翼柱形药柱发动机点火瞬态三维数值模拟  

Numerical simulation of SRM with finocyl grain during ignition transient

作　　者：独娟子[1] 余贞勇[1] 何景轩[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

出　　处：《固体火箭技术》2009年第2期180-182,共3页Journal of Solid Rocket Technology

摘　　要：采用流体计算软件(Fluent),通过用户自定义函数(UDF),考虑了燃烧室瞬时压强变化的影响,对某固体火箭发动机点火瞬态内流场进行了三维模拟,得出了点火瞬态头部压强-时间变化曲线。结果表明,堵盖打开前燃烧室压强振荡1次,堵盖打开后燃烧室压强振荡3次;随着点火燃气不断加入,燃烧室压强从头至尾呈现先弱后强的变化趋势。该方法能较好地预示点火瞬态的启动特性。By using software（Fluent） of fluid calculation and user definition function（ UDF）, and in consideratiun of the effect of transient pressure interior three dimensional flow field of a SRM with finocyl grain was simulated during ignition transient. They are the curves of pressure-time of transient ignition in head area was obtained. The result shows one pressure oscillation before rup- ture of seal diaphragm and three pressure oscillations after rupture of seal diaphragm isn combustion chamber, and a variety trend of feebleness eatlier and intensity late for the pressute in cobustion chamber. The method can be used to predict characteristics of translent ignition.

关 键 词：固体火箭发动机 点火瞬态 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]