PDF下载 分享
[1]徐学文,牟俊林,任建存,等.固体火箭发动机喷管瞬态流场特性分析[J].火箭推进,2015,41(05):49-53.
　XU Xuewen,MU Junlin,REN Jiancun,et al.The analyses of transient flow-field characteristics in the nozzle of SRM[J].Journal of Rocket Propulsion,2015,41(05):49-53.
点击复制

固体火箭发动机喷管瞬态流场特性分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年05期 页码: 49-53 栏目: 研究与设计 出版日期: 2015-10-31
Title:
The analyses of transient flow-field characteristics in the nozzle of SRM
作者:
徐学文; 牟俊林; 任建存; 单 鑫
海军航空工程学院, 山东 烟台 264001
Author(s):
XU Xuewen;  MU Junlin;  REN Jiancun;  SHAN Xin
Naval Aeronautical Engineering Institute, Yantai 264001, China
关键词:
固体火箭发动机; 喷管; 流场特性
Keywords:
solid rocket motor;  nizzle;  flow-field characteristics
分类号:
V435-34
文献标志码:
A
摘要:
为准确预测某型固体火箭发动机喷管的流场特性，建立了发动机燃烧室－喷管一体化三维流场模型，考虑了上游流场－燃烧室对喷管流场的影响，应用有限体积法，仿真计算出了发动机点火启动过程中喷管内激波的存在及变化趋势，仿真结果与一维等熵函数理论分析结果相一致。结果表明，在发动机点燃初期，喷管内燃气呈现亚音速流动，随着时间推移，在喷管扩张段出现了一道激波，燃气流动出现壅塞，随着燃烧室内燃气压力升高，激波逐渐移出喷管，喷管内呈现超音速顺畅流动。
Abstract:
The 3-D integrated flow-field simulation model of the motor combustion chamber and nozzle was established in order to accurately calculate the flow-field characteristics in the nozzle of the solid rocket motor, the effect of combustion chamber flow field on nozzle flow field being taken into account. The existance and changing trend of a shock wave in the nozzle were calculated during ignition start-up of SRM using the finite volume method, which was consistent with the result of 1-D isentropic funtion theory. As shown in the results, the fuel gas behaving as subsonic flow in the nozzle at the beginning of grain ignition, the fuel gas behaved as choked flow in the nozzle because a shock wave existed in the divergent nozzle with the increase of gas pressure in the chamber, and the fuel gas behaved as supersonic smooth flow in the divergent nozzle when the shock wave were moved outside the nozzle with ignition time increasing.

参考文献/References:

[1]丁英涛, 谢君堂, 仲顺安. 微型喷管内气体流动的流量壅塞现象[J]. 北京理工学学报, 2006,26(12): 1086-1089.
[2]张修峰, 杨立, 宋智勇. 喷管通道内气体流动特性的实验分析与数值模拟[J]. 机电工程技术, 2010, 39(4): 25-28.
[3]刘君, 郭健. 双斜喷管固体火箭发动机流动特性数值模拟[J]. 固体火箭技术, 2002, 25(1): 8-9.
[4]黄宏艳, 王强. 过膨胀状态下轴对称收-扩喷管内外流场计算及分析[J]. 航空动力学报, 2007, 22(7): 1069-1073.

[5]罗静, 王强, 额日其太. 轴对称矢量喷管内流特性的不同湍流模型计算[J]. 推进技术, 2003, 24(4): 326-329.

[6]赵汝岩,隋玉堂,周红梅.具有潜入式喷管的翼柱形药柱发动机火焰传播过程研究[J]. 固体火箭技术, 2010, 33(6): 526-630.
[7]杨乐, 余贞勇, 何景轩. 基于FLUENT 的固体火箭发动机点火瞬态内流场仿真影响因素分析[J]. 固体火箭技术, 2011, 34(4): 474-477.
[8]WILLIAM A D, MICHAEL T H, ROBERT A F. Integ- rated 3-D simulation of solid propellant rockets,AIAA 2001-3949[R]. USA:AIAA,2001.
[9]FIEDLER R, JIAO X, NAMAZXIFARD A. Coupled fluid-structure 3-D solid rocket motor simulations,AIAA2001-3549[R]. USA:AIAA,2001.
[10]VERSTEEG H K, MALAASEKERAW. An introduction to computational fluid dynamics-The Finite Volume Method[M]. Beijing：Beijing World Publishing Corpration. 2000.
[11]苏长荪. 高等工程热力学[M]. 北京: 高等教育出版社, 1987 .

相似文献/References:

[1]梁俊龙,张贵田,秦艳平.基于高阶WENO格式的喷管动态特性仿真分析[J].火箭推进,2015,41(04):29.
　LIANG Junlong,ZHANG Guitian,QIN Yanping.Simulated analysis on nozzle dynamic characteristics based on high-order WENO scheme[J].Journal of Rocket Propulsion,2015,41(05):29.
[2]南向军,张 锐,张留欢.壁面散热对超声速喷管性能的影响[J].火箭推进,2015,41(03):33.
　NAN Xiang-Jun,ZHANG Rui,ZHANG Liu-huan.Effect of wall surface heat dissipation on performance of supersonic nozzle[J].Journal of Rocket Propulsion,2015,41(05):33.
[3]韩 磊,何卫东.液体火箭发动机喷管冷却槽数字化加工技术[J].火箭推进,2014,40(04):57.
　HAN Lei,HE Wei-dong.Digitization process technology of cooling grooves on nozzle of liquid-propellant rocket engine[J].Journal of Rocket Propulsion,2014,40(05):57.
[4]邵松林.某发动机整机模态分析[J].火箭推进,2012,38(04):55.
　SHAO Song-lin.Modal analysis of a rocket engine[J].Journal of Rocket Propulsion,2012,38(05):55.
[5]宋亚飞,高 峰,杨小秋.来流马赫数对射流矢量喷管内流场影响的动态模拟[J].火箭推进,2011,37(06):38.
　SONG Ya-fei,GAO Feng,YANG Xiao-qiu.Dynamic simulation for effect of incoming flow Mach number on internal flow field of fluidic thrust vectoring nozzle[J].Journal of Rocket Propulsion,2011,37(05):38.
[6]宋亚飞,高 峰,曾 华,等.射流推力矢量喷管中粒子运动轨迹的数值模拟[J].火箭推进,2011,37(02):48.
　SONG Ya-fei,GAO Feng,ZENG Hua,et al.Numerical simulation of particle trajectory in fluidic thrust vector nozzle[J].Journal of Rocket Propulsion,2011,37(05):48.
[7]靳瑞斌,向红军.一种新的模拟固体火箭发动机射流铝颗粒燃烧的方法[J].火箭推进,2010,36(06):25.
　JIN Rui-bin,XIANG Hong-jun.New method of numerical simulation of combustion aluminium droplet in exhaust plume for SRM[J].Journal of Rocket Propulsion,2010,36(05):25.
[8]孙成,方杰,郑力铭,等.N20微推力器性能及喷管热结构分析[J].火箭推进,2008,34(05):5.
　Sun Wei,Fang Jie,Zheng Liming,et al.N20 micro-thruster performance and the nozzle thermo-structure analysis[J].Journal of Rocket Propulsion,2008,34(05):5.
[9]艾春安,高利荣,吴安法.固体火箭发动机多层结构壳体的 导波频散特性分析[J].火箭推进,2008,34(05):16.
　Ai Chun'an,Gao Lirong,Wu Anfa.Analysis of dispersive characteristics of guided waves for multi-layered structure of solid rocket motor shell[J].Journal of Rocket Propulsion,2008,34(05):16.
[10]王鹏,李旭昌,徐颖军,等.固体火箭发动机总体优化设计[J].火箭推进,2007,33(04):16.
　Wang Peng,Li Xuchang,Xu Yingjun.The optimal design of solid rocket motors[J].Journal of Rocket Propulsion,2007,33(05):16.

备注/Memo

收稿日期：2014-10-11；修回日期：2014-12-05 作者简介：徐学文（1971—），男，副教授，博士，研究领域为固体火箭发动机可靠性与推进剂性能

更新日期/Last Update: 1900-01-01