过载对固体发动机凝相粒子运动的影响分析

王立武; 赵朝坤; 田维平; 郭运强

doi:10.7638/kqdlxxb-2018.0193

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

过载对固体发动机凝相粒子运动的影响分析

研究论文 | 更新时间：2026-05-28

- 过载对固体发动机凝相粒子运动的影响分析
- Analysis of particle motion in solid rocket motor under different acceleration
- 空气动力学学报 2020年38卷第5期页码：874-879
- 作者机构：
  
  1. 西北工业大学燃烧、热结构与内流场重点实验室,西安,710072
  2. 中国航天科技集团有限公司第四研究院第四十一研究所,西安,710025
  3. 中国航天科技集团有限公司第四研究院,西安,710025
- 作者简介：
  
  王立武(1989-), 男, 博士, 研究领域为固体火箭发动机设计.E-mail:wangliwu41@126.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0193
  中图分类号： V435
- 纸质出版：2020
- 稿件说明：
移动端阅览
王立武, 赵朝坤, 田维平, 郭运强. 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 particle motion in solid rocket motor under different acceleration[J]. 2020, 38(5): 874-879.
王立武, 赵朝坤, 田维平, 郭运强. 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. DOI： 10.7638/kqdlxxb-2018.0193.

WANG Liwu, ZHAO Chaokun, TIAN Weiping, et al. Analysis of particle motion in solid rocket motor under different acceleration[J]. 2020, 38(5): 874-879. DOI： 10.7638/kqdlxxb-2018.0193.

摘要

为了获得过载对固体发动机凝相粒子运动规律的影响，采用理论分析和数值仿真相结合的方法，分析了不同过载条件下凝相粒子运动及壁面粒子浓度分布情况。结果表明，横向过载将改变粒子的运动轨迹，引起粒子在发动机内部停留时间的增加；在过载条件作用下，燃烧室筒段壁面和喷管收敛段壁面均存在粒子浓度局部增大的区域，呈现多峰分布现象；不同横向过载、轴向过载条件通过改变粒子的偏转方向和随流性，最终导致燃烧室壁面和喷管收敛段壁面粒子浓度的改变。

Abstract

In order to obtain the regulation of particle motion in solid rocket motor(SRM) under overload conditions

theoretical and numerical methods are used to analyze particle motion and concentration under different acceleration. A three-dimensional model of viscous compressible two-phase flow in the SRM was established. The Eulerian-Lagrangian multiphase model was used to calculate the trajectories of the discrete phase. This analysis used the numerical solution of Reynolds-averaged Navier-Stokes equations for the continuous phase

coupled with a Lagrangian analysis for the discrete phase to simulate the two-phase internal flow. Results show that the lateral overload increases particle residence time in the SRM by changing the trajectory of particles. In addition

the surface of the SRM combustion chamber and the nozzle convergent section both have an area with high particle concentration

which has an multimodal distribution. Furthermore

different lateral and axial overload leads to the change of particle concentration in surface of the SRM combustion chamber and the nozzle convergent section

which is caused by transforming the direction of particle.

关键词

Keywords

references

CAO J, GUO Y H, XING Q. Research on the working stabilization of solid rocket motor under high overload[J]. Aero Weaponry, 2014(1):33-36.(in Chinese)

LIU Y. The experimental simulation technique of flow field under high acceleration condition[D]. Xi'an: Northwestern Polytechnical University, 2004. (in Chinese)

LI J, HE G Q, CHEN J, et al. Study of experimental method for ablation of insulator of SRM with high acceleration (Ⅱ) Convergent tube experimental method[J]. Journal of Propulsion Technology, 2004, 25(3):196-198.(in Chinese) doi:10.13675/j.cnki.tjjs.2004.03.002

LIU Y, LI J, YANG S, et al. Investigation on ablation mechanism and model of EPDM insulator under high acceleration condition(Ⅰ):Analysis of ablation mechanism[J]. Journal of Solid Rocket Technology, 2011, 34(2):229-233.(in Chinese)

GAO F, WANG J H, MA C R. Numerical simulation of the tail nozzle pipe of heat transfer in high acceleration[J]. Journal of Air Force Engineering University (Natural Science Edition), 2012, 13(1):1-5.(in Chinese)

XIE W C, XU D L, CAI X Y, et al. Design of air to air missile propulsion system[M]. Beijing:National Defence Industry Press, 2007.(in Chinese)

GUO Y H, LIANG X G, CHEN B. Working process simulation of solid rocket motor with high acceleration load[J]. Aero Weaponry, 2008(1):21-25.(in Chinese)

WU Y, HE G Q, SUN Z P, et al. Experiment study of effects induced by overload on SRM performance[J]. Journal of Solid Rocket Technology, 2010, 33(5):511-514.(in Chinese)

CROWE C. Modeling fluid-particle flows-Current status and future directions[C]//30th Fluid Dynamics Conference. 1999: AIAA-99-3690.

KING M K. Critical review:modeling of acceleration effects on solid propellant combustion[J]. AIAA Journal, 1976, 14(1):18-25. doi:10.2514/3.61329

GREATRIX D R. Structural vibration and solid rocket combustion instability[J]. Canadian Aeronautics Space Journal, 1998, 44(1):9-24.

SABNIS J S, DE JONG F J, GIBELING H J. Calculation of particle trajectories in solid-rocket motors with arbitrary acceleration[J]. Journal of Propulsion and Power, 1992, 8(5):961-967. doi:10.2514/3.23579

HEG Q, WANG G H, CAI T M, et al. Numerical simulation on 3-D two-phase flow field in SRM with acceleration load[J]. Journal of Propulsion Technology, 2002, 23(3):182-185.(in Chinese)

LI Y S, YE D Y, LI F X. An experimental study of SRM insulation erosion performance under transverse g-load in flight[J]. Journal of Aerospace Power, 2004, 19(2):278-282.(in Chinese)

TIANW P, XU T W, WANG J R. Progress on condensed-phase particle characteristic and insulation ablation in SRM chamber with flight overload[J]. Journal of Solid Rocket Technology, 2015, 38(1):30-36, 66.(in Chinese)

JIANGG Q, WANG S H, WANG Y. Finite element numerical simulation of two-phase flow in nozzle for solid rocket motor[J]. Acta Aerodynamica Sinica, 1991, 9(1):58-66.(in Chinese)

DANL P, ZHANG Z P, ZHAO Y Z, et al. Numerical study of particle trajectories in a nozzle with a tail pipe[J]. Journal of Aerospace Power, 2003, 18(2):258-263.(in Chinese)

LIU Y, HE G Q, LI J, et al. Numerical study on 3D two-phase flow field for tail-pipe nozzle SRM under high acceleration[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2006, 26(1):421-424.(in Chinese) doi:10.15892/j.cnki.djzdxb.2006.s2.028

ZHANG Z F, LIU Y, CAI T M. Application of stochastic trajectory model in tail-nozzle SRM flow field numerical simulation[J]. Journal of Solid Rocket Technology, 2007, 30(5):376-380.(in Chinese)

WANG Y T, LIU G, CHEN Z B. Summary of the first aeronautical computational fluid dynamics credibility workshop[J]. Acta Aerodynamica Sinica, 2019, 37(2):247-261.(in Chinese)

XUT W, TIAN W P, WANG J R. Numerical simulation of flow field of tactical SRM with low and medium acceleration[J]. Journal of Propulsion Technology, 2015, 36(4):532-539.(in Chinese)

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

基于神经网络与遗传算法的热气防冰结构优化

交错型CPR方法的保正实现策略及其对比研究

大展弦比飞行器突风响应数值计算

类HyTRV升力体阻尼/交叉动导数特性分析

水滴撞击运动超疏水表面特性及其调控