低温硝酸羟胺基单组元推力器气动谐振内加热快速催化点火起动

doi:10.7527/S1000-6893.2026.32878

Abstract

Abstract:

In order to achieve the rapid catalytic ignition startup of Hydroxylammonium Nitrate （HAN）-based monopropellant thrusters under low-temperature conditions （below 0 ℃）， a gas dynamic resonance internal heating method is adopted to centrally heat the front section of the thruster’s catalyst bed. Three low-temperature （-9 ℃） startup tests are conducted on a 20 N HAN-based monopropellant thruster， and the heat transfer process inside the combustion chamber of the internally heated monopropellant thruster is studied through system simulation calculations. The test results show that using nitrogen as the resonant working medium， the HAN-based thruster can achieve rapid catalytic ignition and startup under low-temperature conditions， reducing the preheating time required for traditional catalyst bed electric heating from tens of minutes to tens of seconds， and significantly shortening the ignition delay time； the preheating time for low-temperature pre-pulse ignition is reduced to approximately 20 s. The heat transfer calculation results show that the resonance heater can stably output a heating power of about 30-35 W； during the pre-pulse ignition phase， the pressure rise gradient is large， and the thermal accumulation effect promotes the rapid temperature rise inside the combustion chamber. At the end of this phase， the temperature difference between the casing and the catalyst bed is about 500 ℃； in the pulse operation phase， the catalyst bed is already at a relatively high temperature level， and the temperature difference between the casing and the catalyst bed is about 200 ℃； during the continuous operation phase， due to the continuous supply of propellant， the maximum temperature inside the catalyst bed can reach about 1 150 ℃， with a temperature difference of about 600 ℃ from the casing. The application of gas dynamic resonance heating method can realize the rapid catalytic ignition startup of HAN-based monopropellant thrusters under low-temperature conditions.

Key words: monopropellant thruster, hydroxylammonium nitrate, catalytic ignition, gas dynamic resonance heating, low-temperature startup

CLC Number:

V434

Yezhen SUN, Jun CHEN, Guozhu LIANG, Zhigang WANG, Liangen XIA, Xiaodong WANG. Gas dynamic resonance internal heating rapid catalytic ignition startup of low temperature hydroxylammonium nitrate-based monopropellant thruster[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(14): 132878.

Figures/Tables 19

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References 31

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组分	摩尔分数	质量分数
H₂O	0.587 94	0.454 94
CO₂	0.029 08	0.055 00
N₂	0.212 83	0.256 17
O₂	0.169 17	0.232 71

编号	初始温度/℃				氮气通气时间/s	预脉冲点火和脉冲工作		连续工作
编号	T1	T2	T3	T4	氮气通气时间/s	起动时序/s	起动程序	起动时序/s	工作时间/s
S-01	-9.38	-9.02	-9.18	-9.10	75	61.533	（0.05 s/1.00 s）×10
S-01	-9.38	-9.02	-9.18	-9.10	75	82.952	（0.1 s/1.0 s）×50
S-02	-9.64	-9.25	-9.37	-9.33	50	56.141	（0.05 s/0.95 s）×10	66.160	10
S-02	-9.64	-9.25	-9.37	-9.33	50	83.145	（0.1 s/1.0 s）×50	167.415	10
S-03	-9.60	-9.20	-9.35	-9.24	20	25.361	（0.05 s/1.00 s）×10
S-03	-9.60	-9.20	-9.35	-9.24	20	41.781	（0.1 s/1.0 s）×50

工况	温度/℃
工况	T1	T2	T3	T4
10次预脉冲点火前	4.33	-2.14	-6.37	-7.00
10次预脉冲点火后	56.34	168.23	195.63	147.72
50次脉冲工作前	130.46	233.14	243.30	183.85
50次脉冲工作后	505.15	662.51	661.79	616.01

工况	温度/℃
工况	T1	T2	T3	T4
10次预脉冲点火前	-0.51	-4.79	-7.65	-7.96
10次预脉冲点火后	86.21	235.47	221.99	157.60
第1次连续工作后	373.95	634.54	667.49	664.47
50次脉冲工作前	349.61	553.03	608.69	591.57
50次脉冲工作后	504.30	668.23	668.56	633.50
第2次连续工作前	442.57	535.70	555.55	514.01
第2次连续工作后	497.92	738.34	752.66	753.53

工况	温度/℃
工况	T1	T2	T3	T4
10次预脉冲点火前	-7.47	-8.14	-8.94	-8.87
10次预脉冲点火后	55.53	196.73	225.57	161.27
50次脉冲工作前	99.97	247.67	258.86	193.16
50次脉冲工作后	478.91	644.33	647.96	602.10

Gas dynamic resonance internal heating rapid catalytic ignition startup of low temperature hydroxylammonium nitrate-based monopropellant thruster

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工况	推进剂消耗计算值/g	推进剂消耗测量值/g	相对误差/%
S-01	92.333	93.571	1.32
S-02	268.578	266.627	0.73
S-03	95.339	95.166	0.18

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