含装药裂纹固体火箭发动机点火过程内流场数值模拟  

Numerical Analysis of Internal Flow Field in Igniting Process for the Solid Rocket Motor with Propellant Crack

作　　者：周红梅[1] 于胜春[2] 王庆官[1] 隋玉堂[1] 

机构地区：[1]海军航空工程学院战略导弹工程系,烟台264001 [2]海军航空工程学院飞行器工程系,烟台264001

出　　处：《导弹与航天运载技术》2009年第2期1-4,共4页Missiles and Space Vehicles

基　　金：总装十一五预研课题项目

摘　　要：基于裂纹流场与发动机内流场的耦合作用机理,利用裂纹出口流场参数来计算裂纹向燃烧室流场喷射质量流率的方法,对含装药裂纹固体火箭发动机点火过程的内流场进行了数值模拟,得到了内流场的分布情况,通过分析计算结果,总结出不同位置、不同几何尺寸的裂纹对发动机内流场的影响规律。Based on the coupling principle of the propellant crack flow and the motor internal flow field, using the parameters of the flow field on the crack outlet, the mass flow rate spurted by crack from combustor is computed. The internal flow field in igniting process for the solid rocket motor with propellant crack is simulated, the detailed distribution about the internal flow field for the motor is obtained. At last, the infuences of propellant of cracks at different positions and in different shapes on motor combustor internal flow field are obtained.

关 键 词：固体火箭发动机 裂纹 内流场 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]