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

Dingguo XIA; Guiyang XU; Zhijun WEI; Weiqi ZHANG

doi:10.13224/j.cnki.jasp.20210131

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

Rocket Engine | 更新时间：2025-04-07

- Impact of ignition charge on ignition process of dual⁃pulse solid rocket motor
- Journal of Aerospace Power Vol. 37, Issue 2, Pages: 433-442(2022)
- 作者机构：
  
  1.北京理工大学宇航学院，北京 100081
  2.中国兵器工业集团有限公司西安近代化学研究所，西安 710065
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210131
  CLC：
- 稿件说明：
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Dingguo XIA, Guiyang XU, Zhijun WEI, et al. Impact of ignition charge on ignition process of dual⁃pulse solid rocket motor[J]. Journal of Aerospace Power, 2022, 37(2): 433-442.
DOI：

Dingguo XIA, Guiyang XU, Zhijun WEI, et al. Impact of ignition charge on ignition process of dual⁃pulse solid rocket motor[J]. Journal of Aerospace Power, 2022, 37(2): 433-442. DOI： 10.13224/j.cnki.jasp.20210131.

摘要

为了确定第二脉冲点火药量对双脉冲发动机点火过程的影响规律，以某双脉冲固体火箭发动机为模型，采用轴对称非定常Navier⁃Stokes方程和标准

k⁃ε

湍流模型，对第二脉冲点火过程进行了仿真，研究了点火装置工作持续时间和点火燃气流量对于点火延迟的影响。研究结果表明：点火燃气流量相同时，增加点火装置工作持续时间可以有效减小第二脉冲点火延迟，该点火延迟存在一个极限值即最小点火延迟。不同点火燃气流量对应不同的最小点火延迟，点火燃气流量越大，最小点火延迟越小，两者之间存在着负指数关系。在设计第二脉冲点火药量时，自由容积应选取为第一、二脉冲自由容积之和更加合理。

Abstract

In order to find out the impact of ignition charge on ignition process in the second pulse，a model was established.The axisymmetric unsteady Navier⁃Stokes equation and the standard

k⁃ε

turbulence model were used to simulate the second pulse ignition process.Based on that，the impacts of the igniter working duration and ignition gas flow rate on the ignition delay were studied.The results showed that：when the ignition gas flow rate was constant，increasing the igniter working duration can effectively shorten the second pulse ignition delay，and there existed a limit value of the ignition delay，which was defined as the minimum ignition delay.Different ignition gas flow rates corresponded to different minimum ignition delay，and the bigger ignition gas flow rate indicated the smaller minimum ignition delay.The ignition gas flow rate had a negative exponential relationship with the minimum ignition delay.Choosing the free volume as the sum of the first and second pulse free volumes is more reasonable when calculating the second pulse ignition charge.

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references

方家洪 . 固体火箭发动机在航天领域的应用 [J]. 国外导弹与宇航 , 1984 , 7 （ 11 ）: 20 ⁃ 26 .

FANG Jiahong . Application of solid rocket motor in aerospace field [J]. Foreign Missiles and Aerospace ， 1984 , 7 （ 11 ）: 20 ⁃ 26 . （in Chinese）

寇军强 . 固体火箭推进技术发展趋势及关键技术分析 [J]. 弹箭与制导学报， 1999 （ 1 ）: 53 ⁃ 56 .

KOU Junqiang . Development trend and key technology analysis of solid rocket propulsion technology [J]. Journal of Projectiles Rockets Missiles and Guidance ， 1999 （ 1 ）: 53 ⁃ 56 . （in Chinese）

王志健 , 何国强 , 魏祥庚 , 等 . 空空导弹多脉冲固体火箭发动机能量分配优化研究 [J]. 弹箭与制导学报， 2010 , 30 （ 6 ）: 144 ⁃ 146 .

WANG Zhijian , HE Guoqiang , WEI Xianggeng , et al . An investigation of optimizing energy allocation on multi⁃pulse solid rocket motor in airborne misssile [J]. Journal of Projectiles Rockets Missiles and Guidance ， 2010 , 30 （ 6 ）: 144 ⁃ 146 . （in Chinese）

NAUMANN K W ， STADLER L . Double⁃pulse solid rocket motor technology‑applications and technical solutions [R]. AIAA⁃2010⁃6754 , 2010 .

DOMBROWSKI D C ， FREY T J ， NEVRINCEAN A G . Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture : US5675966 [P]. 1997⁃10‑14 .

STADLER L , TROUILLOT P , RIENCKER C , et al . The dual pulse motor for LFK NG [R]. AIAA⁃2006⁃4762 , 2006 .

TROUILLOT P ， AUDRI D ， RUIZ S . Design of internal thermal insulation and structures for the LFK NG double⁃pulse motor [R]. AIAA⁃2006⁃4763 , 2006 .

刘伟凯 , 何国强 , 王春光 . 双脉冲发动机中金属膜片动态与静态打开对比分析 [J]. 推进技术， 2014 , 35 （ 9 ）: 1259 ⁃ 1264 .

LIU Weikai ， HE Guoqiang ， WANG Chunguang . Research on dynamic and static opening of metal diaphragm in double pulse solid rocket motor [J]. Journal of Propulsion Technology ， 2014 ， 35 （ 9 ）: 1259 ⁃ 1264 . （in Chinese）

刘伟凯 , 惠博 . 双脉冲发动机中金属膜片式隔舱设计方法 [J]. 固体火箭技术， 2013 , 36 （ 4 ）: 486 ⁃ 490 .

LIU Weikai ， HUI Bo . Research on designing method of metal diaphragm PSD in double pulse solid rocket motor [J]. Journal of Solid Rocket Technology ， 2013 , 36 （ 4 ）: 486 ⁃ 490 . （in Chinese）

王春光 , 任全彬，田维平 , 等 . 脉冲发动机中金属膜片式隔舱动态破坏过程研究 [J]. 固体火箭技术， 2013 , 36 （ 1 ）: 22 ⁃ 26 .

WANG Chunguang ， REN Quanbin , TIAN Weiping , et al . Research on the process of dynamic failure of metal diaphragm pulse separation device in pulse motor [J]. Journal of Solid Rocket Technology ， 2013 , 36 （ 1 ）: 22 ⁃ 26 . （in Chinese）

谢娜 , 娄永春，孙长宏 , 等 . 某双脉冲发动机燃烧室两相流场数值分析 [J]. 固体火箭技术， 2012 , 35 （ 3 ）: 335 ⁃ 338 .

XIE Na ， LOU Yongchun , SUN Changhong , et al . Numerical analysis of two⁃phase flow in combustion chamber of dual⁃pulse motor [J]. Journal of Solid Rocket Technology ， 2012 , 35 （ 3 ）: 335 ⁃ 338 . （in Chinese）

朱卫兵 , 张永飞 , 陈宏 , 等 . 双脉冲发动机内流场研究 [J]. 弹箭与制导学报， 2012 , 32 （ 1 ）: 114 ⁃ 118 .

ZHU Weibing , ZHANG Yongfei , CHEN Hong , et al . The study of dual⁃pulse solid rocket motor's inner flow field [J]. Journal of Projectiles Rockets Missiles and Guidance ， 2012 , 32 （ 1 ）: 114 ⁃ 118 . （in Chinese）

黄波 , 李映坤 , 陈雄 . 双脉冲发动机Ⅱ脉冲点火瞬态工作特性研究 [J]. 弹道学报， 2019 , 31 （ 4 ）: 68 ⁃ 73,81 .

HUANG Bo , LI Yingkun , CHEN Xiong . Investigation on the pulse Ⅱ ignition transient operation characteristics of dual pulse motor [J]. Journal of Ballistics ， 2019 , 31 （ 4 ）: 68 ⁃ 73,81 . （in Chinese）

汤亮 , 邓康清 , 余小波 . 隔舱式双脉冲发动机第Ⅱ脉冲点火过程数值仿真 [J]. 航空动力学报， 2020 , 35 （ 7 ）: 1541 ⁃ 1548 .

TANG Liang ， DENG Kangqing ， YU Xiaobo . Numerical simulation for the second pulse ignition progress in compartment dual⁃pulse motor [J]. Journal of Aerospace Power ， 2020 , 35 （ 7 ）: 1541 ⁃ 1548 . （in Chinese）

杨春庆 , 魏志军 , 张雷 , 等 . 隔层式多脉冲发动机点火延迟数值仿真研究 [J]. 推进技术， 2014 , 35 （ 4 ）: 514 ⁃ 522 .

YANG Chunqing ， WEI Zhijun ， ZHANG Lei ， et al . Numerical simulation of ignition delay for elastomeric barrier multi⁃pulse solid rocket motor [J]. Journal of Propulsion Technology ， 2014 ， 35 （ 4 ）: 514 ⁃ 522 . （in Chinese）

LUKE G D . A study of the ignition transient in large aspect ratio solid rocket motors [D]. Berkeley，US : University of California ， 1996 .

王元有 . 固体火箭发动机设计 [M]. 北京：国防工业出版社， 1984 .

王玲玲 . 固体火箭发动机点火过程数值分析 [D]. 哈尔滨：哈尔滨工程大学， 2008 .

WANG Lingling . Numerical analysis of solid rocket motor ignition transient [D]. Harbin : Harbin Engineering University ， 2008 . （in Chinese）

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