导弹垂直发射出筒过程中通气空泡流研究  

An investigation of ventilated cavitating flow in vertical launching of a missile

作　　者：刘筠乔[1] 鲁传敬[1] 李杰[1] 曹嘉怡[1] 

机构地区：[1]上海交通大学船舶海洋与建筑工程学院,上海200240

出　　处：《水动力学研究与进展（A辑）》2007年第5期549-554,共6页Chinese Journal of Hydrodynamics

摘　　要：将通气空泡技术应用于导弹水下垂直发射出筒过程,通气空泡是高速航行体获得稳定空泡的一种重要技术。采用基于Mixture多相流模型的有限体积法求解RANS方程,结合动网格技术,对水下垂直发射导弹出筒过程的轴对称流场进行了数值模拟,研究导弹的流体动力特性和通气空泡的演化。结果表明通气空泡可减小导弹出筒过程中的阻力和改善导弹的流体动力载荷。The ventilated cavitation, which is an important technique to obtain stable cavity for high-speed vehicle, is applied to missile＇s underwater vertical launching from an emitter. The finite volume method based on the multiphase model is adopted to solve RA.NS equations. The launching process is simulated combined with the dynamic meshes method. The instanta-neous axisymmetric flow field, the hydrodynamics characteristics of missile and the evolution of ventilated cavity are derived. The results show that the ventilated cavitation plays an important role in reducing the missile＇s drag and improving its hydrody-namic loads.

关 键 词：通气空泡 导弹 水下发射 动网格技术 

分 类 号：TJ760.13[兵器科学与技术—武器系统与运用工程]