1,000-hours Demonstration of a 6-kW-class Hall Thruster for All-Electric Propulsion Satellite

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

doi:10.2322/tastj.17.589

Cited by 5 publications

(1 citation statement)

References 17 publications

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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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Section: Introductionmentioning

confidence: 99%

Control algorithm for a 6 kW hall thruster

et al. 2022

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Comparative analysis of several electric propulsion systems that can be used as propulsion systems for mini/micro satellites

Jiang

Sun

Wei

et al. 2021

2021 IEEE 4th International Electrical and Energy Conference (CIEEC)

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Control Algorithm for 6 kW Hall Thruster

Matsunaga

Watanabe

Cho

et al. 2022

Preprint

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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. Discharge oscillation control decreased the number of 0.1 ms segments with amplitudes exceeding 1.5 A from 700 to 0 by changing the coil current. 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%.

show abstract

1,000-hours Demonstration of a 6-kW-class Hall Thruster for All-Electric Propulsion Satellite

Cited by 5 publications

References 17 publications

Control algorithm for a 6 kW hall thruster

Control algorithm for a 6 kW hall thruster

Comparative analysis of several electric propulsion systems that can be used as propulsion systems for mini/micro satellites

Control Algorithm for 6 kW Hall Thruster

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