摘要
随着固体推进技术的发展 ,越来越多的战术导弹采用了单室双推力固体火箭发动机 ,燃烧室和喷管的受热情况严重 ,必须对其进行深入研究 ,以保证发动机可靠工作。文中对此建立了集药柱几何计算、内流场、传热与烧蚀于一体的计算系统 ,并形成了成熟的软件 ,对一具体算例进行了绝热结构和烧蚀结构防护层的安全厚度设计 ,与工程实际应用厚度的比较表明 ,此系统用于工程中方便可靠。
With the development of the solid rocket technology, the single chamber,dual thrust solid rocket motor is often used in tactical missiles. To confirm the safety of the rocket motor,it is necessary to make a deep research on the heat transfer of the combustion chamber and the nozzle. An analysis system is presented in this paper,which includes computation of grain geometric shape,internal flow field,heat transfer and ablation. And a set of ripe software has been developed. An example of designing the safety thickness of the insulation structure and ablator is given. By comparig the calculation result with the practically thickness, the system is proved credible and convenient.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2002年第3期17-20,共4页
Journal of Solid Rocket Technology
