Investigation of the Start Transient in a Hall Thruster

Abstract

A two dimensional axisymmetric fully kinetic Particle-in-Cell/Monte Carlo Collision (PIC-MCC) model is used to describe the ignition process in a Hall thruster. A current peak and latter the periodic oscillation of current and electric potential are found. The corresponding evolutions of plasma density, electric potential and atom density during the ignition process are introduced in the paper. In addition, influences of mass flow rate and discharge potential on current peak are modeled and analyzed. The simulated results are consistent with former experimental results.

Fast Camera Imaging of Hall Thruster Ignition

“…The results resemble simulations reported previously [1,2]. PIC simulations reveal strongly peaked (8x-10x steadystate mean) density and current before entering stable operation at 50 µs [2].…”

“…Recently, 2-D particle-in-cell codes have modeled plasma density, potential, and current during the ignition phase [1,2], but limited experimental evidence is available for comparison [3]. Here we contribute time-resolved images of the thruster ignition, revealing azimuthal spatial structure and an intensity peak lasting for an ionization-relevant timescale.…”

Experimental investigation of the effects of variable expanding channel on the performance of a low-power cusped field thruster

“…19 It also can be seen that models with expanding-angle have a higher maximum value of efficiency and impulse, while the optimal operating states are at larger mass flow rate.…”

“…It is known that compared with Hall thrusters, the cusped field thrusters start up with a relatively small ignition voltage and they are free from current impact (an instantaneous anode current peak in ignition, which would have an impact on power supply modules, usually in Hall thrusters). 19 In terms of physical mechanism, a central leak path in the channel was found in our recent Particle-in-Cell simulation, through which some electrons can arrive at the anode along the thruster centerline and give rise to the ignition at a relative low discharge voltage. 20 In the ignition process, the source electrons have to overcome the magnetic mirror outside the channel exit during a startup period in cusped field thrusters.…”

Magnetic field deformation due to electron drift in a Hall thruster

“…The PIC codes in our lab have been used in many other studies including ignition processes, near wall transportation, double stage Hall thruster, oscillation sheath and et al [13][14][15][16] These methods employ particle-in-cell with Monte-Carlo methods to deal with collision between ions and electrons. The model 14 is 2D-3V cylindrical coordinate and contains r, z, v (r,z,θ) .…”