导弹热分离环境下发动机壳体温度分布研究  

Numerical Simulation on the Temperature Distribution of Motor Cases under Thermal Seperation of Missile

作　　者：肖育民[1] 李江[1] 孙得川[1] 蔡体敏[1] 

机构地区：[1]西北工业大学航天工程学院

出　　处：《固体火箭技术》1998年第4期13-17,共5页Journal of Solid Rocket Technology

摘　　要：用数值模拟的方法对多级导弹级间分离时发动机壳体前后封头的温度分布进行了预示。流场计算采用Ｇｏｄｕｎｏｖ格式求解非常定轴对称Ｅｕｌｅｒ方程组；针对物理域比较复杂，采用了区域重叠的分区算法；热流计算考虑了燃气射流中Ａｌ２Ｏ３粒子含量在驻点区引起的热增量。结果表明：对于前封头，由于含有Ａｌ２Ｏ３粒子而引起的驻点区热增量因子达４～６，计算得到的最大热流与实测热流接近；对于后封头，不需采用驻点区热增量模型进行热流计算。The temperature distribution on the fore and aft domes of motors under thermal seperation of missile are predicted utilizing numerical simulation.The Godunov scheme is used to solve the unsteady axisymmetric Euler equations and an overlap zonal multi domain approach for its complex physical region.In calculating the heat flow,the heat increment resulting from the Al 2O 3 particles contained in the combustion gas is considered in the stagnation region.The results show that,for the fore dome,the calculated maximum heat flow agree with the measured maximum heat flow and the augmentation factor can be 4～6;for the aft dome,heat flow calculation need not account for the heat augmentation model for stagnation region.

关 键 词：数值模拟 热流测量 温度分布 导弹 发动机 壳体 

分 类 号：V435.22[航空宇航科学与技术—航空宇航推进理论与工程] TJ760.11[兵器科学与技术—武器系统与运用工程]