基于筒式保护结构的导弹出水分离过程研究  

Investigation on Water Surfacing Process Separation of Submarine Missile-in-container

作　　者：李晶[1] 李吉[1] 陆宏志[1] 

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术》2016年第1期13-16,共4页Missiles and Space Vehicles

摘　　要：在出水过程中,由飞行介质改变带来的载荷冲击及海面波浪等不确定因素造成的复杂水动力环境,极大地增加了导弹与保护筒的分离风险。从多刚体动力学角度出发,对复杂水动力环境下的两刚体相对运动过程进行数值仿真,通过试验数据的对比修正,最终获得比较成熟的出水分离仿真方法。试验与仿真方法相结合研究了导弹出水过程中角速度显著减小现象的形成机理,为出水分离姿态预估提供理论基础。Experimental and numerical investigations are conducted for water surfacing process separation of submarine telescoping vehicle. It shows that the separation method presented is highly effective and engineering realizable by analyzing experiment data. The simulation focuses on the complicated hydrodynamic environment during water surfacing process, especially the effect of hydrodynamic change. The investigation is implemented to study the phenomenon that angular velocity decreases evidently. Finally, the reliable simulation method is obtained.

关 键 词：分离 套筒式水下航行器 试验 数值仿真 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]