摘要
为满足炮射导弹发动机的延迟点火需求,某型产品采用了一种简易的延期点火结构。通过应用不同尺寸的延期体结构,对不同喉径间隙的固体火箭发动机点火内流场特性进行数值模拟。建立了推进剂加质燃烧模型,计算得到了从点火开始到延期体结构逸出前过程中发动机内流场的压力分布情况。采用6DOF动网格模型,模拟出延期体结构逸出喷管的瞬间过程的内流场特性。研究结果表明,在点火建压阶段,间隙越小,发动机内流场瞬态变化越剧烈,达到指定延期体逸出压强的时间越长;在逸出过程中,当延期体结构头端到达喷管喉部时会产生强烈的压力振荡现象,间隙越小,振荡现象越剧烈。
In order to meet the demand of delayed ignition of gun-launched missile engine, a simple extended ignition structure is adopted for a type. By applying different sizes of delayed body structures, the flow field characteristics inside the ignition of solid rocket launchers with different throat diameter gaps are numerically simulated. A propellant additive combustion model is established and the pressure distribution in the internal flow field of the engine is calculated from the start of ignition to the escape of the extended body structure. A 6DOF dynamic mesh model was used to simulate the internal flow field characteristics during the moment when the extension structure escapes from the nozzle. The results show that the smaller the gap is, the more violent the transient changes in the internal flow field of the engine, and the longer the time to reach the specified extended body escape pressure;during the escape process, strong pressure oscillations occur when the extended body structure reaches the nozzle throat at the head end, and the smaller the gap is, the more violent the oscillations are.
作者
井世博
郑健
李嘉旻
JING Shibo;ZHENG Jian;LI Jiaming(School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,Jiangsu,China)
出处
《弹箭与制导学报》
北大核心
2023年第1期32-40,共9页
Journal of Projectiles,Rockets,Missiles and Guidance
关键词
炮射导弹
延期点火具
喉径间隙
点火瞬态特性
gun-launched missile
delayed igniter
throat diameter gap
ignition transient characteristics
