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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2009年第2期180-182,共3页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
点火瞬态
数值模拟
solid rocket motor
ignition transient
numerical simulation
