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With the rapid development of commercial space in recent years, the low-power and low-cost propulsion systems are needed more and more urgently. Compared with conventional chemical propulsion, electric propulsion has a higher specific impulse. Compared with the conventional xenon propellant, iodine propellant that does not require high pressure storage, is cheap and close to the relative atomic mass and ionization energy of xenon. Electron cyclotron resonance source has the advantages of no internal electrode, low pressure ionization, high plasma density and compact structure, which is suitable for low power electric propulsion. Therefore, the study of low power iodine propellant electron cyclotron resonance plasma source is of great significance. In this study, a set of corrosion-resistant feed system with balanced and stable output of iodine vapor is designed. Then the iodine-corrosion-resistant electron cyclotron resonance thruster is designed completely. A corrosion-resistant coaxial cavity structure is used to feed the microwave to the thruster, and the channel magnetic field is changed into a cusped field to generate more electron cyclotron resonance (ECR) layers. Finally, the combined ignition experiment is successfully conducted, showing the first plasma source using electron cyclotron resonance to ionize iodine propellant that can be used for electric propulsion in the world. The analyses of experiments, static magnetic field, microwave electric field distribution show that the unstable plasma plume scintillation at low power and low flow is caused by the conversion between ordinary wave electron plasmon resonance heating mode and extraordinary wave electron cyclotron resonance heating mode. The decrease of ionization rate at a high flow rate is caused by electron loss, wall loss and electronegativity of iodine propellant. Based on this principle, an improvement scheme is proposed. The plasma source has no obvious damage after discharge, which indicates that it has the potential of long life. This work preliminarily proves that the low power electron cyclotron resonance electric propulsion scheme of low power iodine propellant is feasible.
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Keywords:
- electric propulsion /
- iodine propellant /
- feed system /
- electron cyclotron resonance plasma source
[1] Heidt H, Puig-Suari J, Moore A S, Nakasuka S, Twiggs R J 2000 Proceedings of the 14th Annual/USU Conference on Small Satellites Logan, August 21–24, 2000 SSC00-V-5
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Shen Y J 2010 M. S. Thesis (Harbin: Harbin Institute of Technology
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Google Scholar
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Google Scholar
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Google Scholar
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Google Scholar
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图 2 ECR等离子体源实物图(a)及原理图(b)
Figure 2. Photo of microwave plasma source (a) and schematic diagram (b).
图 3 等离子体源磁感应强度分布
Figure 3. Magnetic induction intensity distribution of plasma source.
图 4 ECR层中微波电场垂直分量(E⊥)的分布图. 图中白线表示磁场线, 黄色箭头表示微波电场线
Figure 4. Distribution diagram of microwave electric field vertical component (E⊥) in ECR layer. The white lines represent magnetic field lines and the yellow arrows represent microwave electric field lines.
图 5 碘等离子体源系统示意图
Figure 5. Diagram of iodine plasma source system.
图 6 碘工质贮供系统实物图(a)和流量标定示意图(b)
Figure 6. Physical picture of iodine feed system (a) and schematic diagram of flow calibration (b).
图 7 耐碘腐蚀真空试验平台
Figure 7. Iodine corrosion resistance vacuum test platform.
图 8 探针诊断电路和探针位置示意图, 其中包括法拉第探针和RPA
Figure 8. Probe diagnostic circuits and schematic view of the probe positions, including a Faraday probe and RPA.
图 9 碘罐温度与质量流量关系拟合曲线
Figure 9. Iodine tank temperature and mass flow fitting curve.
图 10 碘工质ECR等离子体源放电图像
Figure 10. Image of iodine propellant microwave plasma source discharge.
图 11 在低流量低功率下, 等离子体源羽流闪烁过程 (a)离子电流密度随时间变化; (b)羽流闪烁过程的图像
Figure 11. Plasma source plume scintillation process at low flow and low power: (a) Change of ion current density with time; (b) image of plume scintillation process.
图 12 离子电流密度分布
Figure 12. Ion current density distribution.
图 13 工质利用率
Figure 13. Utilization rate of propellant.
图 14 不同流量下的离子能量分布
Figure 14. Ion energy distribution at different flow rates.
图 15 不同功率下的离子能量分布
Figure 15. Ion energy distribution at different power levels.
图 16 在微波功率为10 W、质量流量为0.52 mg/s的条件下, 0°—90°内的时间平均离子能量角分布图
Figure 16. Contour maps of the time-averaged ion energy angle distribution from 0 to 90° with a 10 W MW power, and 0.52 mg/s mass flow rate.
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[1] Heidt H, Puig-Suari J, Moore A S, Nakasuka S, Twiggs R J 2000 Proceedings of the 14th Annual/USU Conference on Small Satellites Logan, August 21–24, 2000 SSC00-V-5
[2] 许亮亮, 蔡明辉, 杨涛, 韩建伟 2020 69 165203
Google Scholar
Xu L L, Cai M H, Yang T, Han J W 2020 Acta Phys. Sin. 69 165203
Google Scholar
[3] Poghosyan A, Golkar A 2017 Prog. Aero. Sci. 88 59
Google Scholar
[4] Tsay M, Model J, Barcroft C, Frongillo J, Zwahlen J, Feng C 2017 Proceedings of the 35th International Electric Propulsion Conference Atlanta, USA, October 8–12, 2017 IEPC-2017-264
[5] Hillier A, Branam R, Huffman R, Szabo J, Paintal S 2011 Proceedings of the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition Orlando, Florida, January 4–7, 2011 AIAA-2011-524
[6] Dankanich J W, Calvert D, Kamhawi H, Hickman T, Szabo J, Byrne L 2015 Proceedings of the 34th International Electric Propulsion Conference Kobe-Hyogo, July 4–10, 2015 IEPC-2015-303
[7] Polzin K A, Seixal J F, Mauro S L, Burt A O, Martinez A, Martin A K 2017 Proceedings of the 35th International Electric Propulsion Conference Atlanta, Georgia, October 8–12, 2017 IEPC-2017-11
[8] Szabo J, Robin M, Paintal S, Pote B, Hruby V, Freeman C 2013 Proceedings of the 33th International Electric Propulsion Conference Washington, D. C., October 6–10, 2013 IEPC-2013-311
[9] Tsay M, Frongillo J, Hohman K 2015 Proceedings of the 34th International Electric Propulsion Conference Hyogo-Kobe, July 4–10, 2015 IEPC-2015-273
[10] Rafalskyi D, Martínez J M, Habl L, Rossi E Z, Proynov P, Boré A, Baret T, Poyet A, Lafleur T, Dudin S, Aanesland A 2021 Nature 599 411
Google Scholar
[11] Manente M, Trezzolani F, Mantellato R, Scalzi D, Schiavon A, Souhair N, Duzzi M, Barato F, Cappellini L, Barbato A, Paulon D, Selmo A, Bellomo N, Gloder A, Toson E, Minute M, Magarotto M, Pavarin D 2019 Proceedings of the 36th International Electric Propulsion Conference Vienna, September 15–20, 2019 IEPC-2019-417
[12] Manente M, Trezzolani F, Mantellato R, Scalzi D, Schiavon A, Cappellini L, Barato F, Bellomo N, Gloder A, Toson E, Minute M, Vallisari D, Magarotto M, Pavarin D 2019 Proceedings of the 36th International Electric Propulsion Conference Vienna, September 15–20, 2019 IEPC-2019-419
[13] Bellomo N, Magarotto M, Manente M, Trezzolani F, Mantellato R, Cappellini L, Paulon D, Selmo A, Scalzi D, Minute M, Duzzi M, Barbato A, Schiavon A, Fede S D, Souhair N, Carlo P D, Barato F, Milza F, Toson E, Pavarin D 2022 CEAS Space J. 14 79
Google Scholar
[14] Szabo1 J, Pote B, Paintal S, Robin M, Hillier A, Branam R D, Huffman R E 2012 J. Propul. Power 28 848
Google Scholar
[15] Dankanich J W, Szabo J, Pote B, Oleson S, Kamhawi H 2014 Proceedings of the 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference Cleveland, July 28–30, 2014 AIAA-2014-3905
[16] Tsay M, Frongillo J, Hohman K, Malphrus B K 2015 Proceedings of the 29th AIAA/USU Conference on Small Satellites Logan, August 9, 2015 SSC15-XI-1
[17] Yang J H, Jia S X, Zhang Z H, Zhang X H, Jin T, Li L, Cai Y, Cai J 2020 Plasma Sci. Technol. 22 094006
Google Scholar
[18] 申英杰 2010 硕士学位论文(哈尔滨: 哈尔滨工业大学)
Shen Y J 2010 M. S. Thesis (Harbin: Harbin Institute of Technology
[19] Shuaibov A K, Grabovaya I A, Gomoki Z T, Kalyuzhnaya A G, Shchedrin A I 2009 Tech. Phys. 54 1819
Google Scholar
[20] Matsutani A, Ohtsuki H, Koyama F 2005 Jpn. J. Appl. Phys. 44 L576
Google Scholar
[21] Fehsenfeld F C, Evanson K M, Broida H P 1965 Rev. Sci. Instrum. 36 294
Google Scholar
[22] Hawley M C, Asmussen J, Filpus J W, Whitehair S, Hoekstra C, Morin T J, Chapman R 1989 J. Propul. Power 5 703
Google Scholar
[23] Agnihotri A N, Kelkar A H, Kasthurirangan S, Thulasiram K V, Desai C A, Fernandez W A, Tribedi L C 2011 Phys. Scr. T144 014038
Google Scholar
[24] Biri S, Rácz R, Pálinkás J 2012 Rev. Sci. Instrum. 83 02A341
Google Scholar
[25] Hargus W A, Lubkeman J S, Remy K E, Gonzales A E 2012 Proceedings of the 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Atlanta, Georgia, July 30–August 1, 2012 AIAA-2012-4316
[26] Leins M, Kopecki J, Gaiser S, Schulz A, Walker M, Schumacher U, Stroth U, Hirth T 2014 Contrib. Plasma Phys. 54 14
Google Scholar
[27] Koizumi H, Kuninaka H 2011 Proceedings of the 32nd International Electric Propulsion Conference Wiesbaden, September 11–15, 2011 IEPC-2011-297
[28] Désangles V, Packan D, Jarrige J, Peterschmitt S, Dietz P, Scharmann S, Holste K, Klar P 2022 Proceedings of the 37th International Electric Propulsion Conference Cambridge, June 19–23, 2022 IEPC-2022-513
[29] Fu S H, Ding Z F 2021 Phys. Plasmas 28 033510
Google Scholar
[30] Zeng M, Liu H, Chen Z Q, Huang H Y, Yu D R 2021 Vacuum 192 110486
Google Scholar
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