两相流对固体火箭发动机塞式喷管性能的影响

doi:10.7527/S1000-6893.2022.27890

Abstract

Abstract:

To study the effect of gas-solid two-phase flow on performance of the plug nozzle in solid rocket motor， the two-phase flow field of annular plug nozzle was calculated by particle track model， the movement track of particles in flow field was identified， the influence of different particle sizes on flow field and thrust performance of nozzle was analyzed. Combined with traditional bell nozzle， the thrust performance of plug nozzle and bell nozzle under different working conditions was compared， the influence of gas-solid two-phase flow on the height compensation characteristics of plug nozzle was analyzed. The results show that with the increase of particle size， the particles will appear staggered motion， which increases the complexity of the flow field. And there is only one collision between a single particle and the truncated plug， and the larger the particle size， the more advanced the collision position. The thrust performance loss caused by single particle size is proportional to particle size and inversely proportional to working pressure ratio. Under real working conditions， compared with bell nozzle， gas-solid two-phase flow brings about 3% more thrust efficiency loss to plug nozzle in the design condition， and thrust efficiency eventually tend to be weaker than the bell nozzle at 2.7%， but plug nozzle still has considerable performance advantage in low pressure ratio condition.

Key words: rocket nozzles, annular plug nozzles, altitude compensated, two?phase flow, solid rocket motor

CLC Number:

V430

Hongjin LI, Junwei LI, Kan XIE, Xiang LI, Zheng YANG, Ningfei WANG. Effect of two-phase flow on performance of plug nozzle in solid rocket motor[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(16): 127890-127890.

Figures/Tables 22

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Table 1

Table 2

Fig.6

Table 3

Fig.7

Fig.8

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Table 4

Fig.15

Fig.16

Fig.17

Fig.18

References 24

1	王长辉，刘宇. 塞式喷管在固体火箭发动机上的应用研究［J］. 固体火箭技术， 2005， 28（1）： 36-39， 56.
	WANG C H， LIU Y. Application study of plug nozzles for solid rocket motors［J］. Journal of Solid Rocket Technology， 2005， 28（1）： 36-39， 56 （in Chinese）.
2	SCHNABEL M C， BROPHY C M. Pressure distribution and performance impacts of aerospike nozzles on rotating detonation engines［C］∥2018 AIAA Aerospace Sciences Meeting. Reston： AIAA， 2018.
3	ROMMEL T， HAGEMANN G， SCHLEY C A， et al. Plug nozzle flowfield analysis［J］. Journal of Propulsion and Power， 1997， 13（5）： 629-634.
4	刘亚洲，李平，杨建文. 液体火箭发动机喷管流动特性及高度补偿研究进展［J］. 推进技术， 2022， 43（1）： 14-33.
	LIU Y Z， LI P， YANG J W. Progress of flow characteristics and altitude compensation in liquid rocket engine nozzle［J］. Journal of Propulsion Technology， 2022， 43（1）： 14-33 （in Chinese）.
5	CIEPLUCH C， KRULL H， STEFFEN F W. Preliminary investigation of performance of variable-throat extended-plug-type nozzles over wide range of nozzle pressure ratios： Technical Report Archive & Image Library［R］. Washington， D.C.： National Advisory Committee For Aeronautics， 1954.
6	RAO G V R. Analysis of a new concept rocket nozzle［M］∥Liquid rockets and propellants. Reston： AIAA， 1960： 669-682.
7	HALL C， PANOSSIAN H. X-33 attitude control using the XRS-2200 linear aerospike engine［C］∥35th Joint Propulsion Conference and Exhibit. Reston： AIAA， 1999.
8	琚春光，陈风雨，王国辉. 高度补偿喷管发动机在运载火箭上的应用［J］. 导弹与航天运载技术， 2011， 315（5）： 20-23.
	JU C G， CHEN F Y， WANG G H. Application of aerospike nozzle engine in launch vehicles［J］. Missiles and Space Vehicles， 2011， 315（5）： 20-23 （in Chinese）.
9	任军学，肖建军，刘宇，等. 塞式喷管对固体导弹性能的增益［C］∥中国宇航学会运载系统专业委员会学术交流会. 北京：中国宇航学会， 2005： 213-219.
	REN J X， XIAO J J， LIU Y， et al. Gain of plug nozzles on solid missile performance［C］∥Academic Exchange of Transport System Committee. Beijing： Chinese Society of Astronautics， 2005： 213-219 （in Chinese）.
10	任军学，刘宇，覃粒子. 环簇式塞式喷管在固体火箭发动机上应用探讨［J］. 固体火箭技术， 2005， 28（3）： 184-187.
	REN J X， LIU Y， QIN L Z. Application of annular clustered plug nozzle to solid rocket motor［J］. Journal of Solid Rocket Technology， 2005， 28（3）： 184-187 （in Chinese）.
11	谢侃，刘宇，任军学，等. 两相流环缝塞式喷管设计方法［J］. 航空学报， 2007， 28（6）： 1339-1344.
	XIE K， LIU Y， REN J X， et al. Design methods of two-phase axial plug nozzle［J］. Acta Aeronautica et Astronautica Sinica， 2007， 28（6）： 1339-1344 （in Chinese）.
12	任军学，刘宇，谢侃. 固体火箭发动机塞式喷管两相流场与性能分析［J］. 航空学报， 2007， 28（增）： 23-27.
	REN J X， LIU Y， XIE K. Two-phase flow field in plug nozzle of solid rocket motor and its performance analysis［J］. Acta Aeronautica et Astronautica Sinica， 2007， 28（Sup.）： 23-27 （in Chinese）.
13	琚春光，刘宇，王长辉，等. 塞式喷管二次喷射推力矢量控制研究［J］. 推进技术， 2009， 30（1）： 67-71.
	JU C G， LIU Y， WANG C H， et al. A study for thrust vector control of aerospike nozzle based on second injection［J］. Journal of Propulsion Technology， 2009， 30（1）： 67-71 （in Chinese）.
14	陈涛，刘宇，程诚，等. 固体火箭发动机塞式喷管结构型式与性能分析［J］. 固体火箭技术， 2011， 34（2）：156-160.
	CHEN T， LIU Y， CHENG C， et al. Structure type and performance analysis of aerospike nozzle of solid rocket motor［J］. Journal of Solid Rocket Technology， 2011， 34（2）：156-160 （in Chinese）.
15	李修明，王一白，童悦，等. 固体火箭发动机推力可调塞式喷管数值模拟与冷流试验［J］. 上海航天， 2019， 36（）： 29-34.
	LI X M， WANG Y B， TONG Y， et al. Numerical simulation and cold-flow test of adjustable thrust solid plug nozzle［J］. Aerospace Shanghai， 2019， 36（S1）： 29-34 （in Chinese）.
16	CAUBET P， BERDOYES M. Innovative ArianeGroup controllable solid propulsion technologies［C］∥AIAA Propulsion and Energy 2019 Forum. Reston： AIAA， 2019.
17	HA D S， KIM J J， KIM H J. Dynamic characteristics of the aerospike-shaped pintle nozzle for variable thrust［C］∥AIAA Propulsion and Energy 2019 Forum. Reston： AIAA， 2019.
18	ANGELINO G. Approximate method for plug nozzle design［J］. AIAA Journal， 1964， 2（10）： 1834-1835.
19	淡林鹏，张振鹏，赵永忠，等. 长尾喷管中粒子运动轨迹的数值模拟［J］. 航空动力学报， 2003， 18（2）： 258-263.
	DAN L 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）.
20	GURRIS M， KUZMIN D， TUREK S. Finite element simulation of compressible particle-laden gas flows［J］. Journal of Computational and Applied Mathematics， 2010， 233（12）： 3121-3129.
21	李平，肖良华，何卫锋，等. 收缩-扩张喷管内气固两相流运动规律研究［J］. 工程力学， 2018， 35（12）： 240-247.
	LI P， XIAO L H， HE W F， et al. Research on movement law of gas-solid two-phase flow in convergent-divergent nozzle［J］. Engineering Mechanics， 2018， 35（12）： 240-247 （in Chinese）.
22	穆旭. 固体火箭发动机喷管两相流仿真与型面优化研究［D］. 西安：航天动力技术研究院， 2021.
	MU X. Study on simulation of two-phase flow and profile optimization of solid rocket motor nozzle［D］. Xi'an： Academy of Aerospace Solid Propulsion Technology， 2021 （in Chinese）.
23	BUI T， MURRAY J， ROGERS C， et al. Flight research of an aerospike nozzle using high power solid rockets［C］∥41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston： AIAA， 2005.
24	张宏安，叶定友. 固体火箭发动机喷管凝相粒子尺寸分布研究［C］∥第五届海内外华人航天科技研讨会. 西安：中国宇航学会， 2004： 407-412.
	ZHANG H A， YE D Y. Study on particle size distribution of solid rocket motor nozzle［C］∥The 5th Symposium on Space Science and Technology for Chinese at Home and Abroad. Xi’an： Chinese Society of Astronautics， 2004： 407-412 （in Chinese）.

型面参数	数值	型面参数	数值
收敛比	3	喉部长度/m	0.01
扩张比	52	扩张段长度/m	1.104 9
喉径/m	0.163	初始扩张半角/（°）	29
出口直径/m	1.175 4	出口半角/（°）	17
收敛段长度/m	0.097 8

喷管	燃烧室平均压强/MPa	文献试验结果/N	本文仿真结果/N	误差/%
Aerospike 1	2.18	3 613.40	3 620.53	0.2
Aerospike 3	1.92	3 282.32	3 126.86	4.7

海拔/km	推力效率损失率（钟形）/%			推力效率损失率（塞式）/%
海拔/km	-1 μm	-10 μm	-50 μm	-1 μm	-10 μm	-50 μm
0	7.6	10.5	13.2	9.8	15.0	16.5
5	7.2	10.0	13.7	9.3	15.0	16.4
10	6.9	9.5	13.0	8.5	13.7	15.9
15	6.5	9.0	12.4	8.2	13.1	15.2
20	6.3	8.7	12.0	7.8	12.6	14.6
25	6.1	8.4	11.6	7.6	12.2	14.1
30	6.0	8.2	11.3	7.4	11.9	13.8

[1]	Jianjun WU, Zejun HU, Zhicheng HE, Yu ZHANG, Yang OU, Zhengxue MA, Qinhui PENG, Yuxuan ZHONG. Research progress of electrically controlled solid propulsion technology [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(15): 528716-528716.
[2]	LI Yingkun, HAN Junli, CHEN Xiong, ZHOU Changsheng, GONG Lunkun. Numerical simulation of the ignition transient of dual pulse motor based on multi-physics coupling [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(4): 120409-120409.
[3]	YU Jiaquan, XU Jinsheng, CHEN Xiong, ZHOU Changsheng, JIA Deng, LI Hongwen. Rate-dependent property of propellant and inhibitor interface debonding [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(12): 3861-3867.
[4]	Xiong Wenbo;Liu Yu;Ren Junxue;Zhang Xiaoguang. Generalized Burning Surface Calculation of Three Dimensional Propellant Based on Element Method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(7): 1176-1180.
[5]	Wang Songbai. DISTRIBUTION OF THE PARTICLE DIAMETERS IN THE JET EXHAUST OF SOLID ROCKET MOTOR [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1990, 11(12): 606-609.
[6]	Wang Jiayun;Zhan Zhangpeng and Qu Ziqiang . THE INTEGRATED DESIGN OF MISSILE WITH SOLID ROCKET -RAMJET COMBINATION [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1988, 9(2): 25-34.

Effect of two-phase flow on performance of plug nozzle in solid rocket motor

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 22

References 24

Related Articles 6

Recommended Articles

Metrics

Comments