摘要
为研究导弹发射过程中燃气射流对同心筒和弹体的热冲击和动力冲击效应,基于欧拉-拉格朗日方法,使用域动分层动网格方法,对同心筒发射过程含Al2O3颗粒的气-固两相流场进行了数值计算,得到了发射过程中流场的温度和压强分布情况,计算结果与试验数据的相对误差在允许范围内,表明文中所用计算模型是可靠的。发射过程中燃气射流对后盖的冲刷和烧蚀较为严重,燃气主要从内外筒之间排出。内外筒间距增大后,内筒中的温度先降低后增大,后盖处的压强随之逐渐降低。发动机喷管出口与后盖的距离增大后,内筒中的温度变化较小,后盖处的压强随之逐渐降低。
To study the thermo-impact and the dynamical impact effect of combustion gas jet on concentric canister and missile body during launching process,the gas-solid two phase jet flow field including Al2O3 particles was simulated based on the Euler-Lagrange method and the zone moving and dynamic meshes updating method.The flow structure and temperature and pressure distribution were obtained.The relative error of the simulation result and experimental data is in allowed range.The results show that the gas-solid two phase model is reliable.The erosion and ablation of the canister bottom is serious and the jet flow is mainly ejected through the interval between outer and inner canisters.When the interval between the inner and outer canisters increases,the temperature in the inner canister decreases firstly and then increases and the bottom pressure decreases.When the distance of the nozzle exit and the canister bottom increases,the temperature in the inner canister changes little and the bottom pressure decreases.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第2期140-145,共6页
Journal of Solid Rocket Technology
关键词
同心筒
燃气射流
冲击效应
离散颗粒模型
域动分层法
concentric canister
combustion gas jet flow
impact effect
discrete particle model
zone moving and dynamic laying methods
