某巡航导弹助推器固体火箭发动机点火过程数值模拟

摘要由于固体火箭发动机结构简单、方便文护、可靠性高等优点，现代巡航导弹的助推器已大多采用固体火箭发动机。固体火箭发动机的点火过程对固体火箭发动机的性能及整个助推器工作十分重要，因此本文对某固体火箭助推器的点火过程进行了数值仿真，为某型巡航导弹助推器的研制提供理论与技术支持。27121
通过对点火物理过程的简化，建立了基于可压流动方程和固相点火理论的计算模型。为分析不同压力对点火药燃气在燃烧室内流动的影响，首先不考虑主装药的燃烧，模拟了点火药产生的燃气在燃烧室内的流动过程，得出了各个物理量在燃烧室内的分布；然后模拟了考虑主装药燃烧的点火过程，得到了燃烧室内压力的建立过程和各物理量的分布。数值仿真结果表明点火压力对燃烧室内燃气的流动、燃烧室内压力场的形成和压力的震荡有着较大影响，因此合理设计点火装置对助推固体火箭发动机至关重要。
毕业论文关键词巡航导弹固体火箭助推器点火过程数值模拟
Title Numerical study of ignition process in the solid rocket booster of a cruise missile
Abstract
Solid rocket motor has advantages of simple structure, convenient maintenance ,high reliability，etc.So it has been adapted in most of the modern cruise missile.The ignition process is of great importance to the performance of solid rocket motor and the booster , this paper simulated the ignition process of a cruise missile,it provided theory and technology support to the designation of the solid rocket booster.Through simplifying the physics process of ignition ,compressible flow equation and solid phase ignition theory based simulation model was established. To analyze the flow of powder gas in combustion chamber under different ignition pressure,firstly the process of combustion of propellant was neglected,then the distribution of physical quantities in combustion chamber was got. Secondly, the ignition process considering the combustion of propellant was simulated. The distribution of physical quantities in the combustion chamber especially the rise of pressure were shown.Results showed ignition pressure has great influence on the flow of powder gas ,establishment of pressure filed and the shock of pressure wave in combustion chamber. When the combustion of propellant was considered,the propellant was ignited in a shorter time. So suitable design of an ignition system is great important to the solid rocket booster.
Keywords cruise missile solid rocket booster ignition process numerical study
目次
1 绪论 1
1.1 研究背景及意义. 1
1.2 国内外研究现状. 1
1.3 本文研究内容及手段. 3
2 SRB点火机理及过程. 4
2.1 SRM的点火机理4
2.2 点火药燃烧产物沿着燃气通道传播并传递能量. 6
2.3 装药的局部点燃. 7
2.4 火焰在装药表面的传播. 8
2.5 燃烧室压力的形成. 9
2.6 本章小结. 10
3 SRB点火的数学物理模型11
3.1 SRB的物理模型.11
3.2 SRB点火过程控制方程.11
3.3 数值求解方法. 12
3.4 本章小结. 17
4 SRB燃气传播过程仿真分析. 18
4.1 点火药燃气流动仿真的初始条件和边界条件. 18
4.2 计算模型. 19
4.3 仿真结果. 21
4.4 仿真分析. 30
4.5 本章小结. 34
5 SRB点火过程仿真分析. 36
5.1 加质量流动源项的处理. 36
5.2 初始条件和边界条件. 36
5.3 仿真结果. 37
5.4 本章小结. 41
结论 42
致谢 43
参考文献 44
1 绪论
1.1 研究背景及意义
巡航导弹，又被称为飞航导弹，这种导弹通常以不太高的马赫数（一般为 1Ma左右）飞
行在大气层内。巡航导弹主要通过助推发动机实现助推加速，使其达到一定的高度和速度后某巡航导弹助推器固体火箭发动机点火过程数值模拟:http://www.751com.cn/jixie/lunwen_21522.html