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摘要长期以来，研究者希望设计出一种具有高速度、高比冲、简单结构和低成本的导弹动力装置。固体火箭冲压发动机因其优越的性能，已成为超声速导弹动力装置发展的主要方向之一。本文从固体火箭冲压发动机的工作特性入手，初步设计一种固体火箭冲压发动机并进行内流场的仿真工作。69429
首先进行热力计算，研究不同变量下发动机性能的变化规律，选取合适的空燃比范围，确定补燃室压强。结合理论公式和热力计算结果，设计固体火箭冲压发动机燃气发生室、进气道、补燃室及喷管的结构，初步计算发动机性能参数。使用FLUENT仿真软件进行发动机内流场的仿真工作，通过改变空燃比，比较多种工况下发动机温度、压强、马赫数及燃气组分的变化，并通过分析整理出相关结论。
关键词 固体火箭冲压发动机 热力计算 结构设计 内流场仿真
毕业设计说明书外文摘要
Title Design of 300mm Solid Rocket Ramjet
Abstract
For a long time, researchers hope to design a missile power device which has high speed, high specific impulse, simple structure and low cost. Solid rocket ramjet has become one trend of supersonic missile power device development because of its superior performance. This paper starts with the operation performance of solid rocket ramjet, preliminary designs a kind of solid rocket ramjet and conducts the simulation of internal flow field.
The first part of paper is the thermodynamic calculation, researching the change rules of ramjet performance under different variables, selecting the appropriate range of air-fuel ratio, confirming the pressure in afterburning chamber. The second part is the design of the structure of gas generating chamber, inlets, afterburning chamber and nozzle and doing initial calculation of ramjet performance. The third part is the simulation of internal flow field of ramjet by FLUENT. Change the air-fuel ratio to compare the temperature, pressure, Mach number in ramjet under different working conditions and draw relevant conclusions by figures.
Keywords solid rocket ramjet thermodynamic calculation structure design
simulation of internal flow field
目 录
1 绪论 1
1.1 研究工作的背景与意义 1
1.2 固体火箭冲压发动机国内外研究进展 2
1.3 固体火箭冲压发动机研制的关键技术[] 5
1.4 本文主要研究内容 6
2 固体火箭冲压发动机热力计算 7
2.1 CEA软件介绍 7
2.2 数学模型 9
2.2.1 基本方程 9
2.2.2 参数定义 9
2.2.3 燃烧产物求解 9
2.2.5 性能参数 13
2.3 理论性能分析 14
3 固体火箭冲压发动机初步设计及性能计算 19
3.1 固体火箭冲压发动机结构模型 19
3.2 固体火箭冲压发动机初步设计