基于动网格层铺法的导弹垂直热发射数值仿真  

Numerical Simulation of Missile Vertical Thermal Launch Based on Moving Grid Layering Method

作　　者：徐学文 李恒 白玉 XU Xuewen;LI Heng;BAI Yu(Naval Aviation University,Yantai 264001;No.61035 Troops of PLA,Beijing 102205)

机构地区：[1]海军航空大学,烟台264001 [2]中国人民解放军61035部队,北京102205

出　　处：《舰船电子工程》2022年第9期98-101,共4页Ship Electronic Engineering

摘　　要：针对舰载导弹垂直热发射时高温助推燃气对弹体热冲击问题,文中采用流体动力学流场数值仿真方法,应用动网格层铺法,有效地避免了刚体运动而引起的网格畸变,仿真计算了导弹发射运动过程中高温燃气在弹体表面上的温度分布,仿真结果表明,导弹出筒历时0.4s,头部设备舱附近燃气温度最高,这需要更加关注此处的热防护。Aiming at the thermal impact of high-temperature booster gas on the missile body during vertical thermal launch of shipborne missile,the numerical simulation method of hydrodynamic flow field and the dynamic grid layer method are adopted in this paper to effectively avoid the grid distortion caused by rigid body movement. The temperature distribution of high-temperature gas on the missile surface during missile launch is simulated and calculated. The simulation results show that the missile takes 0.4s to exit the barrel,and the gas temperature near the head equipment cabin is the highest,more attention needs to be paid to the thermal protection here.

关 键 词：流场数值仿真 动网格 导弹发射 热冲击 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]