侧壁开孔管式点火器点火热流与固体药柱表面间传热  

Analysis for the heat transfer between solid propellant surface and heat flux of igniter with side holes

作　　者：钟涛[1] 王中伟[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2005年第4期360-363,共4页Journal of Propulsion Technology

基　　金：国家"八六三"高技术项目资助(2002AA765030)。

摘　　要：分析了固体火箭发动机侧壁开孔长管式点火器点火热流与固体药柱表面间传热机理,根据轴对称边界层原理,借鉴平面间阵列圆孔射流传热模型,在考虑管式点火器与药柱表面同轴圆面间射流传热过程的基础上推导得到传热系数表达式,仿真研究表明模型合理,能对试验现象进行合理解释。The heat transfer mechanism between the solid propellant surface and heat flux of long igniter with side holes was analyzed. A array round nozzle jet heat transferring model between co-axis round surfaces was built. The heat transfer coefficient according to the theory of axisymmetric boundary layer was deduced. Simulation results validated the model and explained some phenomena of experiment.

关 键 词：固体火箭发动机 点火 射流 推进剂药柱 传热 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]