Extending the range of SPT operation - Development status of 300 and 4500 W thruster

Arkhipov, B. A.; Bober, A.; Day, M. L.; Gnizdor, R. Yu.; Kozubsky, K. N.; Maslennikov, N.

doi:10.2514/6.1996-2708

Cited by 12 publications

(9 citation statements)

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“…These range from sub-kW thrusters for small satellites, to 1.5 kW thrusters for station-keeping, to high power thrusters for orbit raising/transfer applications. [1][2][3][4] While a number of Hall thrusters have been, or are in the process of being, flight qualified 5,6 many of the basic physical processes inside the Hall thruster are still not fully understood. In order to improve the performance of the next generation of thrusters, as well as to address spacecraft interaction issues, the ionization and acceleration mechanisms inside the discharge chamber of the Hall thruster must be better understood.…”

Section: Introductionmentioning

confidence: 99%

Internal plasma potential profiles in a laboratory-model Hall thruster

2001

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The Plasmadynamics and Electric Propulsion Laboratory High-speed Axial Reciprocating Probe system is used in conjunction with a floating emissive probe to measure plasma potential in the discharge chamber of the P5 Hall thruster. Plasma potential measurements are made at a constant voltage, 300 V, at two different discharge current conditions: 5.4 and 10 A. The plasma potential contours for the 5.4 A case indicate that the acceleration region begins several millimeters upstream of the exit plane, extends several centimeters downstream, and is uniform across the width of the discharge chamber. The 10 A case is similar to the 5.4 A case with the exception that the acceleration region is shifted downstream on centerline. Axial electric field profiles, computed from the measured potential, show a double peak structure in the 5.4 A case, indicating a zone of ion deceleration. Perturbations to the discharge current are shown to correspond spatially with the location of the peak electric field indicating that thruster perturbations may result from a disturbance to the Hall current, as opposed to ablation of probe material. This conclusion is supported by the lack of any observable material ablation.

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Section: Introductionmentioning

confidence: 99%

Internal plasma potential profiles in a laboratory-model Hall thruster

2001

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“…UT-1 kW HET [55] ---.690 ≈9.0 BN 42 SPT-70 [6] ≥3,000 ×, ‡ --.660 3.6 [56] borosil, BGP-10 [56] -, <60 [56] BHT-600 [15] >932 932 -.615 ≈3.6 [57] HBC BN 5.3 [57] SPT-50 [13] ≥2,500 × 825 -.320 -borosil 50-100 KM-45 [14] 3,500-4,000 1,020 3,500-4,000 * .310 4.1 -10-20 KM-32 [2] 3,000 ‡ 500 2,000-3,000 * .200 5.2 HP BN 23, 12 BHT-200 [15] >1,700 ‡ >1,700…”

Section: -50mentioning

confidence: 99%

“…A more complete summary of Hall thruster erosion measurements is provided in Table 4. SPT-50 [13] 320 47% >2,500 × -KM-45 [14] 310 40-50% [1] 3,500-4,000 -KM-32 [2] 200 30-40% 2,000-3,000 3,000 * BHT-200 [15] 200 43.5% 1,287-1,519 >1,700 HT-100 [16] 175 25% [4] 300 [17] 1,500 [17] * * SPT-30 [18] 150 26% [19] 600 * -SPT-20M [20] <100 ≤38% [5] 594-910 4,000…”

Section: Introductionmentioning

confidence: 99%

Erosion Measurements in a Low-Power Cusped-Field Plasma Thruster

Gildea

Matlock

Martı́nez-Sánchez

et al. 2013

Journal of Propulsion and Power

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“…The direction of the magnetic field at the exit of the Hall thruster channel is perpendicular to the wall, and the potential lines are bent in the direction of the outlet of the channel, resulting in a larger divergence angle of the plume and serious corrosion of the channel wall, which eventually reduces the service life [5][6][7]. In view of the above, scientists proposed many ways to improve the performance of thrusters, such as changing the electromagnetic field configuration, the design of a reasonable channel size, optimizing the wall materials and so on, these methods are also been investigated by PIC simulation [8][9][10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

Study on the influences of ionization region material arrangement on Hall thruster channel discharge characteristics

Duan

SONG

et al. 2017

Plasma Sci. Technol.

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There exists strong interaction between the plasma and channel wall in the Hall thruster, which greatly affects the discharge performance of the thruster. In this paper, a two-dimensional physical model is established based on the actual size of an Aton P70 Hall thruster discharge channel. The particle-in-cell simulation method is applied to study the influences of segmented low emissive graphite electrode biased with anode voltage on the discharge characteristics of the Hall thruster channel. The influences of segmented electrode placed at the ionization region on electric potential, ion number density, electron temperature, ionization rate, discharge current and specific impulse are discussed. The results show that, when segmented electrode is placed at the ionization region, the axial length of the acceleration region is shortened, the equipotential lines tend to be vertical with wall at the acceleration region, thus radial velocity of ions is reduced along with the wall corrosion. The axial position of the maximal electron temperature moves towards the exit with the expansion of ionization region. Furthermore, the electron-wall collision frequency and ionization rate also increase, the discharge current decreases and the specific impulse of the Hall thruster is slightly enhanced.

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Extending the range of SPT operation - Development status of 300 and 4500 W thruster

Cited by 12 publications

References 0 publications

Internal plasma potential profiles in a laboratory-model Hall thruster

Internal plasma potential profiles in a laboratory-model Hall thruster

Erosion Measurements in a Low-Power Cusped-Field Plasma Thruster

Study on the influences of ionization region material arrangement on Hall thruster channel discharge characteristics

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