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基于计算流体动力学方法和均质多相流理论,采用汽化模型模拟燃气与冷却水的汽化过程,使用动态网格分层技术模拟导弹的运动,对燃气-蒸汽弹射气-液两相流场进行三维非定常数值研究.通过与固体火箭发动机尾焰喷水效应实验对比,验证了数值方法的有效性.研究了弹射过程中流场结构、二次流现象和变深度弹射载荷和内弹道变化规律.结果表明:导弹弹射过程中汽化现象发生在弯管壁面处,汽化后的燃气-蒸汽高温区随着发射筒体积的增加发生偏移;燃气-蒸汽在发射筒和弯管截面上存在隔离区和二次流动现象,并且形成不同结构形式的漩涡;弯管受到的最大冲击力出现在0.16s附近和30°~60°弯曲角范围内;弹射深度每增加10m,观测点压力增加0.25MPa,弹动时间延迟0.01s.
Based on computational fluid dynamics and homogeneous multiphase flow theory, a vaporization model was used to simulate the gasification process of gas and cooling water. Dynamic grid stratification was used to simulate the movement of the missile. The gas-vapor ejection gas-liquid two-phase flow field The numerical simulation is validated by comparing with the experimental results of three-dimensional unsteady numerical simulation of solid rocket motor.This paper studies the flow field structure, the secondary flow phenomenon, the variable depth ejection load and the internal ballistic change The results show that the vaporization of the missile occurs at the curved pipe wall, and the gas-steam high temperature area after vaporization shifts with the increase of the volume of the ejector. The gas-steam is isolated on the cross section of the ejector and the elbow Area and secondary flow phenomena, and formed a vortex of different structures; the maximum impact force on the elbow appeared in the range of about 0.16s and 30 ° ~ 60 ° bending angle; for each additional 10m of ejection depth, the pressure at the observation point increased by 0.25MPa , Playing time delay 0.01s.