MPT微波源研制及系统效率分析
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摘要
近十几年来，随着对航天器推进系统性能要求的不断提高，电推进以其独有优势引起了学术和航天工业界的兴趣和重视，并且越来越多地被应用到空间任务中。微波等离子推力器(MPT)是一种电热型推力器，它具有比冲适中、寿命长、羽流污染小等优点，具有广阔的应用前景。微波源作为MPT的能量供给单元，是MPT关键部件之一，其效率高低也是衡量MPT总体性能的重要标志。
目前MPT微波源体积大、重量重，微波输出功率不够稳定，不能在真空环境下工作，对MPT研究和性能提高起着制约作用。本文在原有微波源基础上，通过理论分析和实际设计，研制完成了功率为200W、可在真空下工作的微波源，并在试验基础上对MPT系统效率进行了分析和估算。
论文的主要工作和见解包括：
1．利用微波器件、电路、传热学等有关知识，对微波源主要组成部件进行了分析、比较和选择，确定了其实现方式。微波发生器采用效率高、功率大、价格低的磁控管；磁控管供电电源使用重量轻、效率高、输出功率易于控制的开关电源；器件散热方式运用了可在真空中工作的密闭水循环冷却。
2．详细介绍了微波源微波器件的性能及参数，分析设计了开关电源及微波源散热结构并加工出实物样品，在此基础上制作出整个微波源的试验装置。对试验装置进行调试、标定和实际负载试验，解决了调试过程出现的一些现象，设计出充气密封机箱防止开关电源输出端高压和大功率微波在真空中打火。对微波源标定和负载试验结果给出了分析总结。
3．用长线理论、微波谐振腔电磁场分布及其等效电路，分析了MPT系统微波传输效率，指出了微波源效率和MPT谐振腔耦合效率是影响MPT系统整体效率的主要因素之一。最后结合实验数据估算出MPT实际工作效率约为30％左右。
经过较长时间验证，研制的微波源在地面和真空中均能长时间稳定、可靠工作，性能良好，表明研制的微波源是可行的，另外MPT效率分析初步给出了影响效率的一些因素，这些都为进一步提高MPT性能奠定了基础。
Over the past ten years, with more and more requirements for high performance spacecraft propulsion system, Electric Propulsion (EP) has become highlight of propulsion field because of its unique advantages. Microwave Plasma Thruster (MPT) is a new type of EP, which has high efficiency, moderate Specific Impulse, long life, well compatible with spacecraft and so on. It has wide applying prospect .Microwave Power Supply(MPS) is a main component of MPT which gives MPT energy.
At present, MPS has deficiency of large volume, high weight, unstablable output power, especially being unable to be used in vacuum. This paper aimed to develop a new type of MPS which has 200W output microwave and can work in vacuum. In addition, the paper also simply analysed the MPT efficiency on the base ofexperiment.
The contents of this paper include:
1. Choose the main component element of MPS using related microwave, circuit, heat transfer knowledge,and decide the MPS's forming project. The microwave generator uses magnetron whose power is supplied by switching source, and the instruments' heat elimination is adopted closing water circulation.
2. The function of microwave components was detailedly introduced, and the switching supply as well as MPS's heat emission structure was analysed, on the base of which the experimental MPS was made. Some questions were solved which occurred during experiment of MPS, and the sealed box was designed to prevent the high volatge and large microwave power from discharge, as the same time the experimental results were summed up.
3.With microwave transmission and electromagnetic field theory, the transferring efficiency of MPT system was analysed, and the results show that MPS and MPT resonant cavity were the main factor influencing MPT whole efficiency.
After many examinations, the developed MPS can stably work in atmosphere and vacuum enviroment and has well-behaviour ,which proves it is feasible. The developed MPS together with MPT efficiency gives basis of further improving MPT capability
目前MPT微波源体积大、重量重，微波输出功率不够稳定，不能在真空环境下工作，对MPT研究和性能提高起着制约作用。本文在原有微波源基础上，通过理论分析和实际设计，研制完成了功率为200W、可在真空下工作的微波源，并在试验基础上对MPT系统效率进行了分析和估算。
论文的主要工作和见解包括：
1．利用微波器件、电路、传热学等有关知识，对微波源主要组成部件进行了分析、比较和选择，确定了其实现方式。微波发生器采用效率高、功率大、价格低的磁控管；磁控管供电电源使用重量轻、效率高、输出功率易于控制的开关电源；器件散热方式运用了可在真空中工作的密闭水循环冷却。
2．详细介绍了微波源微波器件的性能及参数，分析设计了开关电源及微波源散热结构并加工出实物样品，在此基础上制作出整个微波源的试验装置。对试验装置进行调试、标定和实际负载试验，解决了调试过程出现的一些现象，设计出充气密封机箱防止开关电源输出端高压和大功率微波在真空中打火。对微波源标定和负载试验结果给出了分析总结。
3．用长线理论、微波谐振腔电磁场分布及其等效电路，分析了MPT系统微波传输效率，指出了微波源效率和MPT谐振腔耦合效率是影响MPT系统整体效率的主要因素之一。最后结合实验数据估算出MPT实际工作效率约为30％左右。
经过较长时间验证，研制的微波源在地面和真空中均能长时间稳定、可靠工作，性能良好，表明研制的微波源是可行的，另外MPT效率分析初步给出了影响效率的一些因素，这些都为进一步提高MPT性能奠定了基础。
Over the past ten years, with more and more requirements for high performance spacecraft propulsion system, Electric Propulsion (EP) has become highlight of propulsion field because of its unique advantages. Microwave Plasma Thruster (MPT) is a new type of EP, which has high efficiency, moderate Specific Impulse, long life, well compatible with spacecraft and so on. It has wide applying prospect .Microwave Power Supply(MPS) is a main component of MPT which gives MPT energy.
At present, MPS has deficiency of large volume, high weight, unstablable output power, especially being unable to be used in vacuum. This paper aimed to develop a new type of MPS which has 200W output microwave and can work in vacuum. In addition, the paper also simply analysed the MPT efficiency on the base ofexperiment.
The contents of this paper include:
1. Choose the main component element of MPS using related microwave, circuit, heat transfer knowledge,and decide the MPS's forming project. The microwave generator uses magnetron whose power is supplied by switching source, and the instruments' heat elimination is adopted closing water circulation.
2. The function of microwave components was detailedly introduced, and the switching supply as well as MPS's heat emission structure was analysed, on the base of which the experimental MPS was made. Some questions were solved which occurred during experiment of MPS, and the sealed box was designed to prevent the high volatge and large microwave power from discharge, as the same time the experimental results were summed up.
3.With microwave transmission and electromagnetic field theory, the transferring efficiency of MPT system was analysed, and the results show that MPS and MPT resonant cavity were the main factor influencing MPT whole efficiency.
After many examinations, the developed MPS can stably work in atmosphere and vacuum enviroment and has well-behaviour ,which proves it is feasible. The developed MPS together with MPT efficiency gives basis of further improving MPT capability
引文
1.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 Gruyter & Co., Nerlin,1996
2.M.Martines-Sanchez "Spacecraft Electric Propulsion - An Overview",Journal of Propulsion and Power. Vol. 14, No.5, 1998.
3.M.M.Micci, Prospects for Microwave Heated propulsion, AIAA-84-1390, 1984.
4.D.A.Schwer and C.L.Merkle, Analysis of microwave-heated rocket engines for space propulsion, AIAA-93-2104.
5.M.C.Hawley and T.J.Morimand, Review of research and development of the microwave electrothermal thruster, AIAA-89-5620.
6.M.C.Hawley, J.S.Asmussen, J.W. Filipus, Review of research and development on the microwave electrothermal thruster, Vol.5, No.6, Nov.-Dec. 1989, pp.703-712.
7.M.R. Durbin and M.M.Micci, Analysis of a Microwave-heated Plasmas in Hydrogen、Helium and Nitrogen, AIAA paper 87-1013, May 1-3, 1987
8.W. Haag, Arcjet Stating Reliability: A Multi-star Test on Hydrogen/Nitrogen Mixtures, AIAA-87-1053, May, 1987
9.V.P. Chiravalle, R.B. Miles, and E.Y. Choueiri, Numerical Simulation of Microwave Sustained Supersonic Plasmas for Application to Space Propulsion, AIAA-2001-0962
10.J.E. Foster and M.J. Patterson, Microwave ECR Ion Thruster Development Activities at NASA GRC, AIAA 2002-3837
11.S.haraburda and M.Hawley, Theoretical Nozzle Performance of a Microwave Electrothermal Thruster Using Experimental Data, AIAA 92-3220, Jul. 1992
12.Sullivan, D.J. and Micci, M.M., Development of a Microwave Resonant Cavity Electrothermal Thruster Prototype, IEPC 93-036
13.D.A.Schwer and C.L.Merkle, Analysis of Microwave-heated Rocket Engines for Space Propulsion, AIAA-93-2104.
14.D.Nordling and M.M.Micci,Low-power microwave arcjet performance testing, IEPC-97-089, Aug. 1997.
15.F.J. Souliez, S.G. Chianese, etc, Low-Power Microwave Arcjet Testing: Plasma and Plume Diagnostics and Performance Evaluation, AIAA 99-2717
16.Kevin D. Diamant, John E. Brandenburg, Ronald B. Cohen and J.F. Kline, Performance Measurements of a Water Fed Microwave Electrothermal Thruster, AIAA 2001-3900
17.S. Haraburda, M..Hawley, Theoretical Nozzle Performance of a Microwave Electrothermal Thruster Using Experimental Data, AIAA 92-3110
18.D.J.Sullian and M.M.Micci, Performance testing and exhaust plume characterization of the
microwave arcjet thruster, AIAA-94-3127, Jun. 1994.
19．毛根旺，何洪庆，杨涓，空间电推进研究—MPT原理性样机研制与性能估算，中国国防科学技术报告，2001
20. D.Nordling, F. Souliez, M.M.Micci, Low-Power Microwave Arcjet Testing, AIAA 98-3499
21．杨祥林等，微波器件原理，电子工业出版社 1994．1
22．电子管设计手册编辑委员会，磁控管设计手册，国防工业出版社 1979．8
23．刘旭东主编，卫星通信技术，国防工业出版社，2000．12
24．王水平，伏敏江，开关稳压电源—原理、设计与实用电路，西安电子科技大学出版社，1997．1
25．黄昌宁，夏莹改编，晶体管电路，科学出版社 1984
26．何希才，新型开关电源设计与应用，科学出版社，2001．2
27．北京半导体器件五厂，集成开关稳压器应用手册，1992
28．唐汉，微波原理，南京大学出版社 1990．5
29．宁平治，闵德芬，微波信息传输技术，上海科学技术出版社 1985．9
30．顾茂章，张克潜，微波技术，清华大学出版社 1989
31．董树义，微波测量技术，北京理工大学出版社 1990．5
32．姚德淼，毛钩杰，微波技术基础，电子工业出版社 1989．9
33．刘胜利，现代高频开关电源实用技术，电子工业出版社 2001．9
34．梁恩主，梁恩维，PROTEL 99 SE电路设计与仿真应用，清华大学出版社 2000．11
35．刘星平，采用脉宽调制器SG3525控制的新型单相交流调压电路，机床电器，2002 No．2
36．颜世刚，张梅荣，一种AC／DC开关电源的研制，电测与仪表，2000年第3期
37．舒兴胜等，用控制磁场的方法稳定磁控管微波功率源的输出功率，真空电子技术，第1期，2000．
38．屈崑，基于虚拟仪器技术的MPT测量系统，硕士学位论文，2002．3
39．张兆镗，钟若青，微波加热技术基础，电子工业出版社 1988．10
40．吴鸿适，微波电子学原理，科学出版社，1987．9
41．方大纲，刘次由，微波理论与技术，兵器工业出版社，1987．8
42．黄晓砥，微波等离子推力器的启动与稳定工作探索研究，硕士学位论文，2001．3
43．杨世铭，传热学，高等教育出版社 1987．10
2.M.Martines-Sanchez "Spacecraft Electric Propulsion - An Overview",Journal of Propulsion and Power. Vol. 14, No.5, 1998.
3.M.M.Micci, Prospects for Microwave Heated propulsion, AIAA-84-1390, 1984.
4.D.A.Schwer and C.L.Merkle, Analysis of microwave-heated rocket engines for space propulsion, AIAA-93-2104.
5.M.C.Hawley and T.J.Morimand, Review of research and development of the microwave electrothermal thruster, AIAA-89-5620.
6.M.C.Hawley, J.S.Asmussen, J.W. Filipus, Review of research and development on the microwave electrothermal thruster, Vol.5, No.6, Nov.-Dec. 1989, pp.703-712.
7.M.R. Durbin and M.M.Micci, Analysis of a Microwave-heated Plasmas in Hydrogen、Helium and Nitrogen, AIAA paper 87-1013, May 1-3, 1987
8.W. Haag, Arcjet Stating Reliability: A Multi-star Test on Hydrogen/Nitrogen Mixtures, AIAA-87-1053, May, 1987
9.V.P. Chiravalle, R.B. Miles, and E.Y. Choueiri, Numerical Simulation of Microwave Sustained Supersonic Plasmas for Application to Space Propulsion, AIAA-2001-0962
10.J.E. Foster and M.J. Patterson, Microwave ECR Ion Thruster Development Activities at NASA GRC, AIAA 2002-3837
11.S.haraburda and M.Hawley, Theoretical Nozzle Performance of a Microwave Electrothermal Thruster Using Experimental Data, AIAA 92-3220, Jul. 1992
12.Sullivan, D.J. and Micci, M.M., Development of a Microwave Resonant Cavity Electrothermal Thruster Prototype, IEPC 93-036
13.D.A.Schwer and C.L.Merkle, Analysis of Microwave-heated Rocket Engines for Space Propulsion, AIAA-93-2104.
14.D.Nordling and M.M.Micci,Low-power microwave arcjet performance testing, IEPC-97-089, Aug. 1997.
15.F.J. Souliez, S.G. Chianese, etc, Low-Power Microwave Arcjet Testing: Plasma and Plume Diagnostics and Performance Evaluation, AIAA 99-2717
16.Kevin D. Diamant, John E. Brandenburg, Ronald B. Cohen and J.F. Kline, Performance Measurements of a Water Fed Microwave Electrothermal Thruster, AIAA 2001-3900
17.S. Haraburda, M..Hawley, Theoretical Nozzle Performance of a Microwave Electrothermal Thruster Using Experimental Data, AIAA 92-3110
18.D.J.Sullian and M.M.Micci, Performance testing and exhaust plume characterization of the
microwave arcjet thruster, AIAA-94-3127, Jun. 1994.
19．毛根旺，何洪庆，杨涓，空间电推进研究—MPT原理性样机研制与性能估算，中国国防科学技术报告，2001
20. D.Nordling, F. Souliez, M.M.Micci, Low-Power Microwave Arcjet Testing, AIAA 98-3499
21．杨祥林等，微波器件原理，电子工业出版社 1994．1
22．电子管设计手册编辑委员会，磁控管设计手册，国防工业出版社 1979．8
23．刘旭东主编，卫星通信技术，国防工业出版社，2000．12
24．王水平，伏敏江，开关稳压电源—原理、设计与实用电路，西安电子科技大学出版社，1997．1
25．黄昌宁，夏莹改编，晶体管电路，科学出版社 1984
26．何希才，新型开关电源设计与应用，科学出版社，2001．2
27．北京半导体器件五厂，集成开关稳压器应用手册，1992
28．唐汉，微波原理，南京大学出版社 1990．5
29．宁平治，闵德芬，微波信息传输技术，上海科学技术出版社 1985．9
30．顾茂章，张克潜，微波技术，清华大学出版社 1989
31．董树义，微波测量技术，北京理工大学出版社 1990．5
32．姚德淼，毛钩杰，微波技术基础，电子工业出版社 1989．9
33．刘胜利，现代高频开关电源实用技术，电子工业出版社 2001．9
34．梁恩主，梁恩维，PROTEL 99 SE电路设计与仿真应用，清华大学出版社 2000．11
35．刘星平，采用脉宽调制器SG3525控制的新型单相交流调压电路，机床电器，2002 No．2
36．颜世刚，张梅荣，一种AC／DC开关电源的研制，电测与仪表，2000年第3期
37．舒兴胜等，用控制磁场的方法稳定磁控管微波功率源的输出功率，真空电子技术，第1期，2000．
38．屈崑，基于虚拟仪器技术的MPT测量系统，硕士学位论文，2002．3
39．张兆镗，钟若青，微波加热技术基础，电子工业出版社 1988．10
40．吴鸿适，微波电子学原理，科学出版社，1987．9
41．方大纲，刘次由，微波理论与技术，兵器工业出版社，1987．8
42．黄晓砥，微波等离子推力器的启动与稳定工作探索研究，硕士学位论文，2001．3
43．杨世铭，传热学，高等教育出版社 1987．10