基于热化学轴对称烧蚀的仿真

基于烧蚀理论与计算机语言设计了固体火箭喷管烧蚀软件的主程序及系统框架.火箭喷管烧蚀是在高温高压冲刷氧化气流作用下发生的,利用极端环境下的热化学烧蚀模型,通过Fortran编程对喷管内热流场及烧蚀进行数值计算,并结合Matlab与VC＋＋自身的特点,采用混合编程技术实现火箭烧蚀软件的前后处理.由算例可知,该软件能够对喷管烧蚀进行仿真,并能够脱离编译环境在Windows平台上使用,使初始参数输入界面化,数值解图形化.

Simulation for Ablation of Axial Symmetry Based on Thermochemistry

The main program and the system frame of ablation software in a solid-propellant rocket nozzle are designed on the basis of both the ablation theory and computer languages. The ablation of solidpropellant rocket nozzle is caused by the oxidation airflow, which is subjected to high temperature and high pressure. Based on the chemistry ablation model under extreme environments, the heat flow field and the ablation in the nozzle are simulated by using Fortran program. And then combining with char- acters of both Matlab and VC ＋ ＋ , the pre-treatment and post-treatment of the software are realized by a hybrid programming method. As results indicate, the software may simulate an ablation of nozzle, which can ran under the Windows platform without building environment. Meanwhile, the input of initial parameters and the graphic display of the numerical solution are all easy to perform.