A three-dimensional full particle particle-in-cell with Monte Carlo collision simulation model is developed to study charge-exchange ion backe ow from a e eld-emission-electric-propulsion thruster using liquid cesium as a propellant. Contamination from backe ow of low-energy charge-exchange ions generated in the plume is an important spacecraft integration issue. Simulations show that the backe ow ion current is on the order of 0.01% of the total emitting current under typical thruster operating conditions. Nearly all charge-exchange ions are collected by the accelerator electrode close to the emitter. Operating a e eld emission thruster at lower neutral e ux, lower emitter current, or higher emitter potentials helps to reduce the backe ow current and possible spacecraft contamination. The operation of a neutralizer does not have a signie cant effect on the backe ow current under typical space plasma environments. A semi-analytical expression is also derived for quick estimations of the e eld emission thruster backe ow current. Nomenclature Aacc = accelerator area, m 2 Ae; Ai; An = exit area of the electron, ion, and neutral beam, m 2 a = emitter‐accelerator distance, m b = half of accelerator aperature, m C
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