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

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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

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Dynamic response of hydrazine⁃based monocomponent rocket engine

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