摘要
炭化层粒子的反弹系数是固体火箭发动机中两相流动计算的一个重要参数。文中设计并建立了测量粒子侵蚀炭化层反弹系数的实验系统,应用直径为1.5mm的粒子对炭化层进行了不同角度下的侵蚀反弹试验,测得各入射角下的法向及切向反弹系数。通过对实验数据应用准牛顿优化算法进行三次方多项式拟合得到法向反弹系数和切向反弹系数随侵蚀角的变化关系式,可为粒子对绝热材料的侵蚀力的计算及固体火箭发动机两相流动计算提供参考。
The rebound coefficient of particle impacting charring-layer is one of important parameters for simulation of two-phase flow in the solid rocket motor. The experimental system for measuring rebound coefficient of particle impacting charring-layer was designed and constituted. The experiment of particle with h 5mm diameter eroding charring-layer and rebounding was carried out at the different incident angle. The normal and tangential rebound coefficients were measured. The cube polynomial of normal and tangential rebound coefficient changing with incident angle were constituted by fitting the experimental data with the norm Newton optimizing algorithm, which could be served as reference for calculating the force of particle eroding heat-insulating material and for simulation of two phase flow in the solid rocket motor.
出处
《弹箭与制导学报》
CSCD
北大核心
2011年第1期119-122,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金(50976095)
武器装备预研基金资助
关键词
粒子侵蚀
三元乙丙
炭化层
反弹系数
particle erosion
ethylene propylene diene monomer
charring-layer
rebound coefficient
