Gas⁃solid two⁃phase flow characteristics of SRM propellant with front and rear wings

Jun ZHANG; Lei QIN; Tianyu GAO; Minghua WANG; Shenxin JIN; Puqing GAO

doi:10.13224/j.cnki.jasp.20210137

Chinese

您当前的位置：

首页 >

文章列表页 >

Gas⁃solid two⁃phase flow characteristics of SRM propellant with front and rear wings

Rocket Engine | 更新时间：2025-04-07

- Gas⁃solid two⁃phase flow characteristics of SRM propellant with front and rear wings
- Journal of Aerospace Power Vol. 37, Issue 3, Pages: 664-672(2022)
- 作者机构：
  
  1.上海海洋大学工程学院，上海 201306
  2.中国航天科工集团有限公司;第六研究院第41研究所，呼和浩特 010010
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210137
  CLC：
- 稿件说明：
移动端阅览
Jun ZHANG, Lei QIN, Tianyu GAO, et al. Gas⁃solid two⁃phase flow characteristics of SRM propellant with front and rear wings[J]. Journal of Aerospace Power, 2022, 37(3): 664-672.
DOI：

Jun ZHANG, Lei QIN, Tianyu GAO, et al. Gas⁃solid two⁃phase flow characteristics of SRM propellant with front and rear wings[J]. Journal of Aerospace Power, 2022, 37(3): 664-672. DOI： 10.13224/j.cnki.jasp.20210137.

摘要

基于可压缩流动强守恒型Navier⁃Stokes方程，运用颗粒轨道模型（PTM）和shear stress transfer（SST）

k⁃ω

湍流模型，采用计算单元内颗粒源法（PSIC）进行气固两相耦合计算，建立了某型前后翼型装药结构固体火箭发动机（SRM）工作初期的三维两相内流场数值计算模型。对比分析了纯气相和气固两相条件下的SRM内部压强场、速度场、粒子沉积质量浓度和分布规律；重点研究了SRM燃烧室和喷管不同部位的颗粒沉积质量浓度，并考虑了不同颗粒物粒径、横向及纵向过载等因素的影响。结果表明：前后翼型装药结构SRM工作过程所产生的固体粒子主要集中于药柱前翼、后翼及筒段壁面；随着颗粒物粒径增加，各监测面上的粒子沉积质量浓度均升高；横向过载量与承载面最大颗粒沉积量呈正相关，且承载面和非承载面的粒子分布不均匀；随着轴向过载增加，颗粒物沿过载方向不断积累，逃逸率升高，沉积量降低；过载所引起的颗粒物方向偏转将同时影响燃烧室和喷管壁面的粒子沉积质量浓度，在前后翼型装药结构SRM绝热层设计中应充分考虑。

Abstract

Based on the Navier⁃Stokes equation with strong conservation of compressible flow，the particle trajectory model （PTM） and shear stress transfer （SST）

k⁃ω

turbulence model were applied to calculate the gas⁃solid two⁃phase coupling by using the particle source method （PSIC） in the computational unit，and the three⁃dimensional two⁃phase flow field numerical calculation model of a type of solid rocket motor （SRM） with front and rear wings propellant at the ignition was established.The pressure field，velocity field，particle deposition mass concentrations and distributions under single⁃phase and two⁃phase conditions were compared and analyzed.The particle deposition mass concentrations in different parts of SRM combustion chamber and nozzle were studied，and the effects of different particle sizes，transvers and axial overloads were considered.The results showed that the solid particles produced by the front and rear wing SRM were mainly concentrated around the front wing，rear wing and the wall of the cylinder.With the increase of particle size，the particle deposition mass concentration on each monitoring surface increased.The transverse overload was positively correlated with the maximum particle deposition on the bearing surface，and the particle distribution on the bearing surface and the non⁃bearing surface was uneven.With the increase of axial overload，particles accumulated continuously along the overload direction，the escape rate increased，and the deposition decreased.The particle direction deflection caused by overload could affect the particle deposition mass concentration on the wall of combustion chamber and nozzle at the same time，which should be fully considered in the design of SRM insulation layer with front and rear wings charge propellant.

关键词

Keywords

references

田维平，王立武，王伟 . 固体火箭发动机技术发展和面临的关键技术问题 [J]. 固体火箭技术， 2021 , 44 （ 1 ）: 4 ⁃ 8 .

TIAN Weiping , WANG Liwu , WANG Wei . Solid rocket engine technology development and key technical problems [J]. Journal of Solid Rocket Technology , 2021 , 44 （ 1 ）: 4 ⁃ 8 . （in Chinese）

杨毅强 . 国外固体运载火箭技术的新进展与启示 [J]. 固体火箭技术， 2012 , 35 （ 5 ）: 569 ⁃ 572,582 .

YANG Yiqiang . New progress and enlightenment of solid rocket technology abroad [J]. Journal of Solid Rocket Technology , 2012 , 35 （ 5 ）: 569 ⁃ 572,582 . （in Chinese）

王宁飞，张峤，李军伟，等 . 固体火箭发动机不稳定燃烧研究进展 [J]. 航空动力学报， 2011 , 26 （ 6 ）: 1405 ⁃ 1414 .

WANG Ningfei , ZHANG Qiao , LI Junwei , et al . Research progress on unstable combustion of solid rocket motor [J]. Journal of Aerospace Power , 2011 , 26 （ 6 ）: 1405 ⁃ 1414 . （in Chinese）

张承志，李江，刘洋，等 . 颗粒冲刷条件对绝热材料烧蚀过程的影响研究 [J]. 固体火箭技术， 2013 , 36 （ 2 ）: 200 ⁃ 205 .

ZHANG Chengzhi , LI Jiang , LIU Yang , et al . Effect of particle erosion conditions on ablation process of insulation materials [J]. Journal of Solid Rocket Technology , 2013 , 36 （ 2 ）: 200 ⁃ 205 . （in Chinese）

王宁飞，苏万兴，李军伟，等 . 固体火箭发动机中铝粉燃烧研究概述 [J]. 固体火箭技术， 2011 , 34 （ 1 ）: 61 ⁃ 66 .

WANG Ningfei , SU Wanxing , LI Junwei , et al . Overview of research on combustion of aluminum powder in solid rocket motor [J]. Journal of Solid Rocket Technology , 2011 , 34 （ 1 ）: 61 ⁃ 66 . （in Chinese）

彭维康，赵晓尧，李子妍，等 . 管状火焰燃烧器中高氧气浓度丙烷燃烧特性 [J]. 工程热物理学报 , 2018 , 39 （ 1 ）: 218 ⁃ 223 .

PENG Weikang , ZHAO Xiaoyao , LI Ziyan , et al . Combustion characteristics of propane with high oxygen concentration in tubular flame burners [J]. Journal of Engineering Thermophysics , 2018 , 39 （ 1 ）: 218 ⁃ 223 . （in Chinese）

李艺，郭晓燕，杨荣杰，等 . 铝/有机氟化物复合物对含铝HTPB推进剂燃烧性能的影响 [J]. 火炸药学报 , 2016 , 39 （ 6 ）: 74 ⁃ 79 .

LI Yi , GUO Xiaoyan , YANG Rongjie , et al . Effect of aluminum/organic fluoride compound on combustion performance of HTPB propellant containing aluminum [J]. Chinese Journal of Explosives and Propellants , 2016 , 39 （ 6 ）: 74 ⁃ 79 . （in Chinese）

崔立堃 . 过载状态下固体火箭发动机内流场数值计算 [J]. 战术导弹技术， 2017 （ 3 ）: 98 ⁃ 103 .

CUI Likun . Numerical calculation of internal flow field of solid rocket motor under overload condition [J]. Tactical Missile Technology , 2017 （ 3 ）: 98 ⁃ 103 . （in Chinese）

李江，何国强，陈剑，等 . 高过载条件下绝热层烧蚀实验方法研究（Ⅱ）收缩管聚集法 [J]. 推进技术， 2004 , 25 （ 3 ）: 196 ‑ 198 .

LI Jiang , HE Guoqiang , CHEN Jian , et al . Experimental method of thermal insulation ablation under high overload （Ⅱ） shrinkage tube aggregation method [J]. Journal of Propulsion Technology , 2004 , 25 （ 3 ）: 196 ⁃ 198 . （in Chinese）

王立武，赵朝坤，田维平，等 . 过载对固体发动机凝相粒子运动的影响分析 [J]. 空气动力学学报， 2020 , 38 （ 5 ）: 874 ⁃ 879 .

WANG Liwu , ZHAO Chaokun , TIAN Weiping , et al . Analysis of the influence of overload on the motion of solid engine condensate particles [J]. Acta Aerodynamica Sinica , 2020 , 38 （ 5 ）: 874 ⁃ 879 . （in Chinese）

苏万兴，李世鹏，张峤，等 . 某固体火箭发动机工作末期不稳定燃烧 [J]. 航空动力学报， 2013 , 28 （ 10 ）: 2376 ⁃ 2383 .

SU Wanxing , LI Shipeng , ZHANG Qiao , et al . The unstable combustion of a solid rocket motor at the end of work [J]. Journal of Aerospace Power , 2013 , 28 （ 10 ）: 2376 ⁃ 2383 . （in Chinese）

郭颜红，梁晓庚，陈斌 . 大过载下固体火箭发动机内弹道计算 [J]. 航空动力学报， 2008 , 23 （ 10 ）: 1944 ⁃ 1948 .

GUO Yanhong , LIANG Xiaogeng , CHEN Bin . Interior ballistic calculation of solid rocket motor under heavy overload [J]. Journal of Aerospace Power , 2008 , 23 （ 10 ）: 1944 ⁃ 1948 . （in Chinese）

常桁，王一白，刘宇，等 . 固体火箭发动机碳基材料喷管机械侵蚀特性 [J]. 航空动力学报， 2016 , 31 （ 3 ）: 756 ⁃ 762 .

CHANG Heng , WANG Yibai , LIU Yu , et al . Mechanical erosion characteristics of solid rocket motor carbon⁃based material nozzle [J]. Journal of Aerospace Power , 2016 , 31 （ 3 ）: 756 ⁃ 762 . （in Chinese）

CORTOPASSI A , BOYER E , KUO K . A subscale solid rocket motor for characterization of submerged nozzle erosion [J]. Journal of Fluids Engineering , 2006 , 134 （ 4 ）: 234 ⁃ 252 .

ACHARYA R , KUO K K . Effect of pressure and propellant composition on graphite rocket nozzle erosion rate [J]. Journal of Propulsion and Power , 2007 , 23 （ 6 ）: 1242 ⁃ 1254 .

CHATURVEDI A K , KΜMAR S , CHAKRABORTY D . Slag prediction in submerged rocket nozzle through two⁃phase CFD simulations [J]. Defence Science Journal , 2015 , 65 （ 2 ）: 99 ⁃ 106 .

SHIMADA T , SEKIGUCHI M , SEKINO N . Flow inside a solid rocket motor with relation to nozzle inlet ablation [J]. AIAA Journal , 2007 , 45 （ 6 ）: 1324 ⁃ 1332 .

QIN F , PENG L N , LI J , et al . Numerical simulations of multiscale ablation of carbon/carbon throat with morphology effects [J]. AIAA Journal , 2017 , 55 （ 10 ）: 3476 ⁃ 3485 .

GUAN Yiwen , LI Jiang , LIU Yang , et al . Deposits evolution and its heat transfer characteristics research in solid rocket motor [J]. Applied Thermal Engineering , 2021 , 184 （ 10 ）: 1359 ‑ 4311 .

何国强，王国辉，蔡体敏，等 . 高过载条件下固体发动机内流场及绝热层冲蚀研究 [J]. 固体火箭技术， 2001 , 24 （ 4 ）: 4 ⁃ 8 .

HE Guoqiang , WANG Guohui , CAI Timin , et al . Study on flow field and adiabatic erosion in solid engine under high overload conditions [J]. Journal of Solid Rocket Technology , 2001 , 24 （ 4 ）: 4 ⁃ 8 . （in Chinese）

何国强，王国辉，蔡体敏，等 . 过载条件下固体发动机内流场数值模拟 [J]. 推进技术， 2002 ， 23 （ 3 ）: 182 ⁃ 185 .

HE Guoqiang , WANG Guohui , CAI Timin , et al . Numerical simulation of flow field in solid engine under overload [J]. Journal of Propulsion Technology , 2002 , 23 （ 3 ）: 182 ⁃ 185 . （in Chinese）

淡林鹏，张振鹏，赵永忠，等 . 长尾喷管中粒子运动轨迹的数值模拟 [J]. 航空动力学报， 2003 ， 18 （ 2 ）: 258 ⁃ 263 .

DAN Linpeng , ZHANG Zhenpeng , ZHAO Yongzhong , et al . Numerical simulation of particle trajectory in long tail nozzle [J]. Journal of Aerospace Power , 2003 , 18 （ 2 ）: 258 ⁃ 263 . （in Chinese）

李越森，叶定友 . 高过载下固体发动机内Al 2 O 3 粒子运动状况的数值模拟 [J]. 固体火箭技术， 2008 , 31 （ 1 ）: 24 ⁃ 27 .

LI Yuesen , YE Dingyou . Numerical simulation of Al 2 O 3 particle motion in solid engine under high overload [J]. Journal of Solid Rocket Technology , 2008 , 31 （ 1 ）: 24 ⁃ 27 . （in Chinese）

于勇，刘淑艳，张世军，等 . 固体火箭发动机喷管气固两相流动的数值模拟 [J]. 航空动力学报， 2009 , 24 （ 4 ）: 931 ⁃ 937 .

YU Yong , LIU Shuyan , ZHANG Shijun , et al . Numerical simulation of gas⁃solid two⁃phase flow in solid rocket motor nozzle [J]. Journal of Aerospace Power , 2009 , 24 （ 4 ）: 931 ⁃ 937 . （in Chinese）

陈福振，强洪夫，高巍然，等 . 固体火箭发动机内气粒两相流动的SPH⁃FVM耦合方法数值模拟 [J]. 推进技术， 2015 , 36 （ 2 ）: 175 ⁃ 185 .

CHEN Fuzhen , QIANG Hongfu , GAO Weiran , et al . Numerical simulation of gas⁃particle two⁃phase flow in solid rocket motor by SPH⁃FVM coupling method [J]. Journal of Propulsion Technology , 2015 , 36 （ 2 ）: 175 ⁃ 185 . （in Chinese）

王立武，田维平，郭运强，等 . 典型喉衬材料抗过载烧蚀性能的实验研究 [J]. 推进技术， 2020 , 41 （ 10 ）: 2367 ⁃ 2373 .

WANG Liwu , TIAN Weiping , GUO Yunqiang , et al . Experimental study on overload ablation resistance of typical throat lining materials [J]. Journal of Propulsion Technology , 2020 , 41 （ 10 ）: 2367 ⁃ 2373 . （in Chinese）

张俊，田中旭，许哲，等 . 柔性喷管 SRM 三维两相内流场数值模拟 [J]. 弹道学报， 2018 , 29 （ 4 ）: 76 ⁃ 80 .

ZHANG Jun , TIAN Zhongxu , XU Zhe , et al . Simulation on 3d two⁃phase inner flow field for flexible⁃nozzle SRM [J]. Journal of Ballistics , 2018 , 29 （ 4 ）: 76 ⁃ 80 . （in Chinese）

张俊，高天宇，高璞清，等 . 固体火箭发动机工作末期的内流场数值计算 [J]. 弹箭与制导学报， 2018 , 38 （ 3 ）: 58 ⁃ 62 .

ZHANG Jun , GAO Tianyu , GAO Puqing , et al . Simulation of inner flow fields at end of burning in SRM [J]. Journal of Projectiles,Rockets,Missiles and Guidance , 2018 , 38 （ 3 ）: 58 ⁃ 62 . （in Chinese）

刘长猛，余贞勇，李侃，等 . 飞行过载下燃烧室凝相粒子沉积特征数值研究 [J]. 固体火箭技术， 2017 ， 40 （ 3 ）: 302 ⁃ 306 .

LIU Changmeng,YU Zhenyong,LI Kan,et alNumerical study on deposition characteristics of condensed phase particles in combustion chamber under flight overload [J]. Journal of Solid Rocket Technology , 2017 , 40 （ 3 ）: 302 ⁃ 306 . （in Chinese）

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Simulation study on the influence of spin on ignition process of two⁃phase in solid rocket motor

Phase transition characteristics of ice crystal particles in motion

Impact of ignition charge on ignition process of dual⁃pulse solid rocket motor

Influence of transverse variable acceleration on design of insulation structure for solid rocket motor

Study on reduction of waste grain rate for semi-spherical conic-column grain

Related Author

Shengfu QIN

Junwei LI

Zhihui ZHANG

Ye HE

Ningfei WANG

Ping HUANG

Xueqin BU

Guiping LIN

Related Institution

School of Aerospace Engineering，Beijing Institute of Technology

School of Aeronautic Science and Engineering，Beihang University

Key Laboratory of Icing and Anti/De⁃icing， China Aerodynamics Research and Development Center

School of Aerospace Engineering，Beijing University of Technology

Xi'an Modern Chemistry Research Institute，China North Industries Group Corporation Limited

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰