Development of a 6-kW-class Hall thruster for geostationary missions

Funaki, Ikkoh; Cho, Shinatora; Sano, Tadahiko; Fukatsu, Tsutomu; Tashiro, Yosuke; Shiiki, Taizo; Nakamura, Yoichiro; Watanabe, Hiroki; Kubota, Kei; Matsunaga, Yoshio; Fuchigami, Kenji

doi:10.1016/j.actaastro.2019.08.029

Cited by 17 publications

(2 citation statements)

References 10 publications

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“…[1][2][3][4][5] In particular, the Japan Aerospace Exploration Agency (JAXA) is developing Engineering Test Satellite-9 (ETS-9), for which a 6-kW-class Hall-effect thruster is under development. This thruster achieved a high thrust level of 392 mN with a specific impulse of 1,940 s. 6) A hollow cathode is utilized as the neutralizer of this ion-emitting Hall-effect thruster; and therefore, the development of a high-current hollow cathode is critically important for achieving high power. Hall-effect thrusters generally create plasma by ionizing the introduced precursor gas with electrons emitted from a low-workfunction material (i.e., thermionic emitter).…”

Section: Introductionmentioning

confidence: 99%

The Effect of Discharge Mode on Ion Energy and Plasma Potential in the Plume Plasma Region

Imai

Imaguchi

Watanabe

et al. 2022

Trans. Japan Soc. Aero. S Sci.

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The ion energy angle distribution and its relationship to plasma parameters for spot and plume modes are elucidated for a LaB 6 hollow cathode with a radiative heater. Measurements were conducted using a retarding potential analyzer (RPA) and a single Langmuir probe. The ion energy distribution function (IEDF) characteristics showed different tendencies in the current density and mass flow-rate dependence under different plasma modes. The IEDF peak potential for the spot mode varied from 16 to 23 V with increasing current density, and the IEDF peak potential for the plume mode varied from 16 to 32 V with decreasing mass flow rate. Considering angle dependency of ion energy, when the observation angle was changed from the radial direction to the axial direction, the IEDF peak potential increased from 29 to 40 V for the plume mode (10 A, 10 sccm) and increased slightly from 16 to 18 V for the spot mode (20 A, 30 sccm). The probe measurement analysis revealed that the IEDF peak energies are the same as, or exceed, the plasma potential and have a qualitative correlation with the electron temperature spatial distribution.

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Section: Introductionmentioning

confidence: 99%

The Effect of Discharge Mode on Ion Energy and Plasma Potential in the Plume Plasma Region

Imai

Imaguchi

Watanabe

et al. 2022

Trans. Japan Soc. Aero. S Sci.

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“…Hall thrusters are candidates for future mission applications [1][2][3][4][5][6][7][8]. The Japan Aerospace Exploration Agency (JAXA) is developing a 6 kW Hall thruster that will be demonstrated on the Engineering Test Satellite-9 (ETS-9) [9][10][11][12][13][14][15][16]. A further requirement for Hall thrusters in future missions is a high-thrust mode and a high speci c impulse (Isp) mode.…”

Section: Introductionmentioning

confidence: 99%

Control algorithm for a 6 kW hall thruster

et al. 2022

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This paper presents a control algorithm for ensuring the stable operation of a 6 kW Hall thruster. The Japan Aerospace Exploration Agency is developing a “wide-range” power processing unit (PPU) to power a 6 kW Hall thruster system, a candidate for all-electric satellites. The PPU provides discharge oscillation, power, and discharge current control. The increments in the control loop are fixed, so the PPU digital controller does not need to calculate them, and the algorithm’s computational complexity is minimal. Results of integration tests on the 6 kW Hall thruster and the PPU breadboard model showed that the three control functions run correctly. The total controlled PPU power was adjusted in the range of 3.45–3.55 kW under constant power control with a target of 3.5 kW. Oscillations of ± 0.05 kW around the target power are acceptable. 70% of the peaks in the discharge current acquired for 100 ms exceeded the limit of 1.5A. Discharge oscillation control varied the coil magnetic field and reduced them to 0%. The PPU successfully controlled the coil current, reducing the discharge current from 13.7 A to 13 A. The propulsion efficiency increased from 59% to 60.5%.

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