knowledge. Numerical simulation of ignition
hotflow's spreading process was carried through using CFX. The
distribution of the pressure, velocity and temperature is introduced,
which changes over the time. Numerical methods were adopted to consider
structure' impact on the engine flow field.
Keywords Pulse rocket engine hotflow impact inner flow field
Numerical Analysis
目 次
1 引言1
1.1 概述1
1.2 国内外研究现状1
1.3 研究意义与背景4
1.4 本文主要工作4
2 点火热冲击流场的数值模拟方法5
2.1 基本方程及数学物理模型5
2.2 CFX 软件简介7
2.3 CFX 求解的设置示例8
3 发动机点火过程热流冲击流场分析10
3.1 点火器介绍10
3.2 研究对象的网格生成10
3.3 边界条件设置14
3.4 点火燃气热流冲击传播过程分析14
4 发动机特征结构对热冲击流场的影响2 4
4.1 点火具结构的影响24
4.2 改变推进剂形状对发动机流场影响的分析28
结论 32
致谢 33
参考文献34 1 引言
1.1 概述
随着对研究的深入，固体火箭发动机的性能越来越高，常规的优化设计及研究方
法已经不能满足固体火箭发动机优化设计的需求。为进一步提高固体火箭发动机的性
能，分析其具体工作过程已经成为一种迫切的需要。在自由装填发动机中，由点火药
生成的高温燃气从点火具破膜喷出并进入燃烧室，将会对药柱产生冲击。随着点火冲
击波在药柱表面的传播，药柱内、外孔受到高温高压气体的冲击而发生变形，甚至使
药柱产生裂纹，导致固体火箭发动机工作失效。脉冲式火箭发动机相比传统固体火箭
发动机，工作时间短，推进剂装药物理性能薄弱，工作过程中流场冲击对发动机性能
的影响更为明显，使得研究脉冲火箭发动机中点火燃气的热冲击流场更为必要。