Publikationsdatum:
2019-07-13
Beschreibung:
The primary life-limiting mechanism of Hall thrusters is the sputter erosion of the discharge channel walls by high-energy propellant ions. Because of the difficulty involved in characterizing this erosion experimentally, many past efforts have focused on numerical modeling to predict erosion rates and thruster lifespan, but those analyses were limited to Hall thrusters operating in the 200-400V discharge voltage range. Thrusters operating at higher discharge voltages (V(sub d) 〉= 500 V) present an erosion environment that may differ greatly from that of the lower-voltage thrusters modeled in the past. In this work, HPHall, a well-established hybrid-PIC code, is used to simulate NASA's High-Voltage Hall Accelerator (HiVHAc) at discharge voltages of 300, 400, and 500V as a first step towards modeling the discharge channel erosion. It is found that the model accurately predicts the thruster performance at all operating conditions to within 6%. The model predicts a normalized plasma potential profile that is consistent between all three operating points, with the acceleration zone appearing in the same approximate location. The expected trend of increasing electron temperature with increasing discharge voltage is observed. An analysis of the discharge current oscillations shows that the model predicts oscillations that are much greater in amplitude than those measured experimentally at all operating points, suggesting that the differences in oscillation amplitude are not strongly associated with discharge voltage.
Schlagwort(e):
Spacecraft Propulsion and Power
Materialart:
AIAA Paper 2013-3887
,
GRC-E-DAA-TN10205
,
AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit; Jul 14, 2013 - Jul 17, 2013; San Jose CA; United States|International Energy Conversion Engineering Conference (IECEC); Jul 15, 2013 - Jul 17, 2013; San Jose CA; United States
Format:
application/pdf
