火箭推进

二硝酰胺铵(ADN)是一种高能量密度、不含氯元素的绿色无毒无机盐类物质。它可以作为氧化剂,与甲醇、水混合后组成ADN基液体推进剂。ADN基液体推进剂作为一种高性能、绿色无毒、可存储的新型推进剂,可以提供相比于传统肼类推进剂更高的比冲性能,代表了空间化学推进技术的一个新的研究方向和发展趋势。主要介绍了北京控制工程研究所研制的ADN基液体空间发动机的实验研究和在轨飞行验证情况。首先,基于可调谐二极管红外吸收光谱(TDLAS)的测量方法,针对一台1 N推力的模型ADN基发动机进行了实验研究,获得了燃烧室内燃气温度、CO与N2O组分浓度等特征参数随喷注压力的变化关系。然后,介绍了0.2 N,1 N,5 N及20 N ADN基发动机的高空模拟热试车试验情况和主要性能指标。最后,介绍了1N ADN基发动机的首次在轨飞行验证情况。这些研究结果有利于绿色空间推进技术的发展。

The experimental investigation and on-orbit flying validation of the ADN-based liquid space engine developed by Beijing Institute of Control Engineering(BICE)are introduced in this paper.The experiment research about the combustion mechanism of the combustion chamber of a 1N model thruster was performed with the measuring method of tunable diode laser absorption spectroscopy(TDLAS).The variation of characteristic parameters such as fuel gas temperature and component concentrations of CO and N2O in the combustion chamber with injection pressure were measured.The effects of the propellant inlet pressure on the combustion process were evaluated.The hot fire test results and main performance indexes of an ADN-based liquid thruster family including 0.2 N, 1 N, 5 N, and 20 N thrusters are presented.The performance data at different operation conditions were obtained.The on-orbit flying validation result of the 1N ADN-based liquid thruster is introduced for the first time.The contents in this paper are beneficial to the development of green aerospace propulsion techniques.

引言
1 基于可调谐二极管红外吸收光谱(TDLAS)的实验研究
2 ADN基液体空间发动机的高空模拟热试车试验研究
3 ADN基液体空间发动机的在轨试验验证
4 结束语

图1 带光学观测窗口的模型发动机结构简图<br/>Fig.1 Structure diagram of thruster model with optical windows

图1 带光学观测窗口的模型发动机结构简图
Fig.1 Structure diagram of thruster model with optical windows

图2 带光学观测窗口的模型发动机实物<br/>Fig.2 Picture of model thruster with optical windows

图2 带光学观测窗口的模型发动机实物
Fig.2 Picture of model thruster with optical windows

图3 TDLAS测量系统示意图<br/>Fig.3 Diagram of TDLAS measurement system

图3 TDLAS测量系统示意图
Fig.3 Diagram of TDLAS measurement system

图4 稳态工况下的气相温度瞬态测量结果<br/>Fig.4 Measurement results of instantaneous gaseous phase temperature under steady-state condition

图4 稳态工况下的气相温度瞬态测量结果
Fig.4 Measurement results of instantaneous gaseous phase temperature under steady-state condition

$图5 稳态工况下的CO摩尔分数瞬态测量结果<br/>Fig.5 Instantaneous measurement results of CO mole fraction under steady-state condition$

图5 稳态工况下的CO摩尔分数瞬态测量结果
Fig.5 Instantaneous measurement results of CO mole fraction under steady-state condition

$图6 稳态工况下的N2O摩尔分数瞬态测量结果<br/>Fig.6 Instantaneous measurement results of N2O mole fraction under steady-state condition$

图6 稳态工况下的N2O摩尔分数瞬态测量结果
Fig.6 Instantaneous measurement results of N2O mole fraction under steady-state condition

图7 不同推力量级ADN基液体空间发动机的热试车试验<br/>Fig.7 Hot fire tests of ADN-based liquid thrusters with different thrust levels

图7 不同推力量级ADN基液体空间发动机的热试车试验
Fig.7 Hot fire tests of ADN-based liquid thrusters with different thrust levels

表1 不同推力量级ADN基液体空间发动机稳态比冲性能<br/>Tab.1 Steady-state specific impulse of ADN-based liquid thruster with different thrust levels

表1 不同推力量级ADN基液体空间发动机稳态比冲性能
Tab.1 Steady-state specific impulse of ADN-based liquid thruster with different thrust levels

表2 1 N ADN基液体空间发动机在轨试验验证情况<br/>Tab.2 On-orbit flying validation of the 1 N ADN-based liquid thruster

表2 1 N ADN基液体空间发动机在轨试验验证情况
Tab.2 On-orbit flying validation of the 1 N ADN-based liquid thruster

[1] Yang R, Thakre P, Yang V. Thermal decomposition and combustion of ammonium dinitramide(Review)[J]. Combust explo shock, 2005, 41: 657-679.
[2] PARK J, CHAKRABORTY D, LIN M C. Thermal decomposition of gaseous ammonium dinitramide at low pressure [C]// Proceedings of Twenty-Seventh Symposium(International)on Combustion. [S.l.]: Combustion Institute, 1998: 2351-2357.
[3] SINDITSKII V P, EGORSHEV V Y, LEVSHENKOV A I, et al. Combustion of ammonium dinitramide, part 1: burning behavior [J]. Journal of propulsion power, 2006, 22: 769-776.
[4] SINDITSKII V P, EGORSHEV VY, LEVSHENKOV A I, et al. Combustion of ammonium dinitramide, part 2: combustion mechanism [J]. Journal of propulsion power, 2006, 22: 777-785.
[5] KOROBEINICHEV O P, BOLSHOVA TA, PALETSKY A A. Modeling the chemical reactions of ammonium dinitramide(ADN)in a flame [J]. Combust flame, 2001, 126: 1516-1523.
[6] THAKRE P, DUAN Y, YANG V. Modeling of ammonium dinitramide(ADN)monopropellant combustion with coupled condensed and gas phase kinetics [J]. Combust flame, 2014, 161: 347-362.
[7] WINGBORG N, JOHANSSON M, BODIN L. Initial development of a laboratory rocket thruster for ADN-based liquid monopropellant: FOI-R-2123-SE [R]. Sweden: Swedish Defence Research Agency, 2006.
[8] LARSSON A, WINGBORG N. Green propellants based on ammonium dinitramide(ADN)[M/OL]. [2011-02-14]. http://xueshu.baidu.com.
[9] YAO Z P, ZHANG W, WANG M, et al. Tunable diode laser absorption spectroscopy measurements of high-pressure ammonium dinitramide combustion [J]. Aerosp Sci Technol, 2015, 45: 140-149.
[10] ZENG H, LI F, ZHANG S H, et al. Midinfrared absorption measurements of nitrous oxide in ammonium dinitramide monopropellant thruster [J]. Journal of propulsion power, 2015, 31: 1496-1500.
[11] JING L, HUO Y, WANG J L, et al. Experimental investigations on the evaporation and combustion processes of ammonium-dinitramide-based liquid propellant [J]. Journal of propulsion power, 2017, 33: 343-349.
[12] ANFLO K, PERSSON M, THORMAHLEN P, et al. Flight demonstration of an ADN-based Propulsion System: IAC-06-C4.108 [R]. [S.l.]: IAC, 2006.
[13] 徐峰,罗军,彭飞,火箭发动机试验红外测温技术应用[J],火箭推进,2017,43(1):,78-84.
[14] ZHOU X. Diode-laser absorption sensor for combustion control[D].USA: Standford University, 2005..

备注

引言

1 基于可调谐二极管红外吸收光谱(TDLAS)的实验研究

2 ADN基液体空间发动机的高空模拟热试车试验研究

3 ADN基液体空间发动机的在轨试验验证

4 结束语

期刊信息