催化床结构对HAN基单组元发动机性能的影响

doi:10.7527/S1000-6893.2023.29818

Abstract

Abstract:

The influence of catalyst bed length and cavity defects on the engine operation process was investigated for a Hydroxylamine Nitrate （HAN）-based monopropellant engine. Numerical simulations were conducted to examine the steady-state operation and startup process of a 300 N engine using porous media assumption， the Volume of Fluid （VOF） model， and the propellant decomposition model. The results indicate that increasing the length of the front bed contributes to performance improvement. By increasing the front bed length from 30 mm to 40 mm， the specific impulse in vacuum is enhanced by 2.7%. However， increasing the length of the front bed leads to a slower response. This not only reduces the pressure and temperature values at the end of the gas filling stage by 6.7% and 12.5% respectively， but also increases the pressurization time caused by the catalyst bed heating. Cavity defects significantly reduce engine performance. When the front bed length is 40 mm， the 5 mm cavity reduces the vacuum specific impulse by 15%.

Key words: hydroxylamine nitrate, catalytic bed structure, liquid-monopropellant rocket engine, stead-state process, start-up process

CLC Number:

V434

Dechuan SUN, Guoqiang ZHANG, Tianliang YAO, Liang GUAN. Influence of catalyst bed structure on performance of HAN⁃based monopropellant engine[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(16): 129818-129818.

Figures/Tables 19

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Table 1

Table 2

Fig.6

Fig.7

Fig.8

Fig.9

Table 3

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

References 28

1	周汉申. 单组元液体火箭发动机设计与研究［M］. 北京：中国宇航出版社， 2009.
	ZHOU H S. Design and research of single-component liquid rocket engine［M］. Beijing： China Aerospace Press， 2009 （in Chinese）.
2	赵许群，王晓东，夏连根，等. 单推-3推进剂催化分解性能研究［C］∥全国催化学术会议， 2002.
	ZHAO X Q， WANG X D， XIA L G，et al. Research on the Catalytic Decomposition Performance of DT-3 Propellant［C］∥National Academic Conference on Catalysis， 2002 （in Chinese）.
3	湛建阶，陈朝辉. 肼类分解催化剂研究进展［J］. 材料导报， 2007， 21（2）： 62-66， 71.
	ZHAN J J， CHEN Z H. Progress in research on hydrazine decomposition catalysts［J］. Materials Review， 2007， 21（2）： 62-66， 71 （in Chinese）.
4	JING L Y， YOU X Q， HUO J L， et al. Experimental and numerical studies of ammonium dinitramide based liquid propellant combustion in space thruster［J］. Aerospace Science and Technology， 2017， 69： 161-170.
5	刘建国，安振涛，张倩，等. 硝酸羟胺的热稳定性评估及热分解机理研究［J］. 材料导报， 2017， 31（4）： 145-152.
	LIU J G， AN Z T， ZHANG Q， et al. Thermal stability evaluation and thermal decomposition mechanism of hydroxylamine nitrate［J］. Materials Review， 2017， 31（4）： 145-152 （in Chinese）.
6	鲍立荣，汪辉，陈永义，等. 硝酸羟胺基绿色推进剂研究进展［J］. 含能材料， 2020， 28（12）： 1200-1210.
	BAO L R， WANG H， CHEN Y Y， et al. Review on hydroxylammonium nitrate based green propellant［J］. Chinese Journal of Energetic Materials， 2020， 28（12）： 1200-1210 （in Chinese）.
7	KATSUMI T， HORI K. Successful development of HAN based green propellant［J］. Energetic Materials Frontiers， 2021， 2（3）： 228-237.
8	AGNIHOTRI R， OOMMEN C. Cerium oxide based active catalyst for hydroxylammonium nitrate （HAN） fueled monopropellant thrusters［J］. RSC Advances， 2018， 8（40）： 22293-22302.
9	FOUST J. Clogged propellant lines doomed NASA lunar cubesat mission［EB/OL］. （2023-8-10）［2023-11-01］. .
10	LEMMER K. Propulsion for CubeSats［J］. Acta Astronautica， 2017， 134： 231-243.
11	TUMMALA A R， DUTTA A. An overview of cube-satellite propulsion technologies and trends［J］. Aerospace， 2017， 4（4）： 58.
12	白梅杉，於希乔，陆文杰，等. 硝酸羟胺发动机喷注器特种流量分配方法［J］. 火箭推进， 2023， 49（5）： 99-106.
	BAI M S， YU X Q， LU W J， et al. Injector flow distribution method of a hydroxylamine nitrate thruster［J］. Journal of Rocket Propulsion， 2023， 49（5）： 99-106 （in Chinese）.
13	LIN Q G， LIU C， LIU J. Development on HAN-based monopropellant thruster： Space Propulsion［C］∥Space Propulsion Conference 2014， 2014.
14	姚天亮，郭曼丽，戴佳，等. 新型弹簧床结构的HAN基发动机技术［J］. 宇航学报， 2019， 40（4）： 444-451.
	YAO T L， GUO M L， DAI J， et al. HAN-based thruster technology with a new spring bed structure［J］. Journal of Astronautics， 2019， 40（4）： 444-451 （in Chinese）.
15	白梅杉，戴佳，姚天亮，等. HAN基无毒单元发动机常温启动技术研究［J］. 宇航总体技术， 2019， 3（2）： 36-43.
	BAI M S， DAI J， YAO T L， et al. Research of HAN-based green monopropellant thruster start under normal temperature［J］. Astronautical Systems Engineering Technology， 2019， 3（2）： 36-43 （in Chinese）.
16	刘川，赵峰，刘俊. HAN基无毒单组元1 N发动机设计研究［J］. 上海航天， 2016， 33（4）： 32-37.
	LIU C， ZHAO F， LIU J. Research on HAN-based green 1 N monopropellant thruster［J］. Aerospace Shanghai， 2016， 33（4）： 32-37 （in Chinese）.
17	WADA A， WATANABE H， TAKEGAHARA H. Combustion characteristics of a hydroxylammonium-nitrate-based monopropellant thruster with discharge plasma system［J］. Journal of Propulsion and Power， 2018， 34（4）： 1052-1060.
18	刘昌国，关亮，施伟，等. 单组元300N发动机低温试验研究［J］. 推进技术， 2021， 42（7）： 1662-1670.
	LIU C G， GUAN L， SHI W， et al. Low temperature experimental research on mono-propellant 300N engine［J］. Journal of Propulsion Technology， 2021， 42（7）： 1662-1670 （in Chinese）.
19	ZHOU X， HITT D. Numerical modeling of monopropellant decomposition in a micro-catalyst bed［C］∥ 35th AIAA Fluid Dynamics Conference and Exhibit. Reston： AIAA， 2005.
20	李岩. ADN推进器的工作过程仿真及结构参数优化设计研究［D］. 北京：北京交通大学， 2014.
	LI Y. Simulation of work process and optimization design of structure parameters of ADN thruster［D］.Beijing： Beijing Jiaotong University， 2014 （in Chinese）.
21	张涛，李国岫，虞育松，等. 基于1N级ADN推力器结构参数优化的仿真研究［J］. 载人航天， 2015， 21（3）： 309-314.
	ZHANG T， LI G X， YU Y S， et al. Simulation study on structural parameter optimization of ADN thruster［J］. Manned Spaceflight， 2015， 21（3）： 309-314 （in Chinese）.
22	郭堂松. HAN基单组元推力器结构参数优化设计的仿真研究［D］. 北京：北京交通大学， 2021.
	GUO T S. Simulation study on optimization design of structural parameters of HAN-based single component thruster［D］.Beijing： Beijing Jiaotong University， 2021 （in Chinese）.
23	蒋耀东，徐全勇，马玉林，等. 肼基单组元火箭发动机的动态响应［J］. 航空学报， 2023， 44（21）： 529170.
	JIANG Y D， XU Q Y， MA Y L，et al. Dynamic response study of hydrazine-based Monocomponent Rocket Engine［J］. Acta Aeronautica et Astronautica Sinica， 2023， 44（21）： 529170.
24	SUN D C， XIANG W B. Simplified numerical simulation model for hydroxyl ammonium nitrate-based monopropellant rocket engines［J］. Aerospace Science and Technology， 2019， 95： 105474.
25	SUN D C， LIU J， XIANG W B. Numerical simulation of the transient process of monopropellant rocket engines［J］. Aerospace Science and Technology， 2020， 103： 105921.
26	孙得川，姚天亮. 硝酸羟胺基单组元液体火箭发动机起动过程的模拟［J］. 推进技术， 2020， 41（1）： 58-64.
	SUN D C， YAO T L. Simulation of start-up transient process for hydroxylamine nitrate-based liquid monopropellant rocket engine［J］. Journal of Propulsion Technology， 2020， 41（1）： 58-64 （in Chinese）.
27	LIU X D， OSHER S， CHAN T. Weighted essentially non-oscillatory schemes［J］. Journal of Computational Physics， 1994， 115（1）： 200-212.
28	SHU C W. High-order finite difference and finite volume WENO schemes and discontinuous Galerkin methods for CFD［J］. International Journal of Computational Fluid Dynamics， 2003， 17（2）： 107-118.

燃气成分	质量分数	摩尔分数
CO₂	0.130 600	0.056 484
H₂O	0.525 700	0.555 781
N₂	0.304 300	0.206 815
H₂	0.016 296	0.155 056
NH₃	0.023 104	0.025 863

位置	粒径/mm	孔隙率	黏性阻力系数/m^-2	惯性阻力系数/m^-1
前床	1.56	0.320	8.675×10⁸	46 499.250
后床	2.7	0.345	2.12×10⁸	20 473.610
隔板		0.454	3.3×10⁷	5 365.085

仿真条件	前床长度/mm	后床长度/mm	催化床初温/K
工况1*	30	26	403
工况2	30	26	383
工况3	30	26	423
工况4	40	16	403
工况5	40	26	403

[1]	. Study on cryogenic fluid labyrinth sealing characteristics considering cavitation effect [J]. Acta Aeronautica et Astronautica Sinica, 0, (): 0-0.
[2]	. The starting and operating characteristics of the precooled supersonic ejector [J]. Acta Aeronautica et Astronautica Sinica, 0, (): 0-0.
[3]	Guangxu WANG, Baoe YANG, Yonghua TAN, Yushan GAO, Bin LI. Randomness of high frequency longitudinal combustion instability in liquid rocket engines [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(14): 129485-129485.
[4]	Huibo WU, Anlong YANG, Feng ZHANG, Baoe YANG, Junkai LIAN, Chenglong TANG. Effects of back pressure on atomization characteristics of impinging jet injector [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529213-529213.
[5]	Yonghua TAN. Research progress in high thrust liquid oxygen methane rocket engine technology [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529690-529690.
[6]	Ruida CHEN, Xiachao CHEN, Hongyu CHEN, Hui XU, Xin HONG. Ignition characteristics and exhaust experiment of 120 N engine at simulated high lunar temperature [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529112-529112.
[7]	Penggang MU, Binchao LI, Jun WANG, Shaowei SONG, Hanyang SHI. Research progress on structural strength of liquid rocket engine during engineering development phase [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529065-529065.
[8]	Feng ZHANG, Yi SUN, Shuai SHANG, Baoe YANG. High pressure combustion experiment for hypergolic propellant unlike doublet injectors [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529507-529507.
[9]	Yushan GAO, Song YAN, Zhiwei ZHANG. Precise engine displacement testing technique based on stereo vision and circular mark points [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 528826-528826.
[10]	Guangxu WANG, Bin LI, Yonghua TAN, Yushan GAO. High frequency combustion instability in liquid rocket engines: Review [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529450-529450.
[11]	Meng DONG, Lixiang XING, Haohai XU. Self⁃excited oscillation and stability of flow regulator pipeline system [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(11): 529427-529427.
[12]	Qiyu ZHOU, Jiaqi ZHANG. Observation on ignition process in small rocket thruster fueled by gaseous oxygen and gaseous methane [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(8): 128876-128876.
[13]	Weiguo ZHAO, Huanhuan QIANG, Xingguo LI. Effect of annular nozzle breadth on cavitation characteristics of high⁃speed inducer [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4): 128730-128730.
[14]	Ziguang LI, Peng CHENG, Qinglian LI, Xiao BAI, Pengjin CAO. Influence of backpressure on spray distribution characteristics of a gas-liquid pintle injector element [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 128614-128614.
[15]	Zehao CHEN, Hui CHEN, Yushan GAO, Hang ZHANG. Review and prospect of model-based fault diagnosis technology for liquid rocket engines [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(23): 629016-629016.

Influence of catalyst bed structure on performance of HAN⁃based monopropellant engine

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 19

References 28

Related Articles 15

Recommended Articles

Metrics

Comments