微波等离子推力器的启动与稳定工作探索研究
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摘要
近十几年来，对各种类型的卫星、探测器、空间站等航天器推进系统的性能的要求不
断提高，使电推进系统进入一个长足的发展时期。微波等离子推力器（MPT—Microwave
Plasma Thruster）是一种新型的在研电热推进装置。它具有寿命长，效率高，羽流污染小的
特点与航天器兼容性好。
在微波等离子推力器中，微波谐振腔是组织微波能量吸收的重要部件，它和化学推进的
燃烧室一样，实现高效率的能量转化。研制出一个高水平的谐振腔对于整个微波等离子推进
系统至关重要。
本文介绍一种新型的集中电容微波谐振腔推力器。它与目前该领域使用的圆柱体
TM011微波谐振模式谐振腔相比，有鲜明的特点。在100W的电功率功耗下，它能在常压下
可靠启动并稳定工作。
所作的研究工作主要包括以下几方面：
1．研究了集中电容微波谐振腔的特性和把它应用于微波电热推进系统的适应性；
2．利用工程有限元法对设计的微波谐振进行了模态分析；
3．将理论分析的结果用于工程设计；
4．设计，加工，安装和调试了实验装置，进行了地面试验，并对结果进行分析。
经过多次的冷调和改进，使MPT能顺利启动并稳定工作，产生了等离子体区。说明MPT
系统原理和设计是可行的，为进一步的工作打下了基础。
In the recent decades, it has lasting demand for high performance of all kinds of
satellites, probes and space stations .lt makes the electric propulsion have a chance to
develop itself afond . Microwave Plasma Thruster (MPT) is a new type of Electric
Propulsion (EP) , which has many advantages , such as high efficiency , moderate
Specific ImpuI~,long life , well compatible with spacecraft and so on.
In MPT system, the microwave resonance cavity is the important part, which is in
charge of making better use of the energy by the gas which is for propulsive use. Like
the combustion chamber in chemical propulsion, it makes the energy conversion in high
efficiency. To develop a potent resonance cavity is the key to all MPT system
development.
In this paper, a new type of the microwave resonance cavity for producing plasma
was introduced. It is concentrated capacity microwave resonance cavity .lts construction
form is first used in the EP field. Contrasted with the cylinder TM011 resonance
cavity ,which is successfully used in the EP field , this cavity has some unequivocal
character At the low electric power and constant press ,100W, it can ignite reliably and
propel stably.
The content of this paper indude:
1. Doing research on the character of the concentrated capacity microwave resonance
cavity and the adaptability of this cavity using in the EP system;
2. Converting the result of theory into the engineering;
3. Analyzing the mode of the resonance cavity;
4. Processing the MPT experiment and analyzing the result
断提高，使电推进系统进入一个长足的发展时期。微波等离子推力器（MPT—Microwave
Plasma Thruster）是一种新型的在研电热推进装置。它具有寿命长，效率高，羽流污染小的
特点与航天器兼容性好。
在微波等离子推力器中，微波谐振腔是组织微波能量吸收的重要部件，它和化学推进的
燃烧室一样，实现高效率的能量转化。研制出一个高水平的谐振腔对于整个微波等离子推进
系统至关重要。
本文介绍一种新型的集中电容微波谐振腔推力器。它与目前该领域使用的圆柱体
TM011微波谐振模式谐振腔相比，有鲜明的特点。在100W的电功率功耗下，它能在常压下
可靠启动并稳定工作。
所作的研究工作主要包括以下几方面：
1．研究了集中电容微波谐振腔的特性和把它应用于微波电热推进系统的适应性；
2．利用工程有限元法对设计的微波谐振进行了模态分析；
3．将理论分析的结果用于工程设计；
4．设计，加工，安装和调试了实验装置，进行了地面试验，并对结果进行分析。
经过多次的冷调和改进，使MPT能顺利启动并稳定工作，产生了等离子体区。说明MPT
系统原理和设计是可行的，为进一步的工作打下了基础。
In the recent decades, it has lasting demand for high performance of all kinds of
satellites, probes and space stations .lt makes the electric propulsion have a chance to
develop itself afond . Microwave Plasma Thruster (MPT) is a new type of Electric
Propulsion (EP) , which has many advantages , such as high efficiency , moderate
Specific ImpuI~,long life , well compatible with spacecraft and so on.
In MPT system, the microwave resonance cavity is the important part, which is in
charge of making better use of the energy by the gas which is for propulsive use. Like
the combustion chamber in chemical propulsion, it makes the energy conversion in high
efficiency. To develop a potent resonance cavity is the key to all MPT system
development.
In this paper, a new type of the microwave resonance cavity for producing plasma
was introduced. It is concentrated capacity microwave resonance cavity .lts construction
form is first used in the EP field. Contrasted with the cylinder TM011 resonance
cavity ,which is successfully used in the EP field , this cavity has some unequivocal
character At the low electric power and constant press ,100W, it can ignite reliably and
propel stably.
The content of this paper indude:
1. Doing research on the character of the concentrated capacity microwave resonance
cavity and the adaptability of this cavity using in the EP system;
2. Converting the result of theory into the engineering;
3. Analyzing the mode of the resonance cavity;
4. Processing the MPT experiment and analyzing the result
引文
1． 毛根旺，何洪庆，杨娟，微波等离子推进系统(MPT)可行性论证，内部资料，1998
2． Avatinjan G A., Rylov Yu P., Salichov R S., "Electric Propulsion Systems for Small Satellites to Observe the Earth,Small Satellites for Earth Observation" Walter de Gmyter & Co., Nerlin ,1996
3． M.Martines-Sanchez "Spacecraft Electric Propulsion-An Overview" , Journal of Propulsion and Power. Vol.14, No.5,1998．
4． M.MMicci, Prospects for Microwave Heated propulsion, AIAA-84-1390,1984．
5． D.A.Schwer and C.L.Merkle, Analysis of microwave-heated rocket engines for space propulsion, AIAA-93-2104．
6． M.C.Hawley and T.J.Morimand, Review of research and development of the microwave electrothermal thruster, AIAA-89-5620．
7． M.G.Hawley, J.SAsmussen, J.W.Filipus, Review of research and development on the microwave electrothermal thruster, Vol.5, No.6, Nov.-Dec. 1989, pp.703-712．
8． S. Haraburda , M. .Hawley , Theoretical Nozzle Performance of a Microwave Electrothermal Thruster Using Experimental Data, AIAA92-3110
9． D.J.Sullian and M.MMicci, Performance testing and exhaust plume characterization of the microwave arcjet thruster, AIAA-94-3127, Jun 1994．
10． D.Nordling and MMMicci , Low-power microwave arcjet performance testing, IEPC-97-089,Aug. 1997．
11． F.J. Souliez , S.G Chianese , etc, Low-Power Microwave Arcjet Testing: Plasma and Plume Diagnostics and Performance Evaluation, AIAA 99-2717
12． CarlNordling，Jonny Osterman，物理学手册，河南科学技术出版社，1986
13． F. J.Souliez,S.G.Chianese,G.H.Dizac and M.M. Micci . Low-Power Microwave Arcjet Test ing :Plasma and Plume Diagnostics and Performance Evaluation . AIAA 99-2717
14． 陈熙，高温电离气体的传热与流动，科学出版社，1993
15． 陈孟尧主编，电磁场与微波技术，高等教育出版社，1989
16． 吴明英，毛秀华，微波技术，西北电讯工程学院出版社，1985
17． 李标荣，莫以豪，王莜珍，无机介电材料， 上海科学技术出版社，1986
18． 龚微蒸，张裕荣，荣磊，电子设备结构设计基础， 东南大学出版社，1994
19． 陈振国，微波技术基础与应用，北京邮电大学出版社，1988
20． 孙道礼，微波技术， 哈尔滨工业大学出版社，1988
21． 贺瑞霞，陈振国等，微波技术基础，人民邮电出版社，1988
22． 顾茂章，张克潜，微波技术，清华大学出版社，1989
23． 张兆镗，钟若青，微波加热技术基础，电子工业出版社，1988
24． 杨涓，何洪庆，毛根旺，微波等离子推力器微波模式的合理选择，推进技术，1999(1)
25． 毛根旺，韩先伟等，电推进研究的技术状态和发展前景，推进会议论文，1999
26． 孙再庸，微波电热推进器的树脂模拟，博士学位论文
27． 韩先伟，微波等离子推力器地面试验系统建设和(尾)羽流流动计算，硕士学位论文
28． 黄晓砥，毛根旺等，微波等离子推进装置的新探索，推进会议论文，2000
2． Avatinjan G A., Rylov Yu P., Salichov R S., "Electric Propulsion Systems for Small Satellites to Observe the Earth,Small Satellites for Earth Observation" Walter de Gmyter & Co., Nerlin ,1996
3． M.Martines-Sanchez "Spacecraft Electric Propulsion-An Overview" , Journal of Propulsion and Power. Vol.14, No.5,1998．
4． M.MMicci, Prospects for Microwave Heated propulsion, AIAA-84-1390,1984．
5． D.A.Schwer and C.L.Merkle, Analysis of microwave-heated rocket engines for space propulsion, AIAA-93-2104．
6． M.C.Hawley and T.J.Morimand, Review of research and development of the microwave electrothermal thruster, AIAA-89-5620．
7． M.G.Hawley, J.SAsmussen, J.W.Filipus, Review of research and development on the microwave electrothermal thruster, Vol.5, No.6, Nov.-Dec. 1989, pp.703-712．
8． S. Haraburda , M. .Hawley , Theoretical Nozzle Performance of a Microwave Electrothermal Thruster Using Experimental Data, AIAA92-3110
9． D.J.Sullian and M.MMicci, Performance testing and exhaust plume characterization of the microwave arcjet thruster, AIAA-94-3127, Jun 1994．
10． D.Nordling and MMMicci , Low-power microwave arcjet performance testing, IEPC-97-089,Aug. 1997．
11． F.J. Souliez , S.G Chianese , etc, Low-Power Microwave Arcjet Testing: Plasma and Plume Diagnostics and Performance Evaluation, AIAA 99-2717
12． CarlNordling，Jonny Osterman，物理学手册，河南科学技术出版社，1986
13． F. J.Souliez,S.G.Chianese,G.H.Dizac and M.M. Micci . Low-Power Microwave Arcjet Test ing :Plasma and Plume Diagnostics and Performance Evaluation . AIAA 99-2717
14． 陈熙，高温电离气体的传热与流动，科学出版社，1993
15． 陈孟尧主编，电磁场与微波技术，高等教育出版社，1989
16． 吴明英，毛秀华，微波技术，西北电讯工程学院出版社，1985
17． 李标荣，莫以豪，王莜珍，无机介电材料， 上海科学技术出版社，1986
18． 龚微蒸，张裕荣，荣磊，电子设备结构设计基础， 东南大学出版社，1994
19． 陈振国，微波技术基础与应用，北京邮电大学出版社，1988
20． 孙道礼，微波技术， 哈尔滨工业大学出版社，1988
21． 贺瑞霞，陈振国等，微波技术基础，人民邮电出版社，1988
22． 顾茂章，张克潜，微波技术，清华大学出版社，1989
23． 张兆镗，钟若青，微波加热技术基础，电子工业出版社，1988
24． 杨涓，何洪庆，毛根旺，微波等离子推力器微波模式的合理选择，推进技术，1999(1)
25． 毛根旺，韩先伟等，电推进研究的技术状态和发展前景，推进会议论文，1999
26． 孙再庸，微波电热推进器的树脂模拟，博士学位论文
27． 韩先伟，微波等离子推力器地面试验系统建设和(尾)羽流流动计算，硕士学位论文
28． 黄晓砥，毛根旺等，微波等离子推进装置的新探索，推进会议论文，2000