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Thrust density distribution of ion thruster is an important factor that affects the orbit correction and station keeping of the spacecraft. Current empirical models mainly concern themselves with the overall thrust of the ion thruster, yet the thrust density distribution has not been fully understood. Hence it is necessary to investigate the thrust density characteristics of the ion thruster to devise the approach to optimizing the thruster performances. In this study, the thrust density characteristics of the ion thruster is analyzed and discussed by combining the empirical and theoretical methods. An ion thruster utilizes biased grids to extract ions from discharge chamber and accelerate them to high velocities, thereby forming a beam and generating thrust. In this paper, we analyze the working process of the ion thruster. The thrust expression as a function of beam micro-particle parameters is presented. Meanwhile the transport process of the plasma in the beam stream is simulated by the particle in cell-Monte Carlo (PIC-MCC) method for two-grid optics. The motion behavior of ions is modeled by the PIC method, while the collisions of particles are modeled by the MCC method. In the simulation, the particle trajectories are traced and the micro information about ejected charged ions is recorded with respect to singly charged ion, doubly charged ion and charge exchanged (CEX) ion. By analyzing the density and axial velocity of the charged particles in the beam stream, the thrust of the beam from a single grid hole can be calculated, based on which the thrust distribution of the thruster can be inferred by considering the distribution of plasma density at the exit of discharge chamber. Moreover, the above theoretical analysis of the thrust density is tested experimentally. The studies show that the thrust contribution percentages of the singly charged ion, doubly charged ion and CEX ion in the beam current are 84.63%, 15.35%, and 1.82%, respectively. Apparently, the main contributions to the thrust are made by the singly charged ions and doubly charged ions in the beam plasma, while the CEX ions have a trivial effect on the variation of the thrust. The distribution of the thrust density shows good symmetry along the central axis and it levels off after a fast decline in the radial direction. Comparisons of empirical and numerical results with the experimental results show that the empirical results have an error of about 4.1% and the numerical results have an error of about 2.8%. This indicates that the computational accuracy of our numerical model is better than that of the empirical model This work provides a reference for optimizing the thrust density uniformity of an ion thruster.
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Keywords:
- ion thruster /
- beam /
- thrust density /
- numerical simulation
[1] Burak K K, Deborah A L 2017 J. Propul. Power 33 264
[2] Li J X, Wang Z H, Zhang Y B, Fu H M, Liu C R, Krishnaswamy S 2016 J. Propul. Power 32 948
[3] Zhang T P, Wang X Y, Jiang H C 2013 Presented at the 33th International Electric Propulsion Conference Washington, USA, October 6-10, 2013 p2013-48-1
[4] Zhou Z C, Gao J 2015 Spacecraft Engineer. 24 6 (in Chinese)[周志成, 高军 2015 航天器工程 24 6]
[5] Williams L T, Walker M L R 2014 J. Propul. Power 30 645
[6] Yamamoto N, Tomita K, Yamasaki N, Tsuru T, Ezaki T, Kotani Y, Uchino K, Nakashima H 2010 Plasma Sources Sci. T. 19 045009
[7] Brophy J R, Wilbur P J 1985 AIAA J. 23 1731
[8] Takao Y, Miyamoto T, Yamawaki K, Maeyama T, Nakashima H 2002 Vacuum 65 361
[9] Goebel D M, Wirz R E, Katz I 2007 J. Propul. Power 23 1055
[10] Kitamura S, Miyazaki K, Hayakawa Y, Yoshida H, Akai K 2003 Acta Astronaut 52 20
[11] Hruby V, Martinez-Sanchez M, Bates S, Lorents D 1994 25th AIAA Plasmadynamics and Lasers Conference Colorado, USA June 20-23, 1994 p94-2466-1
[12] Bramanti C, Izzo D, Samaraee T, Walker R, Fearn D 2009 Acta Astronaut 64 735
[13] Walker R, Bramanti C 2006 42nd AIAA/ASME/SAE/ ASEE Joint Propulsion Conference Exhibit California USA, July 9-12, 2006 p2006-4669-1
[14] Sovey J S, Rawlin V K, Patterson M J 2001 J. Propul. Power 17 517
[15] Chen J J, Zhang T P, Jia Y H, Li X P 2012 High Power Laser and Particle Beams 24 2469 (in Chinese)[陈娟娟, 张天平, 贾艳辉, 李小平 2012 强激光与粒子束流 24 2469]
[16] Yasutaka I, Toshiyuki O 2001 Presented at the 27th International Electric Propulsion Conference Pasadena, USA, October 15-19, 2001 p01-101-1
[17] Chen M L, Xia G Q, Mao G W 2014 Acta Phys. Sin. 63 182901 (in Chinese)[陈茂林, 夏广庆, 毛根旺 2014 物理学报 63 182901]
[18] Ren J X, Li J, Xie K 2013 Plasma Sci. Technol. 15 702
[19] Li J, Chu Y C, Cao Y 2012 J. Propul. Technol. 33 131 (in Chinese)[李娟, 楚豫川, 曹勇 2012 推进技术 33 131]
[20] Chen M L, Xia G Q, Xu Z J, Mao G W 2015 Acta Phys. Sin 64 094104 (in Chinese)[陈茂林, 夏广庆, 徐宗琦, 毛根旺 2015 物理学报 64 094104]
[21] Zhou Z C, Wang M, Zhong X Q, Chen J J, Zhang T P 2015 Chin. J. Vacuum Sci. Technol. 35 1088 (in Chinese)[周志成, 王敏, 仲小清, 陈娟娟, 张天平 2015 真空科学与技术学报 35 1088]
[22] Herman D A, Gallimore A D 2013 Presented at the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Joint Propulsion Conferences Florida USA, July 11-14, 2013 pp2004-3958
[23] Zheng M F, Jiang H C 2011 J. Propul. Technol. 32 762 (in Chinese)[郑茂繁, 江豪成 2011 推进技术 32 762]
[24] Jia Y H, Zhang T P, Zheng M F, Li X K 2012 J. Propul. Technol. 33 991 (in Chinese)[贾艳辉, 张天平, 郑茂繁, 李兴坤 2012 推进技术 33 991]
[25] Zhang Z, Tang H B, Ren J X, Zhang Z, Wang J 2016 Rev. Sci. Instrum. 87 113502
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[1] Burak K K, Deborah A L 2017 J. Propul. Power 33 264
[2] Li J X, Wang Z H, Zhang Y B, Fu H M, Liu C R, Krishnaswamy S 2016 J. Propul. Power 32 948
[3] Zhang T P, Wang X Y, Jiang H C 2013 Presented at the 33th International Electric Propulsion Conference Washington, USA, October 6-10, 2013 p2013-48-1
[4] Zhou Z C, Gao J 2015 Spacecraft Engineer. 24 6 (in Chinese)[周志成, 高军 2015 航天器工程 24 6]
[5] Williams L T, Walker M L R 2014 J. Propul. Power 30 645
[6] Yamamoto N, Tomita K, Yamasaki N, Tsuru T, Ezaki T, Kotani Y, Uchino K, Nakashima H 2010 Plasma Sources Sci. T. 19 045009
[7] Brophy J R, Wilbur P J 1985 AIAA J. 23 1731
[8] Takao Y, Miyamoto T, Yamawaki K, Maeyama T, Nakashima H 2002 Vacuum 65 361
[9] Goebel D M, Wirz R E, Katz I 2007 J. Propul. Power 23 1055
[10] Kitamura S, Miyazaki K, Hayakawa Y, Yoshida H, Akai K 2003 Acta Astronaut 52 20
[11] Hruby V, Martinez-Sanchez M, Bates S, Lorents D 1994 25th AIAA Plasmadynamics and Lasers Conference Colorado, USA June 20-23, 1994 p94-2466-1
[12] Bramanti C, Izzo D, Samaraee T, Walker R, Fearn D 2009 Acta Astronaut 64 735
[13] Walker R, Bramanti C 2006 42nd AIAA/ASME/SAE/ ASEE Joint Propulsion Conference Exhibit California USA, July 9-12, 2006 p2006-4669-1
[14] Sovey J S, Rawlin V K, Patterson M J 2001 J. Propul. Power 17 517
[15] Chen J J, Zhang T P, Jia Y H, Li X P 2012 High Power Laser and Particle Beams 24 2469 (in Chinese)[陈娟娟, 张天平, 贾艳辉, 李小平 2012 强激光与粒子束流 24 2469]
[16] Yasutaka I, Toshiyuki O 2001 Presented at the 27th International Electric Propulsion Conference Pasadena, USA, October 15-19, 2001 p01-101-1
[17] Chen M L, Xia G Q, Mao G W 2014 Acta Phys. Sin. 63 182901 (in Chinese)[陈茂林, 夏广庆, 毛根旺 2014 物理学报 63 182901]
[18] Ren J X, Li J, Xie K 2013 Plasma Sci. Technol. 15 702
[19] Li J, Chu Y C, Cao Y 2012 J. Propul. Technol. 33 131 (in Chinese)[李娟, 楚豫川, 曹勇 2012 推进技术 33 131]
[20] Chen M L, Xia G Q, Xu Z J, Mao G W 2015 Acta Phys. Sin 64 094104 (in Chinese)[陈茂林, 夏广庆, 徐宗琦, 毛根旺 2015 物理学报 64 094104]
[21] Zhou Z C, Wang M, Zhong X Q, Chen J J, Zhang T P 2015 Chin. J. Vacuum Sci. Technol. 35 1088 (in Chinese)[周志成, 王敏, 仲小清, 陈娟娟, 张天平 2015 真空科学与技术学报 35 1088]
[22] Herman D A, Gallimore A D 2013 Presented at the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Joint Propulsion Conferences Florida USA, July 11-14, 2013 pp2004-3958
[23] Zheng M F, Jiang H C 2011 J. Propul. Technol. 32 762 (in Chinese)[郑茂繁, 江豪成 2011 推进技术 32 762]
[24] Jia Y H, Zhang T P, Zheng M F, Li X K 2012 J. Propul. Technol. 33 991 (in Chinese)[贾艳辉, 张天平, 郑茂繁, 李兴坤 2012 推进技术 33 991]
[25] Zhang Z, Tang H B, Ren J X, Zhang Z, Wang J 2016 Rev. Sci. Instrum. 87 113502
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