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Experimental results indicate that there exist two stable discharge operation points in a self-excited mode Hall effect thruster. During the operation, the discharge operation point jumps to and fro between two values, which greatly influences the physical process of plasma discharge in the thruster channel and the comprehensive performance of thrusters. In this paper, by using the relationship between discharge magneto-ampere characteristic curve and magnetic field coil current curve, we propose the physical mechanism of forming the discharge bistable characteristic. On the basis of the mechanism, a method of stabilizing the single discharge operation point is presented through changing the slope of magnetic field coil current curve. The physical explanation is given through established one-dimensional dynamic fluid model for self-excited mode, and the results are approved by the self-excited experiment.
[1] Morozov A I, Savelyev V V 2000 Reviews of Plasma Physics (Volume 21) (New York: Plenum Publishers) 210
[2] 59 7201]
[3] 江滨浩, 徐殿国 2010 59 8676]
[4] Zhurin V V, Kaufman H R, Robinson R S 1999 Plasma Sources Sci. Technol. 8 R15
[5] Liu H, Wu B Y, E P, Duan P 2010 Acta Phys. Sin. 59 7201 (in Chinese) [刘辉, 吴勃英, 鄂鹏, 段萍 2010
[6] Walker M L R, Gallimore A D 2007 Journal of Propulsion and Power 23 528
[7] Linnell J A, Gallimore A D 2006 Journal of Propulsion and Power 22 1402
[8] Book C F, Walker M L R 2010 Journal of Propulsion and Power 26 1036
[9] Ross J L, Sommerville J D, King L B 2010 Journal of Propulsion and Power 26 1312
[10] E P, Duan P, Wei L Q, Bai D Y, Jiang B H, Xu D G 2010 Acta Phys. Sin. 59 8676 (in Chinese) [鄂鹏, 段萍, 魏立秋, 白德宇,
[11] Hruby V, Pote B, Gamero-Castano M, Kolencik G, Byrne L, Tedrake R, Delichatsios M 2001 27th International Electric Propulsion Conference, Pasadena, CA, October 15–19, 2001 IEPC-01-66
[12] Gray H, Provost S, Glogowski M, Demaire A 2005 29th International Electric Propulsion Conference, Princeton University, October 31–November 4, 2005 IEPC-2005-082
[13] Yamamoto N, Komurasaki K, Arakawa Y 2005 Journal of Propulsion and Power 21 870
[14] Tamida T, Nakagawa T, Suga I, Osuga H, Ozaki T, Matsui 2007 Journal of Applied Physics 102 043304 Study on the mechanism of Hall effect thruster
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[1] Morozov A I, Savelyev V V 2000 Reviews of Plasma Physics (Volume 21) (New York: Plenum Publishers) 210
[2] 59 7201]
[3] 江滨浩, 徐殿国 2010 59 8676]
[4] Zhurin V V, Kaufman H R, Robinson R S 1999 Plasma Sources Sci. Technol. 8 R15
[5] Liu H, Wu B Y, E P, Duan P 2010 Acta Phys. Sin. 59 7201 (in Chinese) [刘辉, 吴勃英, 鄂鹏, 段萍 2010
[6] Walker M L R, Gallimore A D 2007 Journal of Propulsion and Power 23 528
[7] Linnell J A, Gallimore A D 2006 Journal of Propulsion and Power 22 1402
[8] Book C F, Walker M L R 2010 Journal of Propulsion and Power 26 1036
[9] Ross J L, Sommerville J D, King L B 2010 Journal of Propulsion and Power 26 1312
[10] E P, Duan P, Wei L Q, Bai D Y, Jiang B H, Xu D G 2010 Acta Phys. Sin. 59 8676 (in Chinese) [鄂鹏, 段萍, 魏立秋, 白德宇,
[11] Hruby V, Pote B, Gamero-Castano M, Kolencik G, Byrne L, Tedrake R, Delichatsios M 2001 27th International Electric Propulsion Conference, Pasadena, CA, October 15–19, 2001 IEPC-01-66
[12] Gray H, Provost S, Glogowski M, Demaire A 2005 29th International Electric Propulsion Conference, Princeton University, October 31–November 4, 2005 IEPC-2005-082
[13] Yamamoto N, Komurasaki K, Arakawa Y 2005 Journal of Propulsion and Power 21 870
[14] Tamida T, Nakagawa T, Suga I, Osuga H, Ozaki T, Matsui 2007 Journal of Applied Physics 102 043304 Study on the mechanism of Hall effect thruster
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