摘要
针对固体火箭发动机被动引射式高模试验研制周期久、成本高的问题,基于N-S方程与S-A模型,利用小扩张比喷管与小尺寸不同直径的高空舱、扩压器、压力远场域对高空模拟试车中的发动机建压、稳压、降压段进行数值仿真,同时分析各模型各阶段高空舱及扩压器内流场结构。结果表明,在发动机压强达到稳定时,大尺寸高空舱相对于小舱而言舱内压强更加稳定,其引射系统中扩压器扩压效果更好,对舱内气体抽吸能力也更强。而大长径比扩压器在引射系统内的减速增压效果相对小长径比而言不明显,气流通过激波时压强与马赫数的变化量分别在2KPa和0.04以内,在扩压器出口处的计算误差与压力远场域的设定有很大关系。
To address the problem of long development cycle and high cost of passive shot high altitude test of solid rocket engine,based on the N-S equation and the S-A model,numerical simulations are carried out for the engine pressure building,pressure stabilization and pressure reduction stages of the high altitude simulator test using small expansion ratio nozzles,small size high altitude chambers with different diameters,pressure diffusers and pressure far fields,and the flow field structures in the high altitude chambers and diffusers are analyzed at each stage of each model.The results show that when the engine pressure is stabilized,the pressure inside the large size cabin is more stable than that inside the small size cabin,and the diffuser in the pilot system has a better pressure expansion effect and a better ability to extract the gas inside the cabin;while the deceleration and pressurisation effect of the large aspect ratio diffuser in the pilot system is not obvious compared with that of the small aspect ratio,and the changes in pressure and Mach number when the airflow passes through the surge are within 2 KPa and 0.04.The calculation error at the outlet of the diffuser is strongly related to the setting of the pressure far field.
作者
苏日泰
李卓
姜皓
SU Ritai;LI Zhuo;JIANG Hao(College of Science,Inner Mongolia University of Technology,Hohhot 010051,China)
出处
《内蒙古工业大学学报（自然科学版）》
2024年第1期23-29,共7页
Journal of Inner Mongolia University of Technology：Natural Science Edition
基金
国家自然科学基金项目(11962021)
内蒙古自治区自然科学基金项目(2021MS05020)。
关键词
固体火箭发动机
高空模拟试车
数值仿真
扩压器
solid rocket motors
high altitude simulation test vehicles
numerical simulation
diffuser
作者简介
第一作者:苏日泰(1996-),男,2020级硕士研究生,主要从事固体火箭发动机高空模拟研究。E-mail:496658325@qq.com;通信作者:李卓(1966-),男,博士,教授,主要从事固体火箭发动机设计研究。E-mail:704028389@qq.com。
