Background Pressure Effects on Ion Velocity Distribution Within a Medium-Power Hall Thruster

2011 ◽  
Vol 27 (4) ◽  
pp. 737-743 ◽  
Author(s):  
Michael R. Nakles ◽  
William A. Hargus
Keyword(s):  
Velocity Distribution ◽  
Pressure Effects ◽  
Hall Thruster ◽  
Ion Velocity

Time-resolved ion velocity distribution in a cylindrical Hall thruster: Heterodyne-based experiment and modeling

2015 ◽  
Vol 86 (3) ◽  
pp. 033506 ◽  
Author(s):  
A. Diallo ◽  
S. Keller ◽  
Y. Shi ◽  
Y. Raitses ◽  
S. Mazouffre
Keyword(s):  
Velocity Distribution ◽  
Hall Thruster ◽  
Time Resolved ◽  
Ion Velocity

scholarly journals Background Pressure Effects on Ion Velocity Distributions in an SPT-100 Hall Thruster

2019 ◽  
Vol 35 (2) ◽  
pp. 403-412 ◽  
Author(s):  
Natalia MacDonald-Tenenbaum ◽  
Quinn Pratt ◽  
Michael Nakles ◽  
Nickolas Pilgram ◽  
Michael Holmes ◽  
...  
Keyword(s):  
Pressure Effects ◽  
Hall Thruster ◽  
Ion Velocity

scholarly journals Background Pressure Effects on the Performance of a 20 kW Magnetically Shielded Hall Thruster Operating in Various Configurations

Aerospace ◽  
2021 ◽  
Vol 8 (3) ◽  
pp. 69
Author(s):  
Antonio Piragino ◽  
Farbod Faraji ◽  
Maryam Reza ◽  
Eugenio Ferrato ◽  
Annalisa Piraino ◽  
...  
Keyword(s):  
Mass Flow ◽  
Discharge Current ◽  
Pressure Effects ◽  
Hall Thruster ◽  
Physical Processes ◽  
Linear Behavior ◽  
Mass Flow Rates ◽  
Anode Mass ◽  
Lower Background ◽  
Operating Regimes

The paper reports the characterization results of a 20 kW-class magnetically shielded Hall thruster in three different configurations and operating with a centrally mounted cathode. The characterization was carried out at two different pumping speeds in SITAEL’s IV10 vacuum chamber, resulting in two different background pressure levels for each tested operating point. A linear behavior of discharge current and thrust values versus the anode mass flow rate was noticed for both pumping speeds levels and for all the three configurations. In addition, the thrust and discharge current values were always found to be lower at lower background pressure levels. From the performance levels, a preliminary estimate of the ingested mass flow rates was performed, and the values were then compared to a recently developed background flow model. The results suggested that, for this thruster and in the tested operating regimes, the change in performance due to background pressure could be ascribed not only to the ingestion of external mass flow coming from the chamber but also to other physical processes caused by the flux of residual background neutrals.

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