肼基单组元火箭发动机的动态响应

doi:10.7527/S1000-6893.2023.29170

Abstract

Abstract:

Monocomponent rocket engines are important elements for attitude adjustment and orbit control of space-craft. According to the dynamic response of hydrazine-based monocomponent rocket engine to the change form of inlet flow， a simulation model of propellant flow， decomposition and heat transfer in the thrust chamber of the engine is established， and the numerical simulation and calculation analysis of three different propellant supply modes （steady-state supply， linear supply and pulse supply） of the engine are carried out by using these models. The result is that the temperature at each point of the engine will vary in response to the inlet flow due to the difference in position. The response of pressure， velocity and thrust to changes in inlet flow rate is very rapid， and the overall trend of the three remains synchronized with the trend of inlet flow rate changes. There are spikes in velocity and thrust that are higher than the stable values during the start-up phase in both steady-state and pulse supply， in the steady-state supply， the velocity and thrust spikes are 8.6% and 4.7% higher than the stable value of the start-up phase， respectively， in the pulsed supply， the velocity and thrust spikes are 6.2% and 3.0% higher than the stable value of the start-up phase， respectively， in the first pulse phase， the velocity and thrust spikes are 6.2% and 3.0% higher than the stable value of the start-up phase， respectively， and the second pulse phase， the velocity and thrust spikes are 9.3% and 5.2% higher than the stable value of the start-up phase， respectively.

Key words: hydrazine, dynamic response, propellant supply, thrust, monocomponent rocket engine

CLC Number:

Yaodong JIANG, Quanyong XU, Yulin MA, yao CHENG. Dynamic response of hydrazine⁃based monocomponent rocket engine[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21): 529170-529170.

Figures/Tables 19

Fig.1

Table 1

Table 2

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Fig.7

Fig.8

Table 3

Fig.9

Table 4

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

References 32

1	刘川，刘俊，邱鑫，等. 火星探测器推进系统初步设想［J］. 火箭推进， 2014， 40（2）： 44-48.
	LIU C， LIU J， QIU X， et al. Preliminary design of propulsion system for Mars exploration［J］. Journal of Rocket Propulsion， 2014， 40（2）： 44-48 （in Chinese）.
2	BAKER R S， CASILLAS A R， GUERNSEY C S， et al. Mars science laboratory descent-stage integrated propulsion subsystem： Development and flight performance［J］. Journal of Spacecraft and Rockets， 2014， 51（4）： 1217-1226.
3	HAN D I， HAN C Y， SHIN H D. Empirical and computational performance prediction for monopropellant hydrazine thruster employed for satellite［J］. Journal of Spacecraft and Rockets， 2009， 46（6）： 1186-1195.
4	HOU B L， WANG X D， LI T， et al. Steady-state behavior of liquid fuel hydrazine decomposition in packed bed［J］. AIChE Journal， 2015， 61（3）： 1064-1080.
5	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.
	CHEN J J， CHEN Z H. Progress in research on hydrazine decomposition catalysts［J］. Materials Review， 2007， 21（2）： 62-66， 71 （in Chinese）.
6	周汉申. 单组元催化分解发动机参数设计［J］. 上海航天， 1990， 7（5）： 8-15.
	ZHOU H S. Parameter design of monocomponent cata lytic decomposition engine［J］. Aerospace Shanghai， 1990， 7（5）： 8-15 （in Chinese）.
7	GOHARDANI A S， STANOJEV J， DEMAIRÉ A， et al. Green space propulsion： Opportunities and prospects［J］. Progress in Aerospace Sciences， 2014， 71： 128-149.
8	冯强. 单组元推进剂喷注与分解对发动机性能的影响［D］. 大连：大连理工大学， 2021： 20-34.
	FENG Q. Influence of propellant injection and decomposition on monopropellant engine［D］. Dalian： Dalian University of Technology， 2021： 20-34 （in Chinese）.
9	GUAN J W， LI G X， LI H M， et al. Effect of catalytic bed porosity and mass flow rate on decomposition and combustion processes of a HAN-Based monopropellant thruster［J］. Vacuum， 2021， 194： 110566.
10	ZHANG T， LI G X， YU Y S， et al. Numerical simulation of ammonium dinitramide （ADN）-based non-toxic aerospace propellant decomposition and combustion in a monopropellant thruster［J］. Energy Conversion and Management， 2014， 87： 965-974.
11	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： 41-67.
	GUO T S. Simulation study on optimization design of structural parameters of HAN-based single component thruster［D］. Beijing： Beijing Jiaotong University， 2021： 41-67 （in Chinese）.
12	汪双庆. ADN基单组元推力器工作过程中催化分解及燃烧特性仿真研究［D］. 北京：北京交通大学， 2017： 75-98.
	WANG S Q. Simulation research on catalytic decomposition and combustion characteristics of ADN-based monopropellant thruster［D］. Beijing： Beijing Jiaotong University， 2017： 75-98 （in Chinese）.
13	于泽游. HAN基单组元火箭发动机流动与传热仿真研究［D］. 大连：大连理工大学， 2019： 32-34.
	YU Z Y. Numerical simulation on flow and heat transfer of Han-based monopropellant rocket engine［D］. Dalian： Dalian University of Technology， 2019： 32-34 （in Chinese）.
14	金东洙. HAN基单组元发动机仿真模型研究［D］. 大连：大连理工大学， 2018： 31-36.
	JIN D Z. Numerical simulation model of HAN-based mono-propellant rocket engine［D］. Dalian： Dalian University of Technology， 2018： 31-36 （in Chinese）.
15	张阿莉，刘国西，张涛，等. 流阻对200N单推-3发动机热试车工作特性的影响［J］. 推进技术， 2023， 2（3）： 1-14.
	ZHANG A L， LIU G X， ZHANG T， et al. Effect of flow resistance on the working characteristics of hot test of 200N single push-3 engine［J］. Propulsion Technology， 2023， 2（3）： 1-14 （in Chinese）.
16	冀鹏，梁树强，肖明杰，等. 高床载单组元肼发动机冷起动过程仿真研究［J］. 科学技术与工程， 2021， 21（32）： 13992-13997.
	JI P， LIANG S Q， XIAO M J， et al. Simulation of cold starting transient characteristics of high bed-load monopropellant hydrazine thruster［J］. Science Technology and Engineering， 2021， 21（32）： 13992-13997 （in Chinese）.
17	冀鹏，雷凡培，梁树强，等. 肼类单组元发动机冷起动过程温度敏感性研究［J］. 导弹与航天运载技术， 2021（6）： 21-26.
	JI P， LEI F P， LIANG S Q， et al. Investigation on the sensitivity of cold starting process of monopropellant hydrazine thruster to initial temperature［J］. Missiles and Space Vehicles， 2021（6）： 21-26 （in Chinese）.
18	汪凤山，姚兆普，刘阳，等. 甲基肼/四氧化二氮发动机脉冲工况仿真与试验研究［J］. 空间控制技术与应用， 2021， 47（4）： 56-62.
	WANG F S， YAO Z P， LIU Y， et al. Numerical and experimental analysis of pulse mode characteristics in a MMH/NTO rocket engine［J］. Aerospace Control and Application， 2021， 47（4）： 56-62 （in Chinese）.
19	李军，常克宇，陈展，等. 针栓喷注器液氧/甲烷推力室设计及试验研究［J］. 推进技术， 2022， 43（11）： 19-24.
	LI J， CHANG K Y， CHEN Z， et al. Design and experimental study of liquid oxygen/methane thrust chamber for pintle injector［J］. Journal of Propulsion Technology， 2022， 43（11）： 19-24 （in Chinese）.
20	陈君. 二硝酰胺铵（ADN）基液体推进剂催化分解及高压燃烧反应的试验与计算研究［D］. 北京：北京交通大学， 2018： 39-58.
	CHEN J. Experimental and computational study of catalytic decomposition and high pressure combustion reaction based on ammonium dinitramide（ADN） liquid propellant［D］. Beijing： Beijing Jiaotong University， 2018： 39-58 （in Chinese）.
21	王超，周旭东，汤建华，等. 单组元肼推力器温度场仿真及试验［J］. 推进技术， 2005， 26（1）： 1-4.
	WANG C， ZHOU X D， TANG J H， et al. Numerical and experimental studies for temperature field of monopropellant hydrazine thruster［J］. Journal of Propulsion Technology， 2005， 26（1）： 1-4 （in Chinese）.
22	冀鹏，肖明杰，梁树强. 单组元姿控动力系统动态过程仿真研究［J］. 兵器装备工程学报， 2022， 43（1）： 114-119.
	JI P， XIAO M J， LIANG S Q. Simulation study on transient process of monopropellant attitude control propulsion system［J］. Journal of Ordnance Equipment Engineering， 2022， 43（1）： 114-119 （in Chinese）.
23	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.
24	孙得川，金东洙，于泽游. 硝酸羟胺基单组元发动机起动过程数值模拟［J］. 兵器装备工程学报， 2018， 39（5）： 5-10.
	SUN D C， JIN D Z， YU Z Y. Numerical simulation of start-up process for HAN-based monopropellant rocket engine［J］. Journal of Ordnance Equipment Engineering， 2018， 39（5）： 5-10 （in Chinese）.
25	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）.
26	曹梦成. 无毒单组元液体火箭发动机起动过程研究［D］. 大连：大连理工大学， 2017： 52-60.
	CAO M C. Research on start process of non-toxic mono-propellant liquid rocket engine［D］. Dalian： Dalian University of Technology， 2017： 52-60 （in Chinese）.
27	PAKDEHI S， SHIRVANI F， ZOLFAGHARI R. A thermodynamic study on catalytic decomposition of hydrazine in a space thruster［J］. Archives of Thermodynamics， 2019， 40（4）： 151-166.
28	KONNOV A A， DE RUYCK J. Kinetic modeling of the decomposition and flames of hydrazine［J］. Combustion and Flame， 2001， 124（1-2）： 106-126.
29	MAKLED A E， BELAL H. Modeling of hydrazine decomposition for monopropellant thrusters［J］. Aviation Technology， 2009， 13（22）： 26-28.
30	COBOS C J， GLARBORG P， MARSHALL P， et al. Re-evaluation of rate constants for the reaction N₂H₄ （+ M） ⇄ NH₂ + NH₂ （+ M）［J］. Combustion and Flame， 2022： 112374.
31	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 engines［M］. Beijing： China Astronautic Publishing House， 2009 （in Chinese）.
32	ERGUN S. Fluid flow through packed columns［J］. Chemical Engineering Progress， 1952， 48（2）： 89-94.

参数	前催化床	后催化床
孔隙率	0.43	0.48
黏性阻力系数	1 615 378 057.46	126 904 315.65
惯性阻力系数	40 733.98	9 680.52
比表面积/m^-1	7 402.6	2 099.89

参数	前催化床
温度/K	300
热导率/（W·（m·K）^-1）	0.045 4
黏度/（kg·（m·s）^-1）	1.72×10^-5
摩尔质量/（kg·kmol^-1）	32.045 28
标准状态焓/（J·（kg·mol）^-1）	9.535×10⁷
标准状态熵/（J·（kg·mol·K）^-1）	238 601

起动	来流温度/K	催化床温度/K	温差∆T/K	吸热量Q/kJ	氨气量/mol
第1次	300	300	0	0	0.097
第2次	300	882.74	582.74	51.87	0.38

	各段温度监测点				各段压强监测点
项目	A	B	C	D	A	B	C
损失/%	33.6	30.8	29.7	39.8	2.0	14.1	14.0

[1]	Runchang HU, Zian WANG, Yongliang CHEN, Dapeng ZHOU, Dapeng YANG, Zheng GONG. Stability augmentation control of thrust-vectored V/STOL aircraft based on L1 adaptive control [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(S1): 727642-727642.
[2]	Qian ZHANG, Yuanxin YANG, Shuo TANG, Xianghang YUE, Zhi XU. Optimal thrust conditions and guidance for Mars solid ascent vehicles [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 328155-328155.
[3]	Libo WANG, Zhiwei JING, Chu TANG. Modelling and simulation of flexible aircraft in blast wind [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 228214-228214.
[4]	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.
[5]	Bowen SHU, Jiangtao HUANG, Zhenghong GAO, Gang LIU, Chengjun HE, Lu XIA. Sensitivity analysis of vector performance of two⁃dimensional shock vector control nozzle [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(13): 127831-127831.
[6]	Hechao ZHENG, Jianhui WANG, Ziyang HU, Zhonghai ZHANG, Guangping HE. Test of aerodynamic modeling accuracy of bird⁃scale flapping⁃wing vehicles [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(10): 127525-127525.
[7]	DENG Yunfei, ZHOU Nan, TIAN Rui, WEI Gang. Response characteristics of sandwich structure with S-shaped CFRP folded core under low velocity impact [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(6): 525446-525446.
[8]	ZHAO Xiaojian, SHAO Xiao, YANG Mingsui. Equivalence of vibro-acoustic response based on scaled thin-walled structures [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(3): 225146-225146.
[9]	CHAI Yuan, LUO Jianjun, WANG Mingming. Predictive game control for on-orbit transportation by multiple microsatellites with impulsive thrust [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(12): 326112-326112.
[10]	FENG Zhenyu, LIU Xu, LIN Lanhui, YANG Yongpan, XIE Jiang, SHI Xiaopeng, XIAO Pei, LI Leizi, YI Pengfei, LIU Xiaochuan, BAI Chunyu. Impact of seatbelts on impact characteristics of aviation seats and occupants [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 224808-224808.
[11]	CUI Peng, SONG Jie, LI Qinglian, CHEN Lanwei, LIANG Tao, SUN Jun. Dynamic modeling and simulation analysis of LOX/RP1 variable thrust engines using motor pump: Part I-single condition analysis [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124884-124884.
[12]	CAO Qikai, WANG Yan, YAO Niankui, HE Gang, CHEN Zhongming, ZHANG Guijiang, TIAN Zhiliang, WU Xinyue. Development and application of strength design technology of advanced carrier-based aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(8): 525793-525793.
[13]	CHEN Yile, YU Kaikai, XU Jinglei. New design method for scramjet nozzles with strong geometric constraints [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(6): 124259-124259.
[14]	MA Zongzhan, XU Zhi, TANG Shuo, ZHANG Qian. Improved iterative guidance method for launch vehicles [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(2): 324218-324218.
[15]	GUO Jia, PANG Zhaojun, YUE Shuai, DU Zhonghua. De-orbit strategy using Bang-Bang control for space tethered-combination [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(12): 324738-324738.

Dynamic response of hydrazine⁃based monocomponent rocket engine

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 19

References 32

Related Articles 15

Recommended Articles

Metrics

Comments