火箭推进

新型绿色单组元液体推进剂发展现状与趋势

1.北京航天试验技术研究所航天绿色推进剂研究与应用北京市重点实验室,北京 100074; 2.航天推进技术研究院,陕西西安 710100; 3.中国航天科技创新研究院,北京 100088

关键词：新型绿色单组元液体推进系统; HAN基单组元液体推进剂; ADN基单组元液体推进剂; 姿轨控动力系统

Development status and trend of novel green monopropellant

BAO Shiguo¹,MA Tianju²,TIAN Guoqing¹,XIANG Kai¹,XUE Wei³,SUN Haiyun¹,FANG Tao¹,ZHANG Xing³

1.Beijing Key Laboratory of Research and Application for Aerospace Green Propellants,Beijing Institute of Aerospace Testing Technology, Beijing 100074, China; 2.Academy of Aerospace Propulsion Technology, Xi'an 710100, China; 3.China Academy of Aerospace Science and Innovation, Beijing 100088, China

Keywords：the novel green monopropellant propulsion system; HAN-based monopropellant; ADN-based monopropellant; attitude-orbit control system

DOI: 10.3969/j.issn.1672-9374.2024.05.001

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参考文献

随着对生态环境、安全的日益关注以及航天推进技术的不断发展,对推进剂提出了绿色无毒的性能要求,新型绿色单组元液体推进系统成为航天推进的重要研究方向之一。硝酸羟铵基单组元液体推进剂(HAN基单组元推进剂)和二硝酰胺铵基单组元液体推进剂(ADN基单组元推进剂)具有绿色无污染、密度大、比冲性能可调节、饱和蒸汽压低和使用维护成本低等特点,可以应用于卫星、飞船、运载火箭等飞行器的姿轨控动力系统,二者均已完成多次飞行演示验证并获得应用,受到了各国航天领域的广泛关注。

With the increasing concern about ecological environment, safety and the development of space propulsion technology, a new requirement for green or non-toxic propellant has been put forward, and the novel green monopropellant propulsion system has become one of the important research directions of space propulsion. Hydroxyammonium nitrate-based monopropellant(HAN-based monopropellant)and dinitrate ammonium-based monopropellant(ADN-based monopropellant)have the characteristics of green and pollution-free, high density, adjustable specific impulse performance, low saturation vapour pressure and low maintenance cost, which can be used in the attitude control system of satellites, spacecraft, launch vehicles, etc. Both HAN-based monopropellant and ADN-based monopropellant have been demonstrated several times, and have attracted much attention in the aerospace field.

引言
1 HAN基单组元液体推进剂
2 ADN基单组元液体推进剂
3 绿色单元液体推进剂的非催化点火
4 从绿色单元液体推进剂发展中得到的启示
5 结论

表1 低燃温中能HAN推进剂配方性能对比<br/>Tab.1 Formulation performance comparison of HAN monopropellant with low combustion temperature

表1 低燃温中能HAN推进剂配方性能对比
Tab.1 Formulation performance comparison of HAN monopropellant with low combustion temperature

表2 部分高能HAN基单组元推进剂的主要性能[22]<br/>Tab.2 Main properties of some high energy HAN-based mono-propellants[22]

表2 部分高能HAN基单组元推进剂的主要性能[22]
Tab.2 Main properties of some high energy HAN-based mono-propellants[22]

表3 无水肼、AF-M315E和SHP163推进剂性能对比<br/>Tab.3 Properties comparison of anhydrous hydrazine,AF-M315E and SHP163

表3 无水肼、AF-M315E和SHP163推进剂性能对比
Tab.3 Properties comparison of anhydrous hydrazine,AF-M315E and SHP163

表4 常温和120 ℃热试车参数[29]<br/>Tab.4 Data of normal temperature and 120 ℃ firing[29]

表4 常温和120 ℃热试车参数[29]
Tab.4 Data of normal temperature and 120 ℃ firing[29]

图1 NASA绿色推进路线图[30]<br/>Fig.1 NASA's green propulsion roadmap[30]

图1 NASA绿色推进路线图[30]
Fig.1 NASA's green propulsion roadmap[30]

图2 NCADE导弹拦截器结构示意图[31]<br/>Fig.2 Schematic diagram of interceptor structure of NCADE missile[31]

图2 NCADE导弹拦截器结构示意图[31]
Fig.2 Schematic diagram of interceptor structure of NCADE missile[31]

图3 GPIM项目的HAN基推进系统[32]<br/>Fig.3 The HAN-based propulsion system for the GPIM project[32]

图3 GPIM项目的HAN基推进系统[32]
Fig.3 The HAN-based propulsion system for the GPIM project[32]

图4 Aerojet公司HAN基推进剂1 N发动机和22 N发动机[32]<br/>Fig.4 Aerojet's HAN-based 1 N and 22 N thrusters[32]

图4 Aerojet公司HAN基推进剂1 N发动机和22 N发动机[32]
Fig.4 Aerojet's HAN-based 1 N and 22 N thrusters[32]

图5 MPS-130立方体卫星推进系统[35]<br/>Fig.5 MPS-130 cubic star propulsion system[35]

图5 MPS-130立方体卫星推进系统[35]
Fig.5 MPS-130 cubic star propulsion system[35]

图6 Lunar Flashlight卫星模拟图[36]<br/>Fig.6 Simulation diagram of Lunar Flashlight satellite[36]

图6 Lunar Flashlight卫星模拟图[36]
Fig.6 Simulation diagram of Lunar Flashlight satellite[36]

图7 HNP系列HAN基单组元推进剂配方性能[42]<br/>Fig.7 Performances of HNP series HAN-based monopropellants[42]

图7 HNP系列HAN基单组元推进剂配方性能[42]
Fig.7 Performances of HNP series HAN-based monopropellants[42]

图8 微小卫星中的GPRCS推进系统[43]<br/>Fig.8 GPRCS propulsion system in microsatellites[43]

图8 微小卫星中的GPRCS推进系统[43]
Fig.8 GPRCS propulsion system in microsatellites[43]

图9 SHP-163推进剂应用于RAPIS-1号卫星[44]<br/>Fig.9 Application of SHP-163 propellant to RAPIS-1 satellite[44]

图9 SHP-163推进剂应用于RAPIS-1号卫星[44]
Fig.9 Application of SHP-163 propellant to RAPIS-1 satellite[44]

图10 新一代载人飞船试验船返回舱[45]<br/>Fig.10 The return capsule of the new generation manned spacecraft test ship[45]

图10 新一代载人飞船试验船返回舱[45]
Fig.10 The return capsule of the new generation manned spacecraft test ship[45]

表5 ADN理化性质及毒性<br/>Tab.5 The physicochemical properties and toxicity of ADN

表5 ADN理化性质及毒性
Tab.5 The physicochemical properties and toxicity of ADN

表6 瑞典研制的一系列ADN基单组元推进剂配方与性能<br/>Tab.6 Formula and properties of ADN-based monopropellants developed by Sweden

表6 瑞典研制的一系列ADN基单组元推进剂配方与性能
Tab.6 Formula and properties of ADN-based monopropellants developed by Sweden

表7 ADN基单组元推进剂的组成与性能<br/>Tab.7 Composition and properties of ADN-based monopropellant

表7 ADN基单组元推进剂的组成与性能
Tab.7 Composition and properties of ADN-based monopropellant

表8 ADN基单组元推进剂低温配方组成<br/>Tab.8 Composition of ADN based monopropellant with low freezing point

表8 ADN基单组元推进剂低温配方组成
Tab.8 Composition of ADN based monopropellant with low freezing point

表9 ADN基离子液体推进剂配方组成与性能<br/>Tab.9 Composition and properties of AND-based ionic liquid propellant

表9 ADN基离子液体推进剂配方组成与性能
Tab.9 Composition and properties of AND-based ionic liquid propellant

表10 无溶剂ADN基离子液体推进剂配方组成与性能<br/>Tab.10 Composition and properties of AND-based ionic liquid propellant without solvent

表10 无溶剂ADN基离子液体推进剂配方组成与性能
Tab.10 Composition and properties of AND-based ionic liquid propellant without solvent

图11 ADN基离子液体推进剂制备示意图[62]<br/>Fig.11 Preparation of ADN-based ionic liquid propellant[62]

图11 ADN基离子液体推进剂制备示意图[62]
Fig.11 Preparation of ADN-based ionic liquid propellant[62]

表11 ADN基离子液体推进剂燃烧试验结果<br/>Tab.11 Combustion test results of ADN-based ionic liquid propellant

表11 ADN基离子液体推进剂燃烧试验结果
Tab.11 Combustion test results of ADN-based ionic liquid propellant

图12 我国ADN基液体推进系统试车实况[65]<br/>Fig.12 Test of ADN-based liquid propulsion system in China[65]

图12 我国ADN基液体推进系统试车实况[65]
Fig.12 Test of ADN-based liquid propulsion system in China[65]

表12 不同推力量级ADN基液体空间发动机稳态比冲性能<br/>Tab.12 Steady-state specific impulse of ADN-based liquid thruster with different thrust levels

表12 不同推力量级ADN基液体空间发动机稳态比冲性能
Tab.12 Steady-state specific impulse of ADN-based liquid thruster with different thrust levels

图13 不同推力量级ADN基液体空间发动机的热试车试验[66]<br/>Fig.13 Fire tests of ADN-based liquid thrusters with different thrust levels[66]

图13 不同推力量级ADN基液体空间发动机的热试车试验[66]
Fig.13 Fire tests of ADN-based liquid thrusters with different thrust levels[66]

图14 HPGP推进系统示意图[67-69]<br/>Fig.14 Schematic diagram of HPGP propulsion system[67-69]

图14 HPGP推进系统示意图[67-69]
Fig.14 Schematic diagram of HPGP propulsion system[67-69]

图15 我国ADN基液体推进剂用卫星[65-66]<br/>Fig.15 China's ADN-based liquid propellant satellite[65-66]

图15 我国ADN基液体推进剂用卫星[65-66]
Fig.15 China's ADN-based liquid propellant satellite[65-66]

图16 点火装置示意图[72]<br/>Fig.16 Schematic diagram of the ignition device[72]

图16 点火装置示意图[72]
Fig.16 Schematic diagram of the ignition device[72]

图17 HAN基单组元推进剂电解引导点火的电化学反应过程示意图[73]<br/>Fig.17 Physiochemical processes involved in electrolytic induced ignition of HAN-based monopropellant[73]

图17 HAN基单组元推进剂电解引导点火的电化学反应过程示意图[73]
Fig.17 Physiochemical processes involved in electrolytic induced ignition of HAN-based monopropellant[73]

图18 采用加热棒点火对LMP-103S进行初步点火试验[77]<br/>Fig.18 Preliminary glow plug ignition test with LMP-103S[77]

图18 采用加热棒点火对LMP-103S进行初步点火试验[77]
Fig.18 Preliminary glow plug ignition test with LMP-103S[77]

图19 液滴点火过程直观图像和纹影图像[79]<br/>Fig.19 Real and schlieren images of droplet ignition process[79]

图19 液滴点火过程直观图像和纹影图像[79]
Fig.19 Real and schlieren images of droplet ignition process[79]

图20 1 N级推力器采用等离子体辅助燃烧的原理图[81]<br/>Fig.20 The schematic diagram of 1 N-stage thruster using plasma-assisted combustion[81]

图20 1 N级推力器采用等离子体辅助燃烧的原理图[81]
Fig.20 The schematic diagram of 1 N-stage thruster using plasma-assisted combustion[81]

图21 ADN/[AMIM][DCA]的重复点火延迟图[87]<br/>Fig.21 Repeated ignition delay diagram of ADN/[AMIM][DCA][87]

图21 ADN/[AMIM][DCA]的重复点火延迟图[87]
Fig.21 Repeated ignition delay diagram of ADN/[AMIM][DCA][87]

图22 点火器概念验证样机的零件分解图[89]<br/>Fig.22 Part decomposition diagram of conceptual verification prototype of igniter[89]

图22 点火器概念验证样机的零件分解图[89]
Fig.22 Part decomposition diagram of conceptual verification prototype of igniter[89]

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期刊信息

火箭推进
JOURNAL OF ROCKET PROPULSION

主管中国航天科技集团有限公司

主办航天推进技术研究院

编辑出版《火箭推进》编辑部

主编张晓军

执行主编陈　晖

编辑部主任马　杰

国内发行《火箭推进》编辑部

国外发行中国国际图书贸易总公司

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邮编 710100

电话 029-85208348

Email work@hjtj1975.com

标准刊号 ISSN 1672-9374
CN 61-1436/V

备注

引言

1 HAN基单组元液体推进剂

2 ADN基单组元液体推进剂

3 绿色单元液体推进剂的非催化点火

4 从绿色单元液体推进剂发展中得到的启示

5 结论

期刊信息