耦合尾喷管堵盖运动的水下固体火箭发动机点火启动过程特性

doi:10.12382/bgxb.2022.0136

摘要/Abstract

摘要：

为研究水下固体火箭发动机点火启动过程的流场特征与工作特性,对尾喷管堵盖分离约束下的点火燃气泡演化过程进行数值模拟。采用流体体积多相流模型与动网格技术,建立耦合喷管堵盖运动的水下燃气射流仿真模型。对点火初期燃气泡形貌瞬态演化和流场参数的振荡特性进行分析,揭示变深度下发动机点火的初始推力脉动特征及形成机制。研究结果表明:点火开盖初期压差驱动堵盖强烈地冲击液相,尾壁空间产生高压区形成初始推力峰;点火深度越深,燃气泡沿轴向的增长速度越慢、长度越短,颈部出现收缩时刻越提前,流场参数和发动机推力的脉动特性越强;深水下燃气泡颈部收缩后,发动机喷口激波系出现往复振荡,导致尾壁空间产生压力振荡形成多个脉动推力峰,激波系的不稳定运动是推力出现脉动的主导因素。

关键词: 固体火箭发动机, 水下点火, 激波运动, 压力振荡, 推力脉动

Abstract:

To investigate the flow field and working characteristics of the underwater solid rocket motor at the initial stage of ignition, the gas bubble evolution process under the constraint of nozzle closure separation is numerically simulated. Based on the VOF multiphase model and dynamic mesh technique, a numerical model of underwater gas jet with the effect of nozzle closure is established. The transient evolution of gas bubble morphology and the oscillation characteristics of flow field parameters are analyzed. The characteristics and formation mechanism of initial thrust pulsation after ignition at variable depths are revealed. The results show that: at the initial stage of nozzle opening, the pressure difference drives the closure to strongly impact the liquid phase, causing a high pressure zone in the tail wall space and the formation of an initial thrust peak; as the ignition depth increases, the axial growth rate is slower and the length becomes shorter, the gas bubble has neck contraction in advance, and the pulsation characteristics of the flow field parameters and thrust of the motor become stronger; at the initial stage of ignition in deep water, the shock wave near nozzle exit has reciprocating oscillations, and the pressure oscillation in the tail wall space forms multiple fluctuating thrust peaks. It is demonstrated that the unstable motion of shock waves is the leading factor of thrust pulsation.

Key words: solid rocket motor, underwater ignition, shock wave motion, pressure oscillation, thrust pulsation

王德友, 李世鹏, 金戈, 王茹瑶, 官典, 王宁飞. 耦合尾喷管堵盖运动的水下固体火箭发动机点火启动过程特性[J]. 兵工学报, 2023, 44(6): 1665-1676.

WANG Deyou, LI Shipeng, JIN Ge, WANG Ruyao, GUAN Dian, WANG Ningfei. Characteristics of Ignition Start-up Process of Underwater Solid Rocket Motor with the Effect of Nozzle Closure[J]. Acta Armamentarii, 2023, 44(6): 1665-1676.

图/表 20

图1 水下固体火箭发动机推力计算示意

Fig.1 Calculation of thrust of underwater solid rocket motor

图2 计算域及边界条件

Fig.2 Computational domain and boundary conditions

图3 网格划分

Fig.3 Meshing

图4 网格无关性分析

Fig.4 Mesh independence analysis

表1 仿真工况

Table 1 Simulation conditions

工况	点火深度/m	环境压力/MPa	破盖压力/MPa
1	10	0.2	3.2
2	50	0.6	3.6
3	90	1.0	4.0

图5 高压水箱实验系统[21]

Fig.5 High pressure tank experimental system[21]

表2 数值仿真与射流实验对比

Table 2 Comparison of numerical and experimental results

图6 射流长度变化规律对比

Fig.6 Comparison of variation law of jet length

表3 不同点火深度的燃气泡演化(上)和马赫数分布(下)

Table 3 Evolution process of gas bubble (above) and contour of Mach number (below) at different ignition depths

图7 不同点火深度的堵盖速度和位移变化

Fig.7 Velocity and displacement curves of nozzle closure at different ignition depths

图8 不同点火深度的发动机推力曲线

Fig.8 Thrust curves of SRM at different ignition depths

图9 深度90m工况发动机推力分量变化

Fig.9 Thrust component curves of SRM at 90m depth

表4 深度90m工况推力峰值时刻流场参数

Table 4 Flow field parameters of peak thrust at 90m depth

图10 压力监测点位置

Fig.10 Locations of pressure monitoring points

图11 点火初期尾壁面压力监测信号

Fig.11 Pressure signals of tail wall at the initial stage of ignition

图12 深度90m工况P0点压力监测信号

Fig.12 Pressure signals of P0 at 90m depth

图13 深度90m工况尾流压力(左)与马赫数(右)分布

Fig.13 Pressure (left) and Mach number (right) distribution at 90m depth

图14 深度90m工况尾壁面压力监测信号

Fig.14 Pressure signals of tail wall at 90m depth

图15 深度90m工况推力脉动特性

Fig.15 Thrust pulsation characteristics at 90m depth

图16 典型时刻轴线流动参数(左)与流场压力分布(右)

Fig.16 Axial flow parameters (left) and pressure distribution (right) of flow field at typical times

参考文献 22

[1]	LOTH E, FAETH G M. Structure of underexpanded round air jets submerged in water[J]. International Journal of Multiphase Flow, 1989, 15(4):589-603. doi: 10.1016/0301-9322(89)90055-4 URL
[2]	LOTH E, FAETH G M. Study of plane under-expanded air jets in water[C]//Proceedings of the AIAA 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference. Buffalo, NY,US:AIAA, 1989.
[3]	TANG J N, WANG N F, SHYY W. Flow structures of gaseous jets injected into water for underwater propulsion[J]. Acta Mechanica Sinica, 2011, 27(4):461-472. doi: 10.1007/s10409-011-0474-4 URL
[4]	施红辉, 王柏懿, 戴振卿. 水下超声速气体射流的力学机制研究[J]. 中国科学: 物理学力学天文学, 2010, 40(1):92-100.
	SHI H H, WANG B Y, DAI Z Q. Research on the mechanics of underwater supersonic gas jets[J]. Science China: Physics, Mechanics & Astronomy, 2010, 40(1):92-100. (in Chinese)
[5]	施红辉, 汪剑锋, 陈帅, 等. 水下超声速气体射流初期流场特性的实验研究[J]. 中国科学技术大学学报, 2014, 44(3):233-237.
	SHI H H, WANG J F, CHEN S, et al. Experimental study on flow characteristics at the initial injection stage of underwater supersonic gas jets[J]. Journal of University of Science and Technology of China, 2014, 44(3):233-237. (in Chinese)
[6]	黄楠, 陈志华, 王争论. 水下超声速气体射流线性稳定性研究[J]. 推进技术, 2021, 42(3):550-559.
	HUANG N, CHEN Z H, WANG Z L. Linear stability of underwater supersonic gas jet[J]. Journal of Propulsion Technology, 2021, 42(3):550-559. (in Chinese)
[7]	ZHANG X Y, LI S P, YANG B Y, et al. Flow structures of over-expanded supersonic gaseous jets for deep-water propulsion[J]. Ocean Engineering, 2020, 213: 107611. doi: 10.1016/j.oceaneng.2020.107611 URL
[8]	张小圆, 李世鹏, 杨保雨, 等. 潜航飞行体深水超音速气体射流的流动稳定性研究[J]. 兵工学报, 2019, 40(12):2385-2398. doi: 10.3969/j.issn.1000-1093.2019.12.001
	ZHANG X Y, LI S P, YANG B Y, et al. Analysis of the flow instability of supersonic gaseous jets for submarine vehicles working in deep water[J]. Acta Armamentarii, 2019, 40(12):2385-2398. (in Chinese) doi: 10.3969/j.issn.1000-1093.2019.12.001
[9]	张小圆, 李世鹏, 杨保雨, 等. 水下固体火箭发动机垂直气体射流结构和推力影响研究[J]. 推进技术, 2021, 42(5):961-969.
	ZHANG X Y, LI S P, YANG B Y, et al. Flow structures of vertical gaseous jets and effects of thrust of underwater solid rocket motor[J]. Journal of Propulsion Technology, 2021, 42(5):961-969. (in Chinese)
[10]	王利利, 刘影, 李达钦, 等. 固体火箭发动机水下超音速射流数值研究[J]. 兵工学报, 2019, 40(6):1161-1170. doi: 10.3969/j.issn.1000-1093.2019.06.006
	WANG L L, LIU Y, LI D Q, et al. Numerical study of underwater supersonic gas jets for solid rocket engine[J]. Acta Armamentarii, 2019, 40(6):1161-1170. (in Chinese) doi: 10.3969/j.issn.1000-1093.2019.06.006
[11]	权晓波, 王占莹, 刘元清, 等. 水环境下喷管流动分离数值研究[J]. 固体火箭技术, 2020, 43(1):8-15.
	QUAN X B, WANG Z Y, LIU Y Q, et al. Numerical simulation research on the flow separation of solid rocket motor in water environment[J]. Journal of Solid Rocket Technology, 2020, 43(1):8-15. (in Chinese)
[12]	许海雨, 罗凯, 黄闯, 等. 通气超空化对水下火箭发动机性能影响[J]. 哈尔滨工业大学学报, 2021, 53(6):41-47.
	XU H Y, LUO K, HUANG C, et al. Influence of ventilated supercavitation on underwater rocket engine[J]. Journal of Harbin Institute of Technology, 2021, 53(6):41-47. (in Chinese)
[13]	乌岳, 李卓, 江晓瑞. 水下点火固体火箭发动机两相流流场数值分析[J]. 航空动力学报, 2018, 33(10):2508-2514.
	WU Y, LI Z, JIANG X R. Numerical analysis for underwater ignition two-phase flow field of solid rocket motor[J]. Journal of Aerospace Power, 2018, 33(10):2508-2514. (in Chinese)
[14]	邹延兵, 卓长飞, 封锋. 火箭发动机水下启动过程流场数值模拟研究[J]. 弹道学报, 2016, 28(4):30-35, 41.
	ZOU Y B, ZHUO C F, FENG F. Numerical simulation of flow field for underwater starting process of rocket engine[J]. Journal of Ballistics, 2016, 28(4):30-35, 41. (in Chinese)
[15]	王晓辉, 张珂, 褚学森, 等. 水下点火推进尾空泡振荡的研究[J]. 船舶力学, 2020, 24(2):136-144.
	WANG X H, ZHANG K, CHU X S, et al. Research on the pressure oscillation process of tail bubble of underwater igniting propulsion[J]. Journal of Ship Mechanics, 2020, 24(2):136-144. (in Chinese)
[16]	汤龙生, 刘宇, 吴智锋, 等. 水下超声速燃气射流气泡的生长及压力波传播特性实验研究[J]. 推进技术, 2011, 32(3):417-420.
	TANG L S, LIU Y, WU Z F, et al. Experimental study on characteristics of bubble growth and pressure wave propagation by supersonic gas jets under water[J]. Journal of Propulsion Technology, 2011, 32(3):417-420. (in Chinese)
[17]	贾有军, 张胜敏, 尤俊峰, 等. 固体发动机水下点火尾流变化过程试验研究[J]. 固体火箭技术, 2015, 38(5):660-663, 678.
	JIA Y J, ZHANG S M, YOU J F, et al. Experimental research on the changing process of underwater ignition wake of solid rocket motor[J]. Journal of Solid Rocket Technology, 2015, 38(5):660-663, 678. (in Chinese)
[18]	张春, 郁伟, 王宝寿. 水下超声速燃气射流的初期流场特性研究[J]. 兵工学报, 2018, 39(5):961-968. doi: 10.3969/j.issn.1000-1093.2018.05.016
	ZHANG C, YU W, WANG B S. Research on the initial flow field characteristics of underwater supersonic gas jets[J]. Acta Armamentarii, 2018, 39(5):961-968. (in Chinese) doi: 10.3969/j.issn.1000-1093.2018.05.016
[19]	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, 2013:16-20.
	TANG J L, LIU P J. Principle of solid rocket motor[M]. Beijing: National Defense Industry Press, 2013:16-20. (in Chinese)
[20]	于邵祯, 姜毅, 周笑飞, 等. 耦合尾喷管堵盖运动的发射箱内流场研究[J]. 兵工学报, 2014, 35(11):1805-1812. doi: 10.3969/j.issn.1000-1093.2014.11.011
	YU S Z, JIANG Y, ZHOU X F, et al. Research on distribution of flow field in launching canister with the effect of nozzle closure[J]. Acta Armamentarii, 2014, 35(11):1805-1812. (in Chinese)
[21]	杨保雨. 水下大深度火箭发动机垂直射流仿真与实验研究[D]. 北京: 北京理工大学, 2019.
	YANG B Y. The numerical simulation and experimental study on vertical gas jet of solid rocket motor in deep water[D]. Beijing: Beijing Institute of Technology, 2019. (in Chinese)
[22]	唐嘉宁, 李世鹏, 王宁飞. 水下固体火箭发动机的负推力现象研究[J]. 固体火箭技术, 2012, 35(3):325-329, 343.
	TANG J N, LI S P, WANG N F. Study on the negative thrust of the underwater solid rocket engines[J]. Journal of Solid Rocket Technology, 2012, 35(3):325-329, 343. (in Chinese)