导弹水下点火推力峰值问题的数值研究  

Numerical Research on Thrust Peak for Missile Launching Underwater

作　　者：张有为[1] 王晓宏[1] 

机构地区：[1]中国科学技术大学,合肥230026

出　　处：《应用力学学报》2007年第2期298-301,共4页Chinese Journal of Applied Mechanics

摘　　要：通过对燃烧室内燃气采用常微分控制方程,对喷管-燃气泡流场采用准一维模型,数值研究了导弹水下点火初期推力峰值与燃气泡初始体积、喷管尾盖打开压强、发射深度等参数的关系。对水流场采用势流理论并通过边界元方法求解,水流场和燃气泡流场由交界面上的压力连续和速度连续条件相互耦合;利用准一维气流场模型计算得到的结果表明导弹在水下点火后瞬间所受推力将急剧增大,与利用球形气泡模型得到的结果一致。计算结果还表明推力峰值随着燃气泡初始体积的增加迅速降低,随着喷管尾盖打开压强的增加而增大,随尾盖质量的增加而增大;在一定范围内发射深度的变化对推力峰值影响较小,计算结果可为工程设计部门提供参考。Adopting a quasi one-dimensional model for nozzle-bubble flow, the differential equations for influence of initial gas volume, bubble and mass of the cover and launching depth upon the thrust peak during missile launching underwater are researched numerically. The potential flow of water is solved with boundary element method, where nozzle-bubble flow and potential flow become coupled at the boundary due to the pressure-continuous and velocity-continuous conditions. The numerical results show that a violent thrust jump appears at ignition coinciding sphere-bubble model; and thrust peak increases with the decreasing initial gas bubble volume or increasing nozzle cover mass; and the launching depth slightly affects the thrust peak.

关 键 词：导弹 水下点火 气-水耦合 喷管 推力 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] V553.1