摘要
文中根据微型火箭发动机的实际工作状态,建立了一种传热模型,以此为依据计算了发动机工作时的瞬态温度场。比较采用铜、铁和铝这三种外壳材料时系统的温度分布,并分析了对药柱燃烧稳定性的影响,这些结果对设计时选择材料有重要参考意义。
In this paper,a simplified heat transfer model is established according to practical working condition of microrocket. Transient distribution of temperature is simulated with this model. Choosing copper . iron and aluminium as shell material ,and transient temperature distribution is simulated respectively. The result is useful for selecting shell material.
出处
《弹箭与制导学报》
CSCD
北大核心
2006年第SA期1166-1167,1171,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
微型火箭发动机
燃烧室
传热
数值模拟
micro-rocket
combustion chamber
heat transfer
numerical simulation
