导弹发动机喷管流场优化设计仿真研究  

A Simulation Research of Optimization Design for Flow Field In the Nozzle of Missile Engine

作　　者：朱柏银 刘少伟[1] 王学智[1] 王伟[1] 

机构地区：[1]空军工程大学防空反导学院,陕西西安710051

出　　处：《计算机仿真》2016年第7期162-165,179,共5页Computer Simulation

基　　金：国家自然科学基金资助项目(61372166)

摘　　要：在导弹发动机喷管结构优化设计的研究中,喷管结构几何形状对导弹飞行器的推进性能有重要影响。为了研究导弹发动机喷管的结构对燃气流场分布影响的问题,保证导弹有足够的推力,采用计算流体力学(CFD)方法,提出用FLUENT计算来实现对导弹喷管物理模型进行数值仿真,分析了燃气射流对喷管的压力、速度、温度的影响情况及变化曲线。仿真结果表明,导弹发动机点火2.7ms时,燃气射流对喷管后盖影响最大,喷管后盖最大压力为0.4MPa,喷管后盖可被燃气流冲破。喷管尾部壁面最大压力为0.55MPa,导弹壁面最高温度可达2400K。因此必须对导弹进行有效的热防护,仿真结果可为导弹发动机喷管的强度设计和导弹的防护提供参考。In the optimization design research on the structure of missile engine nozzle, the shape of nozzle structure has an important effect on the propelling function of the missile flying. To study the problem that the nozzle structure of missile engine produces an effect on the distribution of the flow field, we adopted a method of computational fluid dynamics （ CFD）, and used the FLUENT calculation to achieve numerical simulation in physical model of nozzle＇s flow field, analysed the influences of jet flow on the pressure, speed, and temperature. The simulation results indicate that when the missile engine lighting-off at 2.7ms, the influence of jet flow on the behind lid is maximum, the maximum pressure is 0.4 Mpa, the behind lid can be bursted by the jet flow. The maximum pressure of the ending wall of nozzle is 0.55 Mpa, and the maximum temperature of the missile wall can reach 2400K. Thus, effective hot protection for missile is necessary. The simulated results offer some reference value for the intensity design and mis- sile protection of missile engine nozzle.

关 键 词：燃气射流 动网格 数值仿真 计算流体力学 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]