“锥-柱-槽”药型固体火箭发动机点火过程仿真  

Simulation of Solid Rocket Motor Ignition Process with Conical Column-Groove Propellant

作　　者：瞿煌 孙振生 胡宇 朱玉杰 张寅 QU Huang;SUN Zhensheng;HU Yu;ZHU Yujie;ZHANG Yin(Rocket Force University of Engineering,Xi’an 710025,Shaanxi;Jiangxi GuoKe Defence Group Co.,Ltd.,Nanchang 330000,Jiangxi)

机构地区：[1]火箭军工程大学,陕西西安710025 [2]江西国科军工集团股份有限公司,江西南昌330000

出　　处：《火箭军工程大学学报》2024年第6期91-98,共8页Journal of Rocket Force University of Engineering

基　　金：基础加强领域基金(2021-JCJQ-JJ-0424);陕西省自然科学基础研究计划(2023-JC-QN-0052);陕西省青年人才托举计划(No.20230519);博士后基金(2023M734284)。

摘　　要：为了深入了解固体火箭发动机“锥-柱-槽”复杂结构药型点火瞬态过程中的性能变化规律,以PC3-1固体火箭发动机为研究对象,通过药柱侧壁加质法模拟固体火箭发动机加质燃烧,实现了对“锥-柱-槽”药型的固体火箭发动机点火过程数值仿真,获得了发动机内流场特性及发动机压强随时间的变化规律。结果表明:“锥-柱-槽”药型固体火箭发动机在火焰传播期,药柱头部存在压强振荡现象,振幅超过平均压强的5%,此时药柱燃烧为“粗暴燃烧”;随着燃烧过程的不断进行,前锥柱根部与药柱头部会被同时点燃,在分布燃烧的作用下,燃烧室内压强迅速上升,药柱燃烧模式转换为“平稳燃烧”;点火初期,由于燃烧室内压强较高,点火器产生的燃气动能不足以使燃气穿过堵盖,燃烧室内会出现回流,加剧燃烧室内压强振荡,阻碍药柱燃面扩展,使得固体火箭发动机点火时间延长。To explore the performance variations of the conical-column-groove propellant used in the solid rocket motor(SRM)during the transient ignition process,the numerical simula-tion of the ignition of the SRM with conical-column-groove propellant was conducted.Taking PC3-1 SRM as the subject,the mass addition combustion of the SRM was simulated by grain sidewall refuelling technique.Thereby,characteristics of the internal flow field of the SRM and pressure variations of the SRM along with time were obtained.Results showed that the pressure oscillation occurs at the head of the column and the amplitude exceeds 5%over the average pres-sure.In this phase,the combustion of the grain is turbulent combustion.Along with the combus-tion,the base of the conical and the head of the column are ignited simultaneously,while the pressure in the combustor increases rapidly because of the distributed combustion.The combus-tion of the grain is stable combustion.At initial ignition stage,the internal pressure of the com-bustor is relatively high and the kinetic energy of the gas generated by the ignitor is not adequate to make the gas through the plug cap.Consequently,the backflow occurs in the combustor,which intensifies the pressure oscillation within the combustor,impedes the expansion of the pro-pellant column combustion surface,and delays ignition.

关 键 词：固体火箭发动机 侧壁加质 锥-柱-槽 点火仿真 

分 类 号：V231.25[航空宇航科学与技术—航空宇航推进理论与工程]