Investigation of the Initial Stage of the Discharge in an Ablative Pulsed Plasma Thruster

Abstract

Discharge development in an ablative pulsed plasma thruster is considered. Data obtained experimentally are analyzed. The time of the discharge-development stages is determined. It is revealed that discharge development is determined by the initial stage of the discharge. The initial stage of the discharge in a certain ablative pulsed plasma thruster is investigated. The problem of carbonizing the working surfaces of propellant bars in this thruster is considered. A mathematical model for charged-particle motion in the ablative plasma thruster at the initial stage of the discharge is generated. The main simulation results are presented. The electric field generated by a system of electrodes corresponding to the thruster is plotted theoretically. How the electric field influences the initial stage of the discharge in the ablative pulsed plasma thruster is investigated. The behavior of charged particles under low currents and magnetic field initiation is studied.