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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
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)。
关键词
固体火箭发动机
点火
射流
推进剂药柱
传热
Solid propellant rocket engine
Ignition
Jet flow
Propellant grain
Heat transfer