Research on the Effect of Delayed Igniter and Motor Throat Diameter Gap on Ignition Characteristics

JING Shibo; ZHENG Jian; LI Jiamin

doi:10.15892/j.cnki.djzdxb.2023.01.005

Journal of Projectiles, Rockets, Missiles and Guidance >

2023 , Vol. 43 >Issue 1: 32 - 40

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2023.01.005

Research on the Effect of Delayed Igniter and Motor Throat Diameter Gap on Ignition Characteristics

JING Shibo ,
ZHENG Jian ,
LI Jiamin

Expand

School of Mechanical Engineering, Nanjing University of Science and Technology,Nanjing 210094, Jiangsu, China

Received date: 2022-05-10

Online published: 2025-02-01

Fold

Abstract

In order to meet the demand of delayed ignition of gun-launched missile engine, a simple extended ignition structure is adopted for a type. By applying different sizes of delayed body structures, the flow field characteristics inside the ignition of solid rocket launchers with different throat diameter gaps are numerically simulated. A propellant additive combustion model is established and the pressure distribution in the internal flow field of the engine is calculated from the start of ignition to the escape of the extended body structure. A 6DOF dynamic mesh model was used to simulate the internal flow field characteristics during the moment when the extension structure escapes from the nozzle. The results show that the smaller the gap is, the more violent the transient changes in the internal flow field of the engine, and the longer the time to reach the specified extended body escape pressure; during the escape process, strong pressure oscillations occur when the extended body structure reaches the nozzle throat at the head end, and the smaller the gap is, the more violent the oscillations are.

Key words： gun-launched missile; delayed igniter; throat diameter gap; ignition transient characteristics

Cite this article

JING Shibo , ZHENG Jian , LI Jiamin . Research on the Effect of Delayed Igniter and Motor Throat Diameter Gap on Ignition Characteristics[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2023 , 43(1) : 32 -40 . DOI: 10.15892/j.cnki.djzdxb.2023.01.005

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within

[1]	屠小昌, 张春英, 万东, 等. 大长细比小型固体发动机后点火试验研究[J]. 固体火箭技术, 2001, 24(1): 68-72. TU X C, ZHANG C Y, WAN D, et al. Experimental investigation of aft end ignition for high slenderness ratio and small size solid motor[J]. Journal of Solid Rocket Technology, 2001, 24(1): 68-72.

[2]	李海涛, 鲍福廷. 固体火箭发动机点火过程内弹道计算[J]. 弹箭与制导学报, 2008, 28(5): 152-154. LI H T, BAO F T. Ignition transient interior ballistic calculation of solid rocket motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2008, 28(5): 152-154.

[3]	孟亮飞, 田发林, 周长省. 阶梯装药固体火箭发动机点火内流场特性研究[J]. 弹箭与制导学报, 2010, 30(5): 127-130. MENG L F, TIAN F L, ZHOU C S. The study on ignition interior flow field characteristics of ladder-shaped propellant solid rocket motor.[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010, 30(5): 127-130.

[4]	宋大明, 周长省. 固体火箭发动机瞬态内流场数值仿真[J]. 弹箭与制导学报, 2010, 30(6): 147-149. SONG D M, ZHOU C S. Numerical simulation of transient internal flowfields in solid rocket motor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2010, 30(6): 147-149.

[5]	刘赟, 王浩, 陶如意, 等. 点火过程对小型固体火箭发动机内弹道影响[J]. 含能材料, 2013, 21(1): 75-79. LIU Y, WANG H, TAO R Y, et al. Effects of ignition process on the internal ballistics of small-size solid rocket motor[J]. Chinese Journal of Energetic Material, 2013, 21(1): 75-79.

[6]	张明, 涂四华, 邢一星, 等. 微小型固体火箭发动机点火效率影响研究[J]. 弹箭与制导学报, 2015, 35(5): 92-94. ZHANG M, TU S H, XING Y X, et al. Research of impact on micro solid rocket motor ignition efficiency[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2015, 35(5): 92-94.

[7]	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 J, GAO T Y, GAO P Q, et al. Simulation of inner flow fields at end of burning in a SRM[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018, 38(3): 58-62.

[8]	周柏航, 王浩, 齐治. 点火药盒开孔大小对点火燃气内流场特性影响[J]. 弹道学报, 2021, 33(2): 78-84. DOI ZHOU B H, WANG H, QI Z. Influence of ignition cartridge opening-size on inner flow-field characteristics of ignition gas[J]. Journal of Ballistics, 2021, 33(2): 78-84.

[9]	郑凌轩, 余陵, 相翠玲. 不同环境温度下的点火瞬态过程数值模拟[J]. 兵器装备工程学报, 2021, 42(6): 96-100. ZHENG L X, YU L, XIANG C L. Numerical simulation of transient ignition process based on different ambient temperature[J]. Journal of Ordnance Equipment Engineering. 2021, 42(6): 96-100.

[10]	夏定国, 许桂阳, 魏志军, 等. 点火药量对双脉冲固体火箭发动机点火过程影响[J]. 航空动力学报, 2022, 37(2): 433-442. XIA D G, XU G Y, WEI Z J, 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.

[11]	钟涛. 大长径比固体火箭发动机点火瞬态过程研究[D]. 长沙: 国防科学技术大学, 2005. ZHONG T. Investigation of the ignition transient in large aspect ratio solid rocket motors[D]. Changsha: National University of Defense Technology, 2005.

[12]	MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605.

[13]	张端庆. 固体火箭推进剂[M]. 北京: 兵器工业出版社, 1991. ZHANG D Q. Solid rocket propellant[M]. Beijing: The Publishing House of Ordnance Industry, 1991.

[14]	陈军涛, 蹇泽群, 陈林泉. 固体火箭发动机点火瞬时内流场轴对称数值分析[J]. 固体火箭技术, 2004, 27(3): 173-176. CHEN J T, JIAN Z Q, CHEN L Q. Axisymmetric numerical analysis for ignition transient interior flow field of SRMs[J]. Journal of Solid Rocket Technology, 2004, 27(3): 173-176.

[15]	CHOI H, BAEK S W. A numerical simulation of axisymmetric solid rocket motor ignition transient with radiation effect[J]. Journal of Propulsion and Power, 1996, 16(4): 725-728.

Options

Outlines