Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload

Zhongliang TIAN; Junwei LI; Ye HE; Tuanwei XU; Miao DING; Ningfei WANG

doi:10.12382/bgxb.2022.0162

您当前的位置：

首页 >

文章列表页 >

Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload

更新时间：2025-08-18

- Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload
- Acta Armamentarii Vol. 44, Issue 7, Pages: 1896-1907(2023)
- 作者机构：
  
  1. 北京理工大学宇航学院, 北京 100081
  2. 中国航天科技集团有限公司第四研究院第四十一所燃烧、热结构与内流场重点实验室, 陕西西安 710025
- 作者简介：
- 基金信息：
- DOI：10.12382/bgxb.2022.0162
  CLC：
- Received：15 March 2022，
  
  Published Online：07 August 2023，
  
  Published：30 July 2023
- 稿件说明：
移动端阅览
Zhongliang TIAN, Junwei LI, Ye HE, et al. Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload[J]. Acta Armamentarii, 2023, 44(7): 1896-1907.
DOI：

Zhongliang TIAN, Junwei LI, Ye HE, et al. Analysis of Interior Ballistic Characteristics of Conical Three-Dimensional Charge Column Under Lateral Overload[J]. Acta Armamentarii, 2023, 44(7): 1896-1907. DOI： 10.12382/bgxb.2022.0162.

摘要

高空中作机动飞行的导弹易出现内弹道异常

严重时可能导致飞行任务失败。为了分析内弹道异常机理

对横向过载下发动机内弹道特性展开研究

进行过载下丁羟三组元推进剂燃速测量试验

建立过载下该推进剂燃速模型;基于此模型

模拟锥孔三维药柱非均匀燃面退移

进行全程横向过载、短时恒定横向过载、短时振荡横向过载三种过载方式下发动机的内弹道特性研究。研究结果表明:横向过载会使燃烧室压强增加

绝热层暴露时间提前;振荡式过载产生的压强振荡频率与过载振荡频率一致;瞬间横向过载会使燃烧室压强发生跃迁

在100

过载下

压强增加8%左右

过载消失

压强骤降;若受横向过载时间间隔一定

则导弹在压强稳定时做机动飞行更有利。

Abstract

The occurrence of internal ballistic anomalies during high-altitude missile maneuvering can result in flight mission failures. To analyze the abnormal mechanism of internal ballistics

the internal ballistics characteristics of motor under lateral overload were studied. Experimental measurements of the burning rate of HTPB ternary propellant under overload conditions were conducted

and a burning rate model of the propellant under overload was established. Based on this model

the non-uniform combustion surface retreat of cone-hole grain was simulated. The interior ballistic characteristics of cone-hole grain under three overload modes

namely

full lateral overload

short-time constant lateral overload

and short-time oscillation lateral overload

were studied. The results show that lateral overload increases the pressure in the combustion chamber and accelerates the exposure time of the insulation layer. The pressure oscillation frequency produced by oscillating overload is consistent with that of overload oscillation. Instantaneous lateral overload leads to a transitional increase in combustion chamber pressure. Under 100

overload

the pressure increases by about 8%

the overload disappears

and the pressure plummets. When the lateral overload time interval i

s constant

stable pressure conditions are advantageous for missile maneuvering under overload conditions.

关键词

Keywords

references

唐金兰 , 刘佩进 . 固体火箭发动机原理 [M ] . 北京 : 国防工业出版社 , 2012 : 251 - 253 .

TANG J L , LIU P J . Principle of solid rocket motor [M ] . Beijing : National Defense Industry Press , 2012 : 251 - 253 . (in Chinese)

CROWE C T , WILLOUGHBY P G . Effect of spin on the internal ballistics of a solid propellant motor [C ] //Proceedings of Aerospace Sciences Meeting.New York, NY, US:AIAA,1966.

BAKER K L , CRIWE C T , WILLOUGHBY P G . A photographic and analytic study of composite propellant combustionin an acceleration field [J ] . Journal of Spacecraft & Rockets , 1971 , 8 ( 4 ): 310 - 317 .

WILLOUGHBY P G , CROWE C T , BAKER K L . A photogr-aphic and analytic study of composite propellant Co-mbustion in an acceleration field [J ] . Spacecraft , 1971 , 8 ( 4 ): 310 - 317 .

GLICK R L . An analytical study of the effects of radial acceleration upon the combustion mechanism of solid propellant final report:NASA-CR-66218 [R ] . Washington, D.C. , US : NASA , 1966 .

NORTHAM G B . Effects of steady-state acceleration on combustion characteristics of an aluminized composite solid propellant [J ] . Speculum , 1969 , 44 ( 6 ): 1 - 41 . DOI: 10.2307/2855034 http://doi.org/10.2307/2855034 https://www.journals.uchicago.edu/doi/10.2307/2855034 https://www.journals.uchicago.edu/doi/10.2307/2855034

GREATRIX D R , GOTTLIEB J . Model for prediction of normal acceleration augmentation of composite-propellant combustion [J ] . Mental Retardation , 1987 , 7 ( 2 ): 3 - 6 .

GREATRIX D R . Acceleration-based combustion augmen-tation modelling for noncylindrical grain solid rocket motors [C ] //Proceedings of Joint Propulsion Conference & Exhibit.San Diego,CA, US:AIAA, 1995 .

GREATRIX D R . Powered flight the engineering of aerospace Propulsion [M ] . London,UK:Springer , 2012 : 371 - 373 .

包轶颖 , 赵瑜 , 丁逸夫 , 等 . 横向加速度下固体火箭燃面推移规律 [J ] . 固体火箭技术 , 2016 , 39 ( 1 ): 23 - 27 .

BAO Y Y , ZHAO Y , DING Y F , et al . Solid propellant grain motion under lateral acceleration [J ] . Journal of Solid Rocket Technology , 2016 , 39 ( 1 ): 23 - 27 . (in Chinese)

官典 , 李世鹏 , 刘筑 , 等 . 横向过载对固体火箭发动机推进剂点火建压过程的影响 [J ] . 兵工学报 , 2021 , 42 ( 9 ): 1877 - 1887 . DOI: 10.3969/j.issn.1000-1093.2021.09.008 http://doi.org/10.3969/j.issn.1000-1093.2021.09.008 大过载下固体火箭燃烧与流动状态的剧烈变化会导致内弹道出现异常，严重时可能会引起发动机点火失败。为研究横向过载时点火内弹道特性，建立囊括流场惯性过载效应、过载燃烧效应和侵蚀燃烧效应的点火模型。对不同横向过载下燃烧室压力和侵蚀与过载效应燃速增速占比进行计算，并给出了推进剂火焰传播速度与升压速率的关系。结果表明：正向过载下压力峰值增加，负向过载下压力峰值降低；正向过载下，推进剂前段主要由过载效应影响，后段主要由侵蚀效应影响；正向过载加剧下游侵蚀效应，而负向过载对推进剂的燃烧起削弱作用，但程度较弱、持续时间较短；火焰传播速度峰值时刻、推进剂表面首次全部点燃时刻和升压速率峰值点时刻几乎一致，工程上可以用实验中获得的升压速率分析推进剂表面燃烧状况。

GUAN D , LI S P , LIU Z , et al . Influence of lateral acceleretion on ignition transients of solid rocket motor [J ] . Acta Armamentarii , 2021 , 42 ( 9 ): 1877 - 1887 . (in Chinese)

GREATRIX D R . A study of combustion and flow behavior in solid-propellant rocket motors [D ] . Toronto,Canada : University of Toronto , 1987 .

GREATRIX D R . Correlation of pressure rise with radial vibration level in solid rocket motors [C ] //Proceedings of Joint Propulsion Conference & Exhibit.San Diego,CA,US:AIAA,1995.

GREATRIX D R , HARRIS P G . Structural vibration consi-derations for solid rocket internal ballistics modeling [C ] //Proceedings of AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Las Vegas,NV,US:AIAA, 2000 .

李桢 , 王中伟 , 张为华 , 等 . 横向过载下固体火箭发动机内弹道仿真 [J ] . 弹箭与制导学报 , 2005 , 25 ( 4 ): 726 - 728 ,732.

LI Z , WANG Z W , ZHANG W H , et al . Internal ballistic simulation of solid rocket engine under lateral overload [J ] . Journal of Missile and Guidance , 2005 , 25 ( 4 ): 726 - 728 ,732. (in Chinese)

曹军 , 郭颜红 , 邢强 . 高过载条件下固体火箭发动机工作稳定性研究 [J ] . 航空兵器 , 2014 , 51 ( 1 ): 33 - 36 .

CAO J , GUO Y H , XING Q . Research on the working stability of solid rocket engine under high overload [J ] . Aviation Weapons , 2014 , 51 ( 1 ): 33 - 36 . (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 Y H , LIANG X G , CHEN B . Internal ballistic calculation of solid rocket engines under large overload [J ] . Journal of Aerodynamics , 2008 , 23 ( 10 ): 1944 - 1948 . (in Chinese)

郭颜红 , 梁晓庚 , 陈斌 . 大过载下固体火箭发动机工作过程仿真的数学模型 [J ] . 航空兵器 , 2008 , 45 ( 1 ): 21 - 25 .

GUO Y H , LIANG X G , CHEN B . Working process simulation of solid rocket motor with high acceleration load [J ] . Aero Weaponry , 2008 , 45 ( 1 ): 21 - 25 . (in Chinese)

刘中兵 , 郜伟伟 , 张飞 . 飞行过载对固体发动机内弹道的影响 [J ] . 固体火箭技术 , 2018 , 41 ( 2 ): 169 - 175 .

LIU Z B , GAO W W , ZHANG F . Influence of aeecleration on internal ballistics of solid rocker motor [J ] . Journal of Solid Rocket Technology , 2018 , 41 ( 2 ): 169 - 175 . (in Chinese)

檀叶 , 何景轩 , 孙展鹏 . 过载条件下固体火箭发动机燃烧稳定性分析 [J ] . 弹箭与制导学报 , 2015 , 35 ( 3 ): 113 - 116 .

TAN Y , HE J X , SUN Z P . Combustion Stability analysis for solid rocket motor under overload [J ] . Journal of Projectiles,Rockets,Missiles and Guidance , 2015 , 35 ( 3 ): 113 - 116 . (in Chinese)

张翔宇 , 高波 , 甘晓松 , 等 . 飞行过载对固体火箭发动机不稳定燃烧的影响 [J ] . 宇航学报 , 2019 , 40 ( 8 ): 972 - 976 .

ZHANG X Y , GAO B , GAN X S , et al . Impacts of flight acceleration on combustion instability of solid rocket motor [J ] . Journal of Astronautics , 2019 , 40 ( 8 ): 972 - 976 . (in Chinese)

贺业 , 李军伟 , 田忠亮 , 等 . 过载条件下高铝粉含量丁羟复合推进剂燃烧性能试验研究 [C ] //中国宇航学会固体火箭推进专业委员会第38届学术年会论文集.遵义 , 贵州 : 中国宇航学会 , 2021 : 494 - 500 .

HE Y , LI J W , TIAN Z L , et al . Experimental study on the combustion performance of high aluminum content HTPB composite propellants under overload conditions [C ] //Proceedings of the 38th Academic Annual Meeting of the Solid Rocket Propulsion Professional Committee of the Chinese Aerospace Society. Zunyi , Guizhou : Chinese Aerospace Society , 2021 : 494 - 500 .

万章吉 , 商晨燕 , 曹泰岳 . 加速度对固体发动机内弹道性能影响的实验研究 [J ] . 固体火箭技术 , 1991 ( 3 ): 24 - 30 .

WAN Z J , SHANG C Y , CAO T Y . Experimental study on the influence of acceleration on internal ballistic performance of solid motor [J ] . Solid Rocket Technology , 1991 ( 3 ): 24 - 30 . (in Chinese)

Views

540

下载量

CNKI被引量

Alert me when the article has been cited

提交

Tools

Publicity Resources

An Ranging Airburst Correction Algorithm Based on Equivalent Lead

A Multi-gunpowder Adaptive Tailstock Forward-throwing Technology Based on Pressure Difference Separation

Research on Interior Ballistics Stability of Small-caliber Recoilless Gun with High Muzzle Velocity of Projectile

Interior Ballistic Performance of High-loading-density Modular Charge Based on Sequential Loading

Thermal Interaction Mechanisms of Black Powders with Different Particle Sizes and Cellulose as Packing Material during Ignition

Related Author

Qiusheng LIU

Yong LI

Feiyang MENG

Dongchen TIAN

Yuxing GUO

Meng WANG

Wenqi LIN

Qingchun CUI

Related Institution

Northwest Institute of Mechanical and Electrical Engineering

School of Mechanical and Electrical Engineering, North University of China

Chongqing Jianshe Industry (Group) Co., Ltd.

Chongqing Jialing Special Equipment Co., Ltd.

Postal code：100089
Tel：010-68963060/68962718 Fax：010-68963025 Email：bgxb@cos.org.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备05059581号-4 京公网安备11010802024360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.
Total Visits：44495 Visits Today：475

⁰