固体发动机内流场涡脱落特征数值研究  

Simulation Research on Vortex Shedding Characteristic of Solid Rocket Motor

作　　者：刘长猛[1] 关悦 李鹏飞[3] 王宇[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025 [2]西安向阳航天材料股份有限公司,西安710025 [3]哈尔滨工程大学,哈尔滨150001

出　　处：《战术导弹技术》2016年第4期70-74,81,共6页Tactical Missile Technology

基　　金：国家自然科学基金(10972063)

摘　　要：为了研究分析由不同挡药板结构所引起的固体火箭发动机燃烧室内的流场变化规律,采用大涡模拟方法,对发动机内流场进行数值模拟,计算得到了固体发动机内部的涡脱落频率特征。结果表明,在燃烧室尺度一定的情况下,涡脱落频率会随着挡药板高度和喷管空腔体积的减小而增加,随着挡药板和燃烧室前端面距离的增大而频率值增大。In order to investigate the phenomenon of flow law initiated by configuration of the block,based on large-eddy simulation method,rocket internal flow field is simulated and the frequency characteristic of vortex shedding in solid rocket motor is calculated. The numerical result shows that,the frequency of vortex shedding will becomes larger with the decreasing of the radial characteristic scale of obstacle and the volume of cavity decreases,in the cases of unchanged chamber size. The frequency increases with the increase of the distance between the block and the apical of the chamber.

关 键 词：固体发动机 涡脱落 导弹 火箭发动机 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]