| 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。 |
| 关键词: 固体火箭发动机 点火 射流 推进剂药柱 传热 |
| DOI： |
| 分类号:V435 |
| 基金项目:国家“八六三”高技术项目资助(2002AA765030)。 |
|
| Analysis for the heat transfer between solid propellant surface and heat flux of igniter with side holes |
|
ZHONG Tao, WANG Zhong-wei, ZHANG Wei-hua
|
|
Inst. of Aerospace and Material Engineering,National Univ. of Defence Technology, Changsha 410073, China
|
| Abstract: |
| 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. |
| Key words: Solid propellant rocket engine Ignition Jet flow Propellant grain Heat transfer |
